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NASA Technical Memorandum 107486

Microgravity Environment Description Handbook

Richard DeLombard and Kevin McPherson

Lewis Research Center

Cleveland, Ohio

Kenneth Hrovat, Milton Moskowitz, Melissa J.B. Rogers, and Timothy ReckartTal-Cut CompanyNorth Olmsted, Ohio

July 1997

National Aeronautics andSpace Administration

https://ntrs.nasa.gov/search.jsp?R=19970022250 2018-12-01T05:30:44+00:00Z

Microgravity Environment Description Handbook ]

ABSTRACT

The Microgravity Measurement and Analysis Project (MMAP) at the NASA Lewis Research Center

(LeRC) manages the Space Acceleration Measurement System (SAMS) and the Orbital Acceleration

Research Experiment (OARE) instruments to measure the microgravity environment on orbiting space

laboratories. These laboratories include the Spacelab payloads on the shuttle, the SPACEHAB module

on the shuttle, the middeck area of the shuttle, and Russia's Mir space station. Experiments are

performed in these laboratories to investigate scientific principles in the near-absence of gravity.

The microgravity environment desired for most experiments would have zero acceleration across all

frequency bands or a true weightless condition. This is not possible due to the nature of spaceflightwhere there are numerous factors which introduce accelerations to the environment.

This handbook presents an overview of the major microgravity environment disturbances of these

laboratories. These disturbances are characterized by their source (where known), their magnitude,

frequency and duration, and their effect on the microgravity environment. Each disturbance is

characterized on a single page for ease in understanding the effect of a particular disturbance. The

handbook also contains a brief description of each laboratory.

[ Microgravity Environment Description Handbook I

TABLE OF CONTENTS

ABSTRACT ................................................................................................................................................ i

TABLE OF CONTENTS ........................................................................................................................... ii

ABBREVIATIONS AND ACRONYMS .................................................................................................. iv

1.0 Introduction ........................................................................................................................................ 1

1.10

1.1 Purpose ......................................................................................................................................... 11.2 Additional information ................................................................................................................. 1

1.3 Access to description sheets ......................................................................................................... 21.4 Description of laboratories ........................................................................................................... 2

Orbiter Middeck ........................................................................................................................ 2

Spacelab Module ....................................................................................................................... 3Spacelab MPESS ....................................................................................................................... 3SPACEHAB Module ................................................................................................................. 3

Mir Space Station ...................................................................................................................... 31.5 Orbiter coordinate system ............................................................................................................. 41.6 Spectral Analysis: Cutoff versus Nyquist Frequency ................................................................... 41.7 Signal Aliasing ............................................................................................................................. 41.8 Accelerometer Polarity ................................................................................................................. 51.9 Figures .......................................................................................................................................... 6

1. Orbiter body coordinate system ............................................................................................. 6

2. Orbiter structural coordinate system ...................................................................................... 63. Typical Spacelab Rack Layout .............................................................................................. 74. Microgravity Experiment Locations on the Orbiter .............................................................. 85. Typical Spacelab MPESS with experiments ......................................................................... 86. Typical Middeck Locker Layout ........................................................................................... 97. Earth-Oriented Orbiter Attitudes ......................................................................................... 10

8. Typical Spacelab module configuration .............................................................................. 119. Typical Mir configuration with docked Orbiter .................................................................. 12

References .................................................................................................................................. 13

2.0 Measurement Location Index ........................................................................................................... 14

I. Spacelab ModuleII. Cargo bay / Spacelab MPESSlIl. SPACEHAB moduleIV. Middeck

V. Keel BridgeVI. Mir Space Station

3.0 Cross Reference Lists ....................................................................................................................... 16

3.1 Disturbance Source .................................................................................................................... 163.2 Vehicle ....................................................................................................................................... 17

3.3 Primary Frequency .................................................................................................................... 183.4 Acceleration Magnitude ............................................................................................................ 203.5 No Discernible Effects ............................................................................................................... 21

ii


4.0 Microgravity Environment Description Sheets

I. Spacelab ModuleII. Cargo bay / Spacelab MPESSI11. SPACEHAB moduleIV. Middeck

V. Keel BridgeVI. Mir Space StationVII. Other

Appendices

A. Accessing SAMS & OARE data via the intemet ....................................................................... A1

B. Bibliography ................................................................................................................................ B 1

list of mission summary reportscompendiumdescription of SAMSdescription of OAREshuttle reference document

C. User Comment Sheet ................................................................................................................... C1

°°.

111

Microgravity Environment Description Handbook I

3DMA

a

APU

ATCS

BDPU

CG

DLR

DMT

DSO

DTO

EEPROM

EORF

EVIS

FCS

FES

f¢

f$

goGBX

GMT

Hz

ILRD

IML

IVIS

JSC

KSC

LeRC

LV / LH

LMS

LSLE R/F

MEPHISTO

_gMET

mgMMA

MMAP

MMD

MPESS

MSAD

MSD

Abbreviations and Acronyms

Three-dimensional Microgravity Accelerometer

acceleration magnitude

auxiliary power unit

Active Thermal Control System

Bubble, Drop and Particle Unit

Center of Gravity

German Aerospace Research Establishment (German acronym)

Decreed Moscow Time (ddd/hh:mm:ss)

Detailed Supplementary Objective

Development Test Objective

electrically eraseable programmable read only memory

Enhanced Orbiter Refrigerator/Freezer

Ergometer Vibration Isolation System

Flight Control System

Flash Evaporator System

Cutoff frequency (Hz)

Nyquist frequency (Hz)

Sampling rate (samples per second)

Earth's gravity acceleration level at sea-level (9.81 m/s 2)

glovebox

Greenwich Mean Time (day/hour:minute:second)Hertz

interlimb resistance device

International Microgravity Laboratory

Inertial Vibration Isolation System

NASA Johnson Space Center

NASA Kennedy Space Center

NASA Lewis Research Center

Local Vertical / Local Horizontal

Life and Microgravity Spacelab

Life Sciences Laboratory Equipment Refrigerator/Freezer

Materials for the Study of Interesting Phenomena of Solidification on Earth and in Orbit

microgravity (1/1,000,000 of go)

Mission Elapsed Time (day/hour:minute:second)

milligravity (1/1000 of go)

Microgravity Measurement Assembly

Microgravity Measurement and Analysis Project

Microgravity Measuring Device

Mission Peculiar Equipment Support Structure

Microgravity Science and Applications Division

Microgravity Science Division

iv


NASA

NIZEMI

OARE

OAST

OMS

PAO

PCIS

PIMS

POCC

PRCS

PSD

QSAMRCS

RMS

rpmRSS

SAMS

SIMO DumpSOR/F

STS

TDRSS

TEMPUS

TSH

TSS

_tgUSML

USMP

VRCS

VV

X_.A,¥h.A,Z_._Xh,B,Yh, B,Z-xB

Xh.c,Yb.c,Zh.c

Xo,Yo,ZoX_,Yb,Zb

XB,YB,Z_

National Aeronautics and Space Administration

Slow Rotating Centrifuge Microscope (German acronym)

Orbital Acceleration Research Experiment

Office of Aeronautics and Space Technology

Orbital Maneuvering SystemPublic Affairs Office

Passive Cycle Isolation System

Principal Investigator Microgravity Services

Payload Operations Control Center

primary reaction control system

power spectral density

Quasi-steady Acceleration Measurement experiment

reaction control system

root-mean-square

revolutions per minute

root-sum-of-squares

Space Acceleration Measurement System

simultaneous supply water and waste water dump

Sterling Orbiter Refrigerator/Freezer

Space Transportation System

Tracking and Data Relay Satellite System

electromagnetic containerless proccessing facility (German acronym)triaxial sensor head

Tethered Satellite System

microgravity (1/1,000,000 of go)

United States Microgravity Laboratory

United States Microgravity Payload

vernier reaction control system

velocity vectorSAMS TSH A axes

SAMS TSH B axes

SAMS TSH C axes

Orbiter structural coordinate system axes

Orbiter body coordinate system axesCoordinate notation for the Mir Base Block axes

V


1.0 Introduction

Fluid physics, materials science, combustion science, low temperature microgravity physics,

biotechnology and life sciences experiments are conducted on the NASA Space Shuttle Orbiters and on

Russia's Mir Space Station to take advantage of the reduced gravity environment resulting from the

continuous free fall state of low earth orbit. Accelerometer systems are flown with these experiments to

record the microgravity environment to which the experiments were exposed. This microgravity

environment is a complex combination of accelerations and vibrations generated by orbital mechanics,

vehicle subsystems, flight attitude, vehicle maneuvers, experiment equipment, and the crew.

Two common accelerometer systems flown to support experiments are the Space Acceleration

Measurement System (SAMS) and the Orbital Acceleration Research Experiment (tARE). These

accelerometer systems axe managed by the Microgravity Measurements and Analysis Project (MMAP)

within the Microgravity Science Division (MSD) at NASA Lewis Research Center (LeRC). These

accelerometer systems are flown in support of science experiments sponsored by the Microgravity

Science and Applications Division (MSAD) of the NASA Headquarters Office of Life and Microgravity

Science and Applications. Other accelerometer systems are occasionally flown in support of these and

other science experiments.

The Principal Investigator Microgravity Services (PIMS) project in the MMAP supports

principal investigators of microgravity science experiments as they evaluate the effects of varying

acceleration levels on their experiments.

1.1 Purpose

This handbook was prepared by PIMS to facilitate the interpretation of the microgravity

environment of the various vehicles and carrier combinations which are commonly used for micrograv-

ity science experiments. The intended users are principal investigators, mission scientists, mission

managers, project scientists, and the staff associated with the aforementioned personnel.

This handbook contains examples of microgravity environment disturbances which have been

observed from many missions, several vehicles and several experiment carriers. These disturbances are

first categorized by the source of the disturbance. Cross references are included that list the disturbances

by the vehicle, the location of the measurement, and the characteristics of the disturbance.

1.2 Additional Information

There may be times that a user needs information on a particular type of disturbance which has not

been included here. Please send a description of such disturbances to the PIMS project for

consideration. This handbook has been designed to be updated in the future with additional descriptions

as they are developed by PIMS. To obtain a copy or to "register" for updates, please send an appropriate

request to the following address.


Duc Tmong, PIMS Project Manager

Mail Stop 500-216NASA Lewis Research Center

21000 Brookpark Road

Cleveland OH 44135

Correspondence may also be made by telephone, fax or e-mall.Office number: 216-433-8394

Fax number: 216-433-8660

e-mall: pims @lerc.nasa.gov

Additional information for the missions supported by the SAMS and OARE accelerometers is

available in PIMS mission summary reports published as NASA Technical Memorandum reports. A list

of such reports is included in Appendix B. A copy of such a report may be obtained by contacting the

PIMS Project Manager. A World Wide Web site is also maintained by the PIMS project. Descriptions of

the environment, some mission summary reports, and links to SAMS, OARE & MMAP sites areincluded at this URL:

http://www.lerc.nasa.gov/WWW/MMAP/PIMS/

1.3 Access to description sheets

Each disturbance to the microgravity environment has characteristics of magnitude, duration, and

frequency content. These characteristics are affected by the location of the source, the structural

dynamics of the vehicle, and the measurement location.

Since most users limit their quest to their carrier or location, the disturbances contained in this

handbook have been categorized at the first level by the location where the measurement was made.

Cross reference tables are provided which categorize the disturbances by disturbance source, vehicle,

frequency, and magnitude.

The user must be aware that the categories are not mutually exclusive and that they do overlap one

another. A particular disturbance may be found in many cross reference tables and table headings.

1.4 Description of laboratories

Orbiter Middeck

The Orbiter middeck provides crew accommodations and contains three avionics equipment bays.

Modular stowage lockers are used to store the flight crew's personal gear, mission-required equipment,

and experiments. There are 42 identical lockers, which are 11 X 18 X 21 inches. An experiment is

either designed to fit inside a locker or replace one or more lockers. Individual microgravity science

Microgravity Environment Description Handbook [

experiments are flown on a space-available basis in the Orbiter middeck. Few support services are

available and, in general, mission parameters are not established by experiments in the middeck.

Additional information about the Orbiter middeck may be obtained from [1].

Spacelab Module

The Spacelab pressurized module, or laboratory, is a pressurized container connected to the Orbiter

middeck by a tunnel. Inside the module are experiment racks in which most of the experiment hardware

is installed. The mission crew members may operate the experiments in a shirt-sleeve, laboratory

environment. The Spacelab module is used as a primary payload on dedicated microgravity science

missions to operate a multitude of microgravity science experiments. The mission pararneters, such as

Orbiter attitude and crew timeline, may be optimized for microgravity science operations.

Additional information about the Spacelab module may be obtained from [2].

Spacelab MPESS

The Spacelab Mission Peculiar Equipment Support Structure (MPESS) is a truss structure with

support subsystems which mounts in the cargo bay of the Orbiter. The support subsystems supply

services, such as electrical power, data communications, and thermal conditioning, to the experiments

mounted on the MPESS. The experiments are operated remotely primarily by commands from a science

operations center or, in some cases, by remote crew interaction. These carders have typically been used

as partial Orbiter payloads with the mission parameters for microgravity science operations being

established for only part of the mission.

SPACEHAB Module

The SPACEHAB, Inc. developed the SPACEHAB module to function as a shirt-sleeve environment

laboratory similar to the Spacelab module and the Orbiter middeck and flight decks. The SPACEHAB

Double Module is one of a fleet of modules the company owns and operates. The modules fit into the

payload bay of Space Shuttles, providing laboratory and logistics resupply services to NASA, other

international space agencies, industry, and academia on a lease basis. SPACEHAB is the first company

to commercially develop, own and operate habitable modules that provide laboratory research facilities

and logistics resupply services aboard the U.S. Space Shuttle system, supporting people living and

working in space. [3]

Additional information about the SPACEHAB module may be obtained from [4].

Mir Space Station

Russia's Mir space station is a set of six interconnected modules forming an operational space station

that can be permanently staffed by two or three crew members. The crew work in a shirt-sleeve

environment operating experiments and performing housekeeping tasks. This complex is particularly

appropriate for long duration experiments or for multiple operations of the same experiment.

Additional information about the Mir space station may be obtained from [5,6].

[ Microgravity Environment Description Handbook ]

1.5 Orbiter coordinate system

The Orbiters have two basic orthogonal coordinate systems which are used to specify locations,

positions and orientations within the orbiter: the body coordinate system, and the structural coordinate

system. These are shown in Figures 1 and 2, respectively.

The body coordinate system (Figure 1) has an origin at the orbiter's center of gravity (CG). It is

oriented such that the direction from tail to nose is +X b, the direction from port to starboard is +Yb' and

the direction extending from the payload bay to the Orbiter belly is +Z b. Typically, this is the system

used to specify navigational directions and orientations such as for Local Vertical/Local Horizontal

(LVLH) attitudes.

The structural coordinate system (Figure 2) has an origin at the tip of the external tank. It is oriented

such that the direction from nose to tail is +X 0, the direction from port to starboard is +Y0, and the

direction upward out of the payload bay is +Z 0. Typically, this is the system used to specify the locations

of equipment within the orbiter.

1.6 Spectral Analysis: Cutoff versus Nyquist Frequency

All data acquired by SAMS has been processed using a lowpass filter prior to digitization. This is an

anti-aliasing filter with a roll-off of-140 dB per decade. Typically, the data sampling rate is 5 times the

filter cutoff frequency. This results in oversampling, so that frequency information above the filter cutoff

can be examined. However, the magnitudes of higher frequency disturbances (i.e. above the filter cutoff')have been attenuated.

The highest valid frequency present in the digitized data is called the Nyquist frequency, and is

denoted fN" Mathematically, this frequency is equal to one half of the sampling rate (fs)" The filter cutoff

frequency is specified alongside the sensor head letter, such as "TSH C, 25 Hz" in the data plots of this

handbook. In this example, sensor head C utilized a 25 I-Iz cutoff frequency. In order to obtain the

Nyquist frequency for the head, the sampling rate (f) must be divided by two. For example, a sampling

rate of 125 samples per second results in fN----62.5 HZ.

Spectrograms and PSDs are often shown containing information to the Nyquist frequency. The user

is cautioned that the magnitude of data above the filter cutoff frequency has been attenuated.

Even when imaged to the cutoff frequency, spectrogram plots are only a qualitative tool. Accurate

determination of gRMSlevels can only be made by an integration of a PSD, and cannot be performed

using the PSD magnitudes (colors) shown on a spectrogram plot.

1.7 Signal Aliasing

Signal aliasing is a phenomena caused during the analog-to-digital signal conversion process and

occurs when there are signals present above the Nyquist frequency (denoted fN)" The Nyquist frequency

4


is equal to one half of the sampling rate of the analog-to-digital converter. For example, for data

sampled at 125 samples per second, the Nyquist frequency is 62.5 Hz. Although the SAMS unit utilizes

a -140 dB per decade lowpass cutoff filter, signals which are high magnitude (or particularly close to the

sensor head) may not be fully attenuated above the Nyquist frequency. When this occurs, these higher

frequency signals appear to "fold-over" the Nyquist frequency, and appear as lower frequency signals in

the data, that is, they are aliased. However, these lower-frequency signals do not really exist, and have

no effect on experiments which may be sensitive to frequencies in these lower regions.

1.8 Accelerometer Polarity

The sign convention used for OARE is such that a forward thrust of the Orbiter is recorded as a

negative X b acceleration. This is consistent with a frame of reference fixed to the Orbiter.

The sign convention used for SAMS is such that a forward thrust of the Orbiter is recorded as a

negative X 0 acceleration. This is consistent with a frame of reference fixed to a fixed inertial point in

space.

For a detailed discussion of these two reference frames, including their origins, see [7].

5


+Yb -_ "xb

(Starboard)

-Yb (port)

+Xb (Xb, Yb, Zb) = (0,0,0)

Positive roll yaw Vehicle center of mass

+Zb

Figure 1. Orbiter body coordinate system

+Yo

(Starboard)

t/

I

tl1

I III CL Payload bay

(Xo,Yo,Zo)=(0,0,0)

-X o -Z o

Figure 2.

-Yo (Port)

Orbiter structural coordinate system

6

[ Microgravity Environment Description Handbook ]

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7


aeelab MPESS

Figure 4. Microgravity Experiment Locations on the Orbiter

ZENOSAMS-2

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AADSF

ZENO Electronics SAMS

Module

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MPESS Carrier

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11


®

1) U.S. Space Shuttle

2) Orbital Docking System

3) Kristall module: materials processing

4) Kvant II module: scientific

5) Soyuz transport vehicle

6) Spektr module: geophysical sciences

7) Priroda module: Earth remote sensing

8) Core module: habitation, power, life support

9) Kvant module: astrophysics

10) Progress vehicle

®

/

Figure 9. Typical Mir configuration with docked Orbiter

12

[ Microgravity Environment Description Handbook [

1.10 References

1). http:/_www.ksc.nasa.g_v/shutt_e/techn___gy_sts-newsref_sts_ver-prep.htm_#sts_ver-mpacc_m

2). http:/Iwww.ksc.nasa.govlshuttle/technologylsts-newsref/spacelab.html#spacelab

3). http://www.spacehab.corn/press/news2.html

4). http://www.spacehab.com

5). http://www.osf.hq.nasa.gov/mir/

6). http://liftoff.msfc.nasa.gov/rsa/mir.html

7). DeLombard, R., Compendium of Information for Interpreting the Microgravity Environment of the

Orbiter Spacecraft, NASA Technical Memorandum 107032, August 1996.

13


2.0 MEASUREMENT LOCATION INDEX

This index is based on where the measurements were made. The page numbers below are given by

the handbook section number and the page number within that section.

I. Spacelab Module

Glovebox ................................................................................................................................................ I. 1

Hydraulics .............................................................................................................................................. I. 2

Life Science Laboratory Equipment Refrigerator/Freezer .................................................................... I. 3

TEMPUS experiment ............................................................................................................................ I. 4

Ku-band Antenna ................................................................................................................................... I. 5

Centrifuge (crew member) ..................................................................................................................... I. 6

Crew sleep ............................................................................................................................................. I. 7

Ergometer (crew exercise) ..................................................................................................................... I. 8

PAt Event ............................................................................................................................................. I. 9

Structural modes .................................................................................................................................... I. 10

Rower (crew exercise) ........................................................................................................................... I. 11

Payload Bay Doors Opening ................................................................................................................. I. 12

Payload Bay Doors Closing ................................................................................................................... I. 13

Vernier Reaction Control System (reboost maneuver) .......................................................................... I. 14

Radiator Deploy ..................................................................................................................................... I. 15

H. Cargo Bay / Spacelab MPESS

Radiator Deploy .................................................................................................................................... II. 1

Ku-band Antenna .................................................................................................................................. II. 2

MEPHISTO experiment ....................................................................................................................... II. 3

Orbital Maneuvering System ................................................................................................................ II. 4

Primary Reaction Control System ........................................................................................................ II. 5

Vernier Reaction Control System ......................................................................................................... II. 6

Crew Sleep ............................................................................................................................................ II. 7

Flight Control System ........................................................................................................................... II. 8

Tether Satellite Deploy ......................................................................................................................... II. 9

Ergometer (crew exercise) .................................................................................................................... II. 10

lII. SPACEHAB Module

Centrifuge ............................................................................................................................................ HI. 1

Stirling Orbiter Refrigerator/Freezer ................................................................................................... 111. 2

Ku-band Antenna ................................................................................................................................. III. 3

14


IV. Middeck

Crew sleep ........................................................................................................................................... IV. 1

Ergometer (crew exercise) ................................................................................................................... IV. 2

Interlimb Resistance Device (crew exercise) ....................................................................................... IV. 3

PAO Event ........................................................................................................................................... IV. 4

Treadmill (crew exercise) .................................................................................................................... IV. 5

Ku-band Antenna ................................................................................................................................. IV. 6

V. Keel Bridge (low frequency measurements)

Aerodynamic drag - circular orbit ......................................................................................................... V. 1

Aerodynamic drag - solar inertial orbit ................................................................................................. V. 2

Aerodynamic drag - elliptical orbit ....................................................................................................... V. 3

Flash Evaporation System ..................................................................................................................... V. 4

Mission Low-Frequency Environment (IML-2) .................................................................................. V. 5a

Mission Low-Frequency Environment (USML-2) .............................................................................. V. 5b

Mission Low-Frequency Environment (USMP-2) .............................................................................. V. 5c

Mission Low-Frequency Environment (USMP-3) .............................................................................. V. 5d

Mission Low-Frequency Environment (LMS) .................................................................................... V. 5e

Attitude .................................................................................................................................................. V. 6

Thrusters ................................................................................................................................................ V. 7

Water dump (Supply water dumps) ..................................................................................................... V. 8a

Water dump (Waste water dumps) ....................................................................................................... V. 8b

Water dump (SIMO dumps) ................................................................................................................ V. 8c

VI. Mir Space Station

BKV-3 Dehumidifier ............................................................................................................................ VI. 1

Gyrodynes ............................................................................................................................................. VI. 2Mir structural modes ............................................................................................................................. VI. 3

Mir-Progress docking ........................................................................................................................... VI. 4

Mir-Soyuz docking ............................................................................................................................... VI. 5

Mir-STS docking .................................................................................................................................. VI. 6

Mir-STS undocking .............................................................................................................................. VI. 7

VII. Other Locations

DC-9 ................................................................................................................................................... VII. 1

15

[ Microgravity Environment Description Handbook I

3.0 CROSS REFERENCE LISTS

3.1 DISTURBANCE SOURCE CROSS REFERENCE

Disturbances are caused by various classes of equipment and actions. The page numbers below are

given by the handbook section number and the page number within that section.

I. Vehicle Subsystem Disturbances

Radiator Deploy ...................................................................................................................................... H. 1

Hydraulics ................................................................................................................................................ I. 2

Ku-band Antenna ........................................................................................................ I. 5, II. 2, HI. 3, IV. 6

Life Sciences Laboratory Equipment Refrigerator/Freezer ..................................................................... I. 3

Stirring Orbiter Refrigerator/Freezer .................................................................................................... HI. 2

Payload Bay Doors Opening ................................................................................................................. L 12

Payload Bay Doors Closing ................................................................................................................... I. 13

II. Vehicle Attitude and Maneuver Disturbances

Attitude ................................................................................................................................................... V. 6

Orbital Maneuvering System .................................................................................................................. II. 4

Primary Reaction Control System .......................................................................................................... iI. 5

Vernier Reaction Control System ........................................................................................................... II. 6

HI. Experiment Disturbances

Glovebox .................................................................................................................................................. I. 1

MEPHISTO experiment ......................................................................................................................... II. 3

TEMPUS experiment .............................................................................................................................. I. 4

IV. Crew Induced Activities

Centrifuge (crew member) ....................................................................................................................... I. 6

Crew Sleep ............................................................................................................................ I. 7, II. 8, IV. 1

Ergometer (crew exercise) ............................................................................................................. I. 8, IV. 2

Intedimb Resistance Device (crew exercise) ........................................................................................ IV. 3

PAO Event ..................................................................................................................................... I. 9, IV. 4

Rower (crew exercise) ........................................................................................................................... I. 11

Treadmill (crew exercise) ..................................................................................................................... IV. 5

16


3.2 VEHICLE CROSS REFERENCE

Disturbances peculiar to a vehicle are referenced here. The page numbers below are given by the

handbook section number and the page number within that section.

Orbiter

I. Subsystem

Radiator Deploy ...................................................................................................................................... II. 1

Hydraulics ................................................................................................................................................ I. 2



Stirling Orbiter Refrigerator/Freezer .................................................................................................... HI. 2

Payload Bay Doors Opening ................................................................................................................. I. 12

Payload Bay Doors Closing ....... ............................................................................................................. I. 13

II. Attitudes and Maneuvers

Attitude ................................................................................................................................................... V. 6


Primary Reaction Control System .......................................................................................................... II. 5


HI. Structural Natural Frequencies .................................................................................................. I. 10

Mir

I. Subsystems

BKV-3 Dehumidifier ............................................................................................................................ VI. 1

Gyrodynes ............................................................................................................................................. VI. 2

II. Attitudes and Maneuvers

HI. Docking





17


3.3 PRIMARY FREQUENCY CROSS REFERENCE

The primary frequency of a disturbance is used to classify disturbances in this table. The user must

be aware, however, that many disturbances do not produce an effect entirely at a single frequency. There

are often harmonics of the primary frequency, secondary frequency effects and broad spectrum effectsfrom disturbances.

The page numbers below are given by the handbook section number and the page number within thatsection.

I. Quasi-steady (f < 0.01 Hz)

Aerodynamic drag .................................................................................................................. V. 1, V 2, V. 3


Flash Evaporation System ...................................................................................................................... V. 4

Mission Low Frequency Environment .......................................................... V. 5a, V. 5b, V. 5c, V. 5d, V. 5e

Attitude ................................................................................................................................................... V. 6

Thrusters ................................................................................................................................................. V. 7

Water dumps ..................................................................................................................... V. 8a, V. 8b, V. 8c

II. 0.01 < f < 5 Hz

Crew exercise ................................................................................................... I. 8, I. 11, IV. 2, IV. 3, IV. 5

Structural modes .......................................................................................................................... I. 10, VI. 3

Centrifuge (crew member) ....................................................................................................................... I. 6

IH. 5<f< 10Hz

Structural modes .................................................................................................................................... I. 10

IV. 10 < f< 25 Hz

Ku-band antenna ......................................................................................................... I. 5, II. 2, IN. 3, IV. 6


BKV-3 Dehumidifier on Mir ................................................................................................................ VI. 1

Glovebox .................................................................................................................................................. I. 1

V. 25 < f<50Hz

Centrifuge ............................................................................................................................................. 11I. 1

Ku-band antenna ......................................................................................................... I. 5, II. 2, 1II. 3, IV. 6

Glovebox ................................................................................................................................................. I. 1

18


VI. 50< f< 100 Hz

Stifling Orbiter Refrigerator/Freezer .................................................................................................... m. 2

TEMPUS experiment .............................................................................................................................. I. 4

Ku-band antenna ......................................................................................................... I. 5, II. 2, HI. 3, IV. 6

VII. f> 100 Hz

Gyrodynes on Mir ................................................................................................................................. VI. 2

VIII. Transient


Primary Reaction Control System .......................................................................................................... II. 5






19


3.4 ACCELERATION MAGNITUDE CROSS REFERENCE

The acceleration magnitude of a disturbance has been used to classify these disturbances in this

table. The user must be aware, though that many disturbances do not produce an effect entirely at a

single magnitude at every occurrence. The purpose here is to categorize the disturbances according to

their rough order of magnitude. The page numbers below are given by the handbook section number

and the page number within that section.

I. a < 10 lag

Flash Evaporation System ..................................................................................................................... V. 4

Water dumps ...................................................................................................................... V. 8, V. 8b, V. 8c

II. a < 100 I.tg

Payload bay doors opening ................................................................................................................... I. 12

Payload bay doors closing .................................................................................................................... I. 13


III. a < 500 _g

Radiator Deploy ..................................................................................................................................... II. 1

Vernier Reaction Control System .......................................................................................................... II. 6

Crew Exercise .................................................................................................. I. 8, II. 10, IV. 2, IV. 3, IV. 5

IV. a < 1000 lag

Radiator Deploy ..................................................................................................................................... If.1

Hydraulics ............................................................................................................................................... I. 2

MEPHISTO experiment ........................................................................................................................ II. 3

Vernier Reaction Control System .......................................................................................................... H. 6


V. a > 1000 lag

Primary Reaction Control System ......................................................................................................... H. 5

Orbital Maneuvering System ................................................................................................................. H. 4


TEMPUS ................................................................................................................................................ I. 4

20


3.5 NO DISCERNIBLE EFFECTS

Some activities and actions on a vehicle are not sufficient to cause a noticeable perturbation to the

microgravity environment. These are included in this handbook to show that there should not be much

concern for the effects these actions have on the microgravity environment

Events analyzed and shown to not have discernible effects are cargo bay camera motion and cargo

bay door closing motions.

21

Microgravity Environment Description Handbook Io 1

GLOVEBOX

MISSION

STS-73, October 1995, USML-2

SOURCE OR ACTIVITY

The glovebox was flown in Rack 12 of the

Spacelab module during the USML-2 mission. The

glovebox allowed crew members to handle, transfer,

and manipulate experiment hardware in ways that

are not possible in the open Spacelab environment.

ACCELEROMETER

Ns ,,s

TSH C, 25 Hz

fs = 125 samples per second

MEASUREMENT LOCATION

Larger plot on reverse

EFFECT ON MICROGRAVITY ENVIRONMENT

The glovebox fans contribute to the microgravity environment, as seen in the first portion of the above

plot. As the fans were switched-off, the signals at approximately 13, 20, 39, 48, 51, 53, 58, and 61 Hz are

seen to cease.

For further information, contact Duc Truong

NASA Lewis Research Center, Cleveland, Ohio.

e-mail: [email protected].

Telephone: 216-433-8394. Facsimile: 216-433-8660

URL: http ://www.lerc.nasa.govAVWW/MMAP/PIMS/

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Microgravity Environment Description Handbook Io2

HYDRAULIC SYSTEM

MISSION

STS-65, July 1994, IML-2

SOURCE OR ACTIVITY

There are three independent hydraulic systems

that are used for operation of actuators to control

aero surfaces, main engine gimbals and valves,

landing gear, and nose gear steering. On orbit, the

hydraulic system's fluids are circulated periodically

by electric motor-driven circulation pumps in order

to absorb heat from a heat exchanger and distribute

it to all areas of the system.

ACCELEROMETER

Head A, 10 Hz



::! :.... .b.Module

F"] SPACEHAB Module

['7 Middeck

"-]Keel Bridge


11104

a.9

0,8

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When these pumps are activated, a transient acceleration on the order of 1 mg can be produced. These

pumps operate at 10,000 rpm (166.7 Hz) and normally run for several minutes at distinct times throughout a

mission. The only noticeable impact, however, has been the transient at turn on.





URL: http://www.lerc.nasa.gov/WWW/MMAP/PIMS/

0o

._| -.oo

8


REFRIGERATOR / FREEZER (LSLE)

MISSION


SOURCE OR ACTIVITY

The Life Science Laboratory Equipment

refrigerator/freezer was used during IML-2 to

preserve perishable samples for postflight analysis.

This refrigerator/freezer has a motor driven

compressor which cycles on and off to maintain the

temperature.


ACCELEROMETER

Ns s

Head C, 100 Hz



_iii::::::...::!:i:i:!:i:i:i:!:_:!:_ii:::_!:i_::::::.:......

iiiii_l_b Module

.... ===========================:::....

-'] SPACEHAB module ..............'::::_*:_::"

N e,

MBI_: Lil, Sdfaet [a_mor,/BC_F_m


Cycling of its compressor produced an intermittent oscillatory disturbance with a fundamental frequency

around 22 Hz and with second, third, and fourth harmonics visible below the filter cutoff frequency. The

LSLE operated for the duration of the mission with a duty cycle ranging from 9 to 13 minutes on and 16 to

25 minutes off. Root-mean-square acceleration levels resulting from this 22 Hz component are typically

about 400 gg_s. This refrigerator/freezer was also operated on STS-42, STS-47, and STS-78.



e-mail [email protected].


URL: http ://www.lerc. nasa. gov/WWW/MMAP/P IMS/

i

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Microgravity Environment Description Handbook I 1.4

TEMPUS

MISSION


SOURCE OR ACTIVITY

During IML-2, TEMPUS enabled investigators

to study various thermodynamic and kinetic

properties of different samples without

contamination from container walls. For each run, a

spherical sample is levitated by an electromagnetic

coil, melted, and then cooled. The TEMPUS

facility utilized a water pump with a nominal

rotational rate of 4800 rpm (80 Hz).

Larger plots on reverse

ACCELEROMETER

_SAMS ["'] OARE

Head C, 100 I41



mb

m_mb

10 4

to 4

11.10 _

_to"

_|O -a

III [IX_: _ _ Wee _mp

n I I I d d a n I

10 -P

10.1t

10-n

_ (H:_)


When this pump was operating (duration times ranging from 10 minutes to over 7 hours), it caused a

substantial disturbance around 80 Hz with a magnitude of 4 to 5 mg_s.





URL: http ://www.lerc. nasa govAVWW/MMAP/P IMS/

ft. 16._

_md _ 1o_o Hs

f_ 500.0 _m_km ptt _4

d_ 0.0_,0_12tt,i

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MEDS: TEMPUS Water Pump

001/ ,3:00 001_Mission Elapsed Time (Day/Hour:Minute)

MET Start at 001/03:00:00.897, Harming k=18

MEDS: TEMPUS Water Pump

I I I I I I I I

_4L-2

-7

-7.5

-8.5

-9

-9.5

-10

-10.5

-11

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0I ! I,o 2'o 3'o ,o 5'0 6o 7'o 8'o 9'o ,oo

_equency (Hz)

[ Microgravity Environment Description Handbook

Ku-BAND ANTENNA

MISSION


SOURCE OR ACTIVITY

The Ku-band antenna is located in the forward

portion of the payload bay on the starboard side of

the vehicle. On orbit, this antenna is deployed for

communications between the orbiter and the

Tracking Data Relay Satellite System (TDRSS). It

is dithered at 17 Hz to prevent stiction of the gimbal

mechanism to which it is mounted.


ACCELEROMETER

[_"SAMS 1"] OARE

Head C, 100 Hz


io-*,

]dEl)_gudlladC_,_ml_l:_UauA_u D_


Reaction torque forces at the base of the gimbal produce a distinct 17 Hz oscillatory disturbance which

acts as a beacon signal within orbiter acceleration data owing to its intensity and nearly continuous

operation. The intensity of this disturbance is variable, but root-mean-square acceleration levels resulting

from this 17 Hz component are typically about 100 gg_s. Its second and third harmonics at 34 and 51 Hz

are often quite prominent and the 85 Hz harmonic has also been seen.






Vlal C_ lOaO lit

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MEDS: Ku-Band Communications Antenna Dither a,,,,_,_ c_,i_T= 9.ill mm

I I I I I I I I I

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r .......... , ................. • ................... ; .................

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........................... ! ............ f ........... ! .......... ! ............ < ............ ! ............. . ............

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Frequency (I:Iz)

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i

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Time (rain)

I Microgravity Environment Description Handbook I. 6

CENTRIFUGE (crew member)

MISSION

STS-65, July 1994, [ML-2

SOURCE OR ACTIVITY

Experiment operations required a crew member

to mix liquid experiment components. In live video

downlink of this activity, the crew member was

observed to be swinging the sample bag around,

making full circles with his arm.

_°1___]"

i 0ii

_(_)

ACCELEROMETER

I's s

Head B, 5 Hz



_iii:i:::., .i:i:i:!:i:i:_::.:_.:.::::i:.::i:iii:i:i::::.:.:.....::iiii_ Module

D[_ SPACEHAB Module

["7 Middeck

D Keel Bridge

.........:.:-:::................:7,_O _"



The swinging frequency of the crew members arm (about 8 cycles in 10 seconds) and his alignment

imparted a 0.8 Hz disturbance mainly on the Xo and Zo axes where peak-to-peak acceleration levels reached

approximately 100 _g.






no,da, 5.0m MET Start at 008/22:09:23.977 [ML-Zfs= 23.0 ll_.plel per second Structurld Coordinatea

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-2

-4

10-4 Human CentrifugeI I I I I I I

I I I I I I I

0

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.

I

-2

-4

10-4

5 10 15 20 25 30 35

Time (sec)

I I I I I I I

'wll'i'}i

I I I I I I I

i

4

5_

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--2-

--4

0 5 10 15 20 25 30 35

Time (sec)

10 -4I I I I I I I

I I I I 1 l I

_5

II

0 5 10 15 20 25 30 35

Time (sec)

Microgravity Environment Description Handbook Io 7

CREW SLEEP

MISSION

STS-78, June 1996, LMS

SOURCE OR ACTIVITY

On single shift missions, the microgravity

environment becomes quiet during crew sleep.

During these periods, crew induced disturbances, as

well as disturbances from equipment requiring crew

interaction are minimized. The lower activity level

also leads to a diminished excitement of the vehicle

structural modes.

Notice the characteristic transition to sleep

shown in this spectrogram. Around MET

001/11:20, there is a diminished activity level

(notice the quieting of the microgravity

environment under 10 Hz; particularly at the

structural resonance frequencies). Then at MET

001/13:20, there is a further quieting of the

environment, lasting until MET 001/17:20, with a

subsequent increase again at MET 001/19:00. This

2-step quieting is characteristic of sleep periods,

apparently showing a gradual change in activity

during pre-sleep and post-sleep periods.

ACCELEROMETER

r-lo

Head C, 25 Hz



[-7 SPACEHAB Moduie::":::::_*i:iiiiii:_i:i:i!**!:*::::::-:_

N_mmm



Sleep during a single shift mission such as LMS results in acceleration levels in the 1 to 4 Hz range

below about 3 _gms. Vehicle structural modes, the Ku-band antenna, and refrigerator/freezer are the

primary disturbance sources during crew sleep. Due to signal aliasing, this plot shows apparent frequencies

in the 2-4 Hz region, aligned with the LSLE R/F operations. These aliases are a data artifact, and not

indicative of the true microgravity environment. See Section 1 for more information on signal aliasing.





URL: http://www.lerc, nasa.gov/WWW/M /P IMS/

,...,=1

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Microgravity Environment Description Handbook I 1.8

ERGOMETER (crew exercise)

MISSION


SOURCE OR ACTIVITY

The ergometer is a bicycle-type of exercise equipmentin that pedaling is the primary means of getting exercise.This equipment has been configured with various formsof isolation systems on different shuttle missions.

(1) Hard-mounted - No isolation is employed, it isbolted directly to the middeck or flight deck.

(2) Inertial Vibration Isolation System (IVIS) - This

isolation system is primarily aimed at combatting theside-to-side motion of the person who is exercising.Counter-weights are driven by the pedal shaft to be 180 °out of phase with the side-to-side motion.

(3) Passive Cycle Isolation System (PCIS) - Thissystem attempts to "free-float" the exercise equipmentvia four braided cable, wire-rope isolators.

(4) Ergometer Vibration Isolation System (EVIS) -This is a three-axis vibration isolation system. Theergometer Z-axis isolation is an active system ofcounterweights which react to the motion of the crewmember. The ergometer X- and Y-axis isolation isaccomplished by a two-axis slide on the floor of themounting assembly.

(5) Bungee isolation- In this configuration, arecumbent bicycle is suspended by a system of elasticbungee cords. These cords are secured to various pointson the surrounding shuttle structure. The suspensionsupport is primarily in the XY plane of the ergometer.

ACCELEROMETER

[ SAMS E[] OARE

Head A, 10 Hz



ii_i_.b. Module _

_,m_m N- l_'

Larger plot on reverse Tin(ha|)


The effects of exercising on the microgravity environment are seen mainly in the frequency range from

about 1 Hz to 4 Hz and last for the duration of the exercise. Depending on the particular crew member and

the vibration isolation used, typical acceleration levels in this frequency range can vary between 50 l-tg_s to

about 1 mg_s.




Telephone: 216-433-8394• Facsimile: 216-433-8660

URL: http://wwwlerc.nasa.gov/WWW/MMAP/PIMS/

C)

Frequency (Hz)

4_ t.,n

t-D

to

O

RSS Magnitude [loglo(g2/Hz)]

i ! i i

q


PAO EVENT

MISSION


SOURCE OR ACTMTY

Scheduled demonstration or question and

answer events with some or all of the crew

gathered in a single area.

Largerplo_ on reverse

ACCELEROMETER

I's s r-lo

Head A, I0 H_z


M_iiS_R_...b.:.MEoNuT LOCAT 'O N_

["-] Middeck _ J _ ])k

b_Zm_ 10

MI/tSmtattlQ_O4:$$:_.,,

[AO

I I I I I I I I i

I0

-t-

-2

Z

1o1' ::::::::::::::::::::::::::::::::::::::::: fi::::::


It is common that when PAO events take place, the microgravity environment becomes quieter. The

crew is typically not moving about or impacting the spacecraft structure, they are usually free-floating in

front of a camera. Also, experiment operations involving crew interaction are not being conducted for the

duration of the PAO event. This tends to reduce the overall acceleration background level below 10 Hz to

less than 50 lag_s. Vehicle structural modes and the Ku-band antenna are the primary disturbance sources

during PAO events.





URL: http ://www. lerc. nasa. gov/WWW/MMAP/P IM S/

-2 i i i J i i i I i

0 0.5 1 1.5 2 2.5 3 3.5 4 4.5Time (ram)

10 "10 :: ....................... _ ............ : ............ !

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................. ! ............

.............. !,

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......... ! ........ ! ........ _...... _ ..... _.........................................

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Freqe_.ey(I-lz

Microgravity Environment Description Handbook ] 1.10

STRUCTURAL MODES

MISSION

STS-65, July 1994, 12VIL-2

ACCELEROMETER

_SAMS ['-'] OARE

SOURCE OR ACTIVITY

Any structure, including the Orbiter, has natural

frequencies characteristic of its underlying

construction. These depend on many factors such

as mass distribution, materials used in its

fabrication, construction method, and so on.

104

io _, i i i , i i I i ,o i z _ 4 s _ T I 9 io

io_1 J i , i i i i i io 1 1 _ 4 S _ 7 a

IO_, , i , I i , , i i i


Head A, 10 Hz


[--']Micldeck __ _

.... Largerplotsonreverse _ _._lt_____

1it' -

, ; _ , ; ,0_mr_n_ ffm

Nominally, the spectrum below about 10 Hz is dominated by the structural modes of the Orbiter. As

shown in the single axis plot, the shuttle has significant structural modes at about 3.6, 4.7, 5.2, 6.2, 7.4, and

8.5 Hz for the Spacelab module mounted in the cargo bay. Transient and oscillatory disturbances will excite

these modes. Most notable is the response to thruster firings and crew exercise. As seen in the 3-axis plot,

the structural modes at 3.6 and 5.2 Hz are aligned primarily with the Orbiter structural Yo-axis, while the 4.7

Hz mode is felt strongest on the Orbiter structural Zo-axis. The modes at 6.2 and 7.4 Hz have components

in the Orbiter structural XZ-plane, while the 8.5 Hz mode is most pronounced on the Xo-Axis. Some of the

Orbiter natural frequencies have been identified. For example, the 3.6 Hz mode corresponds to fuselage

torsion wing and fin bending. The 5.2 Hz mode corresponds to fuselage first normal bending and the 7.4 Hz

mode corresponds to fuselage first lateral bending. Structural modes associated with the payload bay doors

and radiators are discussed on separate pages of this handbook.oeA





URL: http ://www.lerc.nasa.gov/WWW/MMAP/PIMS/

I-r__ A, lOHz6_50 s_p/_m per mcc_d $b'ur..a_mlModumd1_0.048528 FIg Hlmnlng Wtndow _k=1166)

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i i i i i i i i i1 2 3 4 5 6 7 8 9 10

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|0 -% I I I I I I I I I0 1 2 3 4 5 6 7 8 9 lO

0 1 2 :B 4 5 6 7 8 9 10

Frequency (Hz)

1.11

ROWER (crew exercise)

MISSION

STS-42, January 1992, IML-I

SOURCE OR ACTIVITY

The rower is hard-mounted to the Orbiter

middeck. There is an interface frame which allows

the rower to be installed in place of any seat. Crews

have also performed some resistive type exercises

(bicep curls, squats, etc.) which they have adapted

to meet the machine's operating characteristics.


ACCELEROMETER

Ns s

Head C, 100 Hz


MEASUREMENT LOCATION_

U ...... !i-.'_:.:.:_::i:-:_:i::.> ::" .:::

[--1 Keel Bridge "-,,./_¢" _"_.. :_


The rower exercise causes both fundamental and harmonic disturbances to the microgravity

environment. In this spectrogram, the exercise begins at approximately MET 005/00:18, and ends at

approximately MET 005/00:30. Variations in frequency with respect to time are characteristics of exercise

in which the astronaut can change the pace of the exercise as they are working.

The table on the reverse side gives a select summary of the l.tgms levels associated with rower exercise.





URL: http://www.lerc.nasagov/WWW/MMAP/PIMS/

[(zl-Ivr=)=Iog_m_ ss'4

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I__l i:]P ::: i:':i:? i. Microgravity Environment Description Handbook I 1.12

PAYLOAD BAY

DOORS OPENING MOTION

MISSION


SOURCE OR ACTIVITY

The payload bay doors consist of left- and right-

hand doors hinged at each side of the mid fuselage

and latched mechanically at the forward and aft

fuselage and at the split top centerline. Each door

actuation system provides the mechanism to drive

its door to open, intermediate, or closed positions.

Each mechanism consists of an electromechanical

power drive unit and 6 rotary gear actuators.


ACCELEROMETER

r-lo

Head C, 25 Hz


MEASUREMENT LOCATION /_

C argo::_a_i::__...Mp E S S0"_ " ''::_:::::.":i:i:i:i::':.:_.::.:._.

r-] SPACEHAB module ..................;:_:_.....

rl Middeck _ _/_k

D eel nd e

_'°_ n i i i i n i i i

-_cL.............. 4.. tlla..

•., _Ii0 s no ts zo _"--_Cmo) so ss 4o 4s so

,t tO"

1... ;.r.. 2- tt',4 o $ io IS I /J I IS 441 45 I -

_ .

-,1- l/io s 10 15 ZO Z.5 10 )S _ _ 50

"r_,(mml


The impact of moving the payload bay doors to a more open position is seen most clearly on the ¥o and

Zo axes. The peak acceleration vector magnitude during door motion can approach 1 mg and this motion

has been seen to excite the 0.4 Hz payload bay door structural mode.





URL: http ://www.lerc. nasa. gov/WWW/MMAP/P IMS/

0

0

u _

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......... }J15 10 15 20 25 30 35 40 4.5

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10 4i i i i i i i i i

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Microgravity Environment Description Handbook I. 13

PAYLOAD BAY

DOORS CLOSING MOTION

MISSION


SOURCE OR ACTIVITY

The payload bay doors consist of lef_- and right-

hand doors hinged at each side of the mid fuselage

and latched mechanically at the forward and aft

fuselage and at the split top centerline. Each door

actuation system provides the mechanism to drive

its door to open, intermediate, or closed positions.

Each mechanism consists of an electromechanical

power drive unit and 6 rotary gear actuators.

.[.

o 1 1 } 4 5 6 I ! g IO1"I| ( llill

O,J

;'o31 _t' 1 'l i, rt}q _

., .L ' io i 2 _ 4 'I'5oi_{_) 6 7 s 9 io

ACCELEROMETER

Head C, 25 Hz


ME_iS_bMMEoNduTLOCATIO N__,

Keel Bridge _ _'-_._ _



No obvious impact for the partial closing of the payload bay doors has been identified in the SAMS

data.





URL: http ://www. lerc. nasa.gov/WWW/MMAP/P IMS/

MET Start at 005/00:25:59.998

MEDS: Payload Bay Doors ClosingI f I I

USML-2

Stractamd Co_'dtngta

I I I

0 1 2 3

10 "3I

I i I I

4 5 6 7Time (min)

I I I

01

2

I I I I I I I I

I I 1 I

4 5 6 7

Time (rain)X 10 .3

0.5

0 1

I I I 1 I I

I I I I l I

2 3 4 5 6 7Time (rain)

I

9 10

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_i_i_J,_ __,) I Microgravity Environment Description Handbook1.14

"v

VERNIER REACTION CONTROL

SYSTEM (Reboost Maneuver)

MISSION


SOURCE OR ACTIVITY

During LMS, a detailed test objective called the

Vernier Reaction Control System Reboost

Demonstration was performed to demonstrate

reboost capability for the Hubble Space Telescope

on the STS-82 mission.

SAIM.S Dim fl_ VRC$ Rdmoll I_laema-atmm

io _ io" io

o _1 _2 o Lo4 _1 _z 0 _1 ca

_::_::_::_ Largerplots

_'*'l_vr'l_ '0--7__ _'1 '°]_WI on reverse


ACCELEROMETER

_SAMS _ OARE

Head A, 10 Hz



ii__:---MOdule

0 Keel Bridge '__I

mEW slut OlJCl_tl 3_.I_ +

/

+.-...: -.--. -..............

o I a + ,+ + + + i ,) tom,m

During this test, the Orbiter was in a -XLV/-ZVV attitude while two pairs of VRCS jets (F5L/F5R and L5D/RSD)

were alternately fired in a precise pattern to slightly raise the Orbiter's altitude. This pattern can be seen in the figure

on the right where the forward (FWD) and AFT vernier jet firings are indicated by the top and bottom rows of "+"

markers, respectively. As a result, the Orbiter was boosted to a higher altitude as is suggested by the pitch angle data

plotted at the top of the figure on the right. The acceleration vector magnitude during this test did not exceed 2.5 mg,

and was nominally below about I mg, not much above the background acceJeration environment. The power spectral

density plots of the figure on the left show the acceleration spectra below 0.2 Hz from three different time frames for

all three Orbiter sla'uctural axes, Xo, Yo, and Zo, from top to bottom. The left-most column of plots corresponds to a

time frame just before the VRCS reboost. Plots in the center column were computed from accelerations measuredduring the test and the right-most column of plots corresponds to a time frame which occurred not long after

completion of the test. Comparison of the "during" spectrum to both the '_efore" and "after" spectra reveals that the

VRCS reboost excited the low frequency acceleration environment (below about 0.1 - 0.2 Hz) primarily on the Xo and

Zo axes. Most notably, the excitation produced an increased magnitude around 0.04 Hz.






MBT St*at at 015/19:21:59.983 u,s

VRCS Reboo*t Danoe,fm_c_ s,_._e.,_,.

u v i

95

._ 85

FWD

APT

t

t 2

t u u r i t

+ + ÷ ÷ + + + ÷ ÷ ÷ _- +.4- + 4-

+ + + ÷ ÷ ÷ ÷ 4,._ + ÷ +÷ + +

..(-i), + ÷ ÷ 4- ÷ +

÷ ÷ ÷ ,H- + -g- ÷ + 4,,++ ,.F _ -F

1 2 3 4 5 6 7 8Time (m/a)

9 I0

SAMS Data for VRCS Reboost Demonstra_.on

BBFOREi0 -_

I04

_ 10-1° _

i0 -_

0 0.1 0.2

i0_

e_

lO-"

i

0.1 0.2

LO -4

i0 4

i0 to

I0-_

DURING

10 4

104 __i0 -_

i0 -n

0.04 0.i 0.2

10 4

10 4

I0-_

10-n

0 0.04 011 0.2

IO_' i

I°41o_.l"v-v,

to-'[i

() 0.04 0.I 0.2

Fr_uency (Hz)

AFFflR10 4

10 4

i0-I°

i0 -u

0 0.1 0.2

10 4

0 0.I 0.2

lO _

10 4

i0 -n

0 0.I 0.2

Microgravity Environment Description Handbook 1.15

RADIATOR DEPLOY

MISSION


SOURCE OR ACTIVITY

Radiator panels attached to the forward payload

doors are part of the Active Thermal Control

System which provides orbiter heat rejection during

a mission. Depending on particular mission

requirements, these radiator panels may be

deployed at different angles and may be reoriented

during the mission. In order to deploy each

radiator, six motor driven latches must first be

unlocked, and then the radiators are moved by a

motor with a torque-tube-lever arrangement.


ACCELEROMETER

[_SAMS ["] OARE

TSH A, 10 Hz



10 aPoll _ Jllor [_pl e,/_ I.MS,3AM$ T3H.A

to 4 ......

LO_

,_|0 _

t i i i I i t i tI 2 I 4 _ 6 7 t 9 10


When these doors are moved, transient disturbances are imparted on the orbiter structure by means of

six motor-driven latches. These transients can reach magnitudes of 0.3 mg

The above figure shows 3 overlapping PSDs, plotted for 25 second periods before deploy, during

deploy, and after deploy of the port radiator. The during deploy period shows the presence of 6.30 Hz and

9.47 Hz peaks. After the deploy is completed, there is a 3.37 Hz peak present in the data.





URL: http://www.lerc, nasa.govAVWW/MMAP/PIMS/

Microgravity Environment Description Handbook II. 1.............J

RADIATOR DEPLOY

MISSION

STS-62, March 1994, USMP-2

SOURCE OR ACTIVITY

Radiator panels attached to the forward payload

doors are part of the Active Thermal Control System

which provides orbiter heat rejection during a

mission. Depending on particular mission

requirements, these radiator panels may be deployed

at different angles and may be reoriented during the

mission.

a

ACCELEROMETER

r-lo

Unit F, TSH A, I0 Hz


MEASUREMENT LOCATION ,/__j

_ Spacelab Module __

DIP/ // /



When these doors are moved, transient disturbances are imparted on the orbiter structure by means of

six motor-driven latches. These transients can reach magnitudes of 0.3 mg.





URL: http ://wwwlercnasa g°v/WWW/MMAP/P IMS/

F_

o

v

Microgravity Environment Description Handbook I II. 2

Ku-BAND ANTENNA

MISSION


SOURCE OR ACTIVITY









ACCELEROMETER

N'g s

Unit F, Head B, 25 Hz


MEASUREMENT LOCATION _

_., Spacelab Module __

_ SPACEHAB Module _/:_

[--7 Keel Bridge

m ta M_" +lllt it 011.tll:_00,|2[, Rllm I I_11 o9

"-7_r ......

libi_ Ml_'_ltllt it 0,LI/lI:0_G0,321. [tlltll I _1 119



acts as a beacon signal within orbiter acceleration data owing to its intensity and nearly continuous operation.

The intensity of this disturbance is variable, but root-mean-square acceleration levels resulting from this 17

Hz component axe typically about I00 I-tgms. Its second and third harmonics at 34 and 51 Hz are often quite

prominent and 85 Hz has been seen on the other carriers, using higher frequency sensor heads.






MET Start al 011/21:00:00.321, Harming k=t09

MEDS: Ku-Band Antenna Dither (MPESS Measurement)

I I 1

2'0 30 ,'oFrequency (Hz)

MET Start at 011/21:00:00.321, Hmming k= 219

MEDS: Ka-Bmd Antmma Dithc¢ (MPESS Me.a.mrement)

i

IJ_Mp-_

Sm_InDJ Comdll

-7

15

10 ¸

10

-8

-9

-10

-11

-L2

-13

20 30 4O 50

Time (mm)

mz_

Microgravity Environment Description Handbook II. 3

MEPHISTO

MISSION


SOURCE OR ACTIVITY

A valve was closed on the Materials for the

Study of Interesting Phenomena of Solidification on

Earth and in Orbit (MEPHISTO) furnace

experiment. This valve was latched during

experiment operation to observe the effect of the

vibration on the furnace sample.


t 10 4

!

2 4 6 10 12 14 16 1|

ACCELEROMETER

Unit F, Head A, 10 Hz



_.. Spacelab Module

E_ SPACEHAB Module / /

['7 Middeck _ if/."

[-7 Keel Bridge __

_J

o 2

iilo 2

o 2

14m_ MI_BI_I'O I._m ommg,

m

i l

r- ........... iilj

!; t'o 11 _, i* _;

"ri, _)

• i . _o ........)

4 6 I to 12 t4 14 1!


Closure of a valve used in the experimental apparatus was noticeable in the acceleration data. The effect

was a transient disturbance reaching about 1 mg, which excited a resonant damped ringing at 4.8 Hz evident

primarily in the Zo-axis.





URL: http ://www.lerc. nasa gov/WWW/MMAP/PIMS/

_- IQo_q_ prr _a_d

10 .3[

0.75 •

J

_ 0.5-

>

i

0

I I I

i

I I l r T

2 4 6 8

Start at 011/10:14:44,998 u_tra,

MEDS: MEPI-IISTO Latch Closing sc_=Jeo_a._

I I I I I I

10 12 14 16 18

Time (sec)

7

3.5'

-3.5

-7

0

3.5

0

-3.5

104I I

MET Start at O11/10:14:44.998

mu:,s:ME_STOa_ clo,_I I I I

i2 ; 6 8 10 12 14 16 18

Time (see)

I I I I

I0 aI I I I I

-7

x 10 47

3.5-

, 0 :.=N

-3.5

-7o i

_0 _'2 1', 1'_ 1'_Time (see)

I I I I I I

; _o G _ :_ _'sTime (s,_')

@

_!_i_ii _ _) [, Microgravity Environment Description Handbook II. 4

ORBITAL MANEUVERING SYSTEM

MISSION


SOURCE OR ACTIVITY

The OMS is used to place the vehicle in orbit, for

major velocity changes and to slow the Orbiter for

reentry.


L w Mm' sire m _?:o_._.m

L .......r

mm_

io

°'°( t

20 4O T _lO N 100

p----,

o 20 4o Tlim ) no too

==7 = lit

ACCELEROMETER




_.... Spacelab Module

DS,A Mo o '-7[_ Middeck f I/

m

o.ol --

o---

2o

IdEff _tln it 0oJ¢lTz0_.Jg._

40 60 JO 1_ 120

o Z0 _0 .rlli_0m ) te 100 llm* (_)


When the OMS engines are fired, initial transients in excess of 50 mg have been observed and net

accelerations on the order of 20 mg lasting for as long as 40 seconds occur primarily in the -Xo direction.

Due to the alignment of the engines, the accelerations occur primarily in the Xo axis.






gb I_ amltlllgt_

0.06

MET $tMt at 009/17:05:59.9911 _w

Mm_si omud Mn_vo-al Sym= IOMS)

o._.

o.

_.03 '

-0.06

0,06

0.03-

-0.03

-0.06

0.06

0.03

•0.03 -

_0.06

i i I i i

20

(_)

i i i I

i

A ;,o Bo t_o

b,. LZ_Om Ira' _d

0.0_-

0.06 o

_ 0.04->

0.02

MET Start at 009/17:08:59.998

MEDS: Orbital Maneuvering System (OMS)

J. .L J.

u'lgm_

$tr_mmg cem_mmm

T T T T -r

2O 4O 6O 8O

Time (sec)100 120

v

__/I " -" _ >.::¸:::¸'.5 : I Microgravity Environment Description Handbook I II. 5

PRIMARY REACTION

CONTROL SYSTEM

MISSION


SOURCE OR ACTIVITY

There are 3 8 Primary Reaction Control System

(PRCS) thrusters located on the Orbiter These are

used on orbit to provide attitude pitch, yaw and roll

maneuvers as well as translational maneuvers.


L

I

0,045

;I

20

MJ_" SIvA M 010/17:12:00570

M 81)$: _mr_ ltlcU_ Colt ml _Tmms (PL<3_) _

i i i i i i i i

LLLL,,,160 110 200 Z20 _0

ACCELEROMETER

[_ _'SAMS ["-] OARE




E1 aoo'+Mo u'o

E ] Keel Bridge

MBD_ filmily m.mml+_ _mI S_ ([9,CS) _

o.oa , I I i i i

o+0U -

41

'll

_ _OL-

i


The impulsive nature of PRCS thruster firings produce relatively high acceleration levels ranging from 6

mg to about 55 mg for typical durations between tens of milliseconds and seconds. These impulsive events

also typically excite orbiter structural modes at 3.5, 4.7, and 5.1 Hz. These structural excitations lead to the

"ringing" behavior after the event as seen from 15 - 25 seconds in the plot on the right.





URL: http ://www.lerc. nasa.gov/WWW/MMAP/P [MS/

0.06

MET Star a1010/17:12:00.570 tm_,-a,

MEDS: PrimaryReactionConl_"olSystem (PRCS) sv._ _

I I I I I I I 1

0.045

0.03'

0,015-

LLLL LLL L0 I I I I I ----I | I i I I i i I 11 L

0 20 40 60 80 100 120 140 160 180 200 220 240

Time (sec)

h- L_.O m _ mralid

0.02

0.015-

MET Start at 012/21:29:23.992 tmaP-2F

MEDS: Prm_y Reaction Control System (PRCS) swn,_c_iJ,

I I I I

0,005

V

0

o 10 15 20 25 30

Time (sew:)

Microgravity Environment Description Handbook IIo 6I

VERNIER REACTION

CONTROL SYSTEM

MISSION

STS-75, February 1996, USMP-3

SOURCE OR ACTIVITY

There are six Vernier Reaction Control System

(VRCS) thrusters used for fine adjustment of

vehicle attitude. Two VItCS thrusters (F5R, F5L)

are located in the nose of the orbiter, while four

other VR.CS thrusters (R.51L R5D, L5L, L5D) are

located in the tail.

LJRh

0¢-J

-It,-5

PJL

n _,_$

2o5

1#-6

MBT Stox 101iiol: 0C:o_ OILS

v_ Illrlali| (_L & ,_R)

0 0 0 0 0 a

O O o o ss _O o

÷ ÷ ÷ ÷ _-

T_ 20 11 3O5 t0 _a)

o o o o o a ]

o o o o m o1¢1 o

÷ ÷ ÷ + ÷ .

tO lJ 20 2_ 30

"flare (roll

7_-5 .....

_L 0 0 0 0 0 o

F_R 0 0 0 0 • om o o

_L_J 10 tl 20 23 3O

ACCELEROMETER



MEASUREMENT LOCATION _._

_. Spacelab Module __

rq oaulo 71 N

D Keel Bridge _



The effects of VgCS thruster firings are not as noticeable as PRCS firings. Typical peak acceleration

levels range from 0.3 mg to 0.7 mg. In the above figure, individual firings of the F5R and F5L jets are

indicated by "o" symbols, while combined (simultaneous) firings are denoted by a "+". Notice the tendency

for increased acceleration impulses in the Zo-axis during these simultaneous firings.






Head B, 25.0 lq_

fs,- 125.0 sampleu p_ seconfl

7e-5

F5L

F5R

F5L & F5R

3e-5I

2e-5

le-5

Oe-5

-le-50

MET Start at 010/04:00:00.895 usm-3F$trttettmtl Co_eatnat_

I0 second Interval Avaltge

VRCS Firings (F5L & F5R)I t I I !

0 0 0 0 0 0

o o o o o coo o

+ + + + +

I I I I I

5

TII

J

10 15 20 25 30T'lme(min)

7e-5

F5L

F5R

F5L & F5R

3e-5!

;_ 2e-5

le-5

0e-5

-le-50

I I I I I

0 0 0 0 0 0

0 0 0 0 0 O0 0 0

+ + + + +

I I I I I

5

il

10 15 20 25 30Ttme(min)

7e-5

F5L

F5R

F5L & F5R

3e-5u

N 2e-5

le-5

Oe-5

-le-5

I I I I I

0 0 0 0 0 0

0 0 0 0 0 000 0

+ + + + +

I I I I I

g

.--4II

0 5 10 15 20 25Tune (rain)

30

Microgravity Environment Description HandbookII. 7

CREW SLEEP

MISSION


SOURCE OR ACTIVITY




ACCELEROMETER

r-'lo




Spacelab Module _

_-] SPACEHAB Module ' /

F_Middeck _ _


Crew sleep times during a single shift mission such as USMP-2 result in acceleration levels in the 1 to 4

Hz range below about 10 _tg_s. Vehicle structural modes and the Ku-band antenna are the primary

disturbance sources during crew sleep. VRCS firings continue to affect the environment, as evident by the

broad-band (vertical yellow-green) disturbances in the color spectrogram plot.





URL: http://www.lerc, nasa.gov/WWW/MMAP/PIMS/

H.ml L 2_.0 Hi

It- 12_0 uu_m Ira"

dP= 0.0_2 HI

lO 6

lO 7

IO s

_ /0 .9

10 4o

i04x

i04z

MET Star[at00g/I0:[9:59.996,Harming k=18 ,Js_P-_

MEDS: Crew Sleep (MPESS Measurement) _

1 I , ..... I

......... Z ...........................

::::,: :!::_:::::i:ii::!:!,,i_._ ::::::::::::::::::::::::::::::::::: ..... ::! .,!.! :: :!.::::[:::.!;,,,i::: ii!: ::!, _::: i,::..

:!!_.::_._..:::!!!!!!!!:_.!:.,!!....!....!........_......:: :!_::!:ii!_.!!)!!!:!!!'!!iii.!!!,_!_-i!!:_!:.::................... i ...... i..

............. 2 _:........... 22£2 ii.i iiiiii_i, i ill .i ,i , i iiiii i;i , 21 'i iii _ iii. i

Z "

I

Frequency fflz)

2O

10

MET Start at 008/10:00:00.913, Hm_ning k: 219

MEDS: Crew Sloop (MPESS M_mt)

5O

t_flO.2F

W Oam_tmm_

-7

-8

-9

-10

-11

-[2

-13

-14

20 30 40Time (rain)

i Microgravity Environment Description Handbook ] II. 8

FLIGHT CONTROL SYSTEM

MISSION


SOURCE OR ACTIVITY

Approximately one day before scheduled re-

entry, a two-part checkout procedure is performed

to verify operations of the Orbiter Flight Control

System (FCS). The first part of this checkout uses

one of the three auxiliary power units (APUs) to

circulate hydraulic fluid in order to move the

rudder, elevons, and ailerons of the Orbiter. As an

APU is activated, exhaust gas is vented in the +Zo

direction. The result of this venting is similar in

nature to a VRCS jet firing, ranging from nearly 0

to 30 pounds of force. The exhaust does not vent as

a steady stream, but cycles at approximately 1 to 1.5

Hz.


ACCELEROMETER

[_SAMS E] OARE

Unit G, Head A, 5 Hz



_-] Spacelab Module _

r--I o<,u,0 '

" Milr _Itln l_Ol$1t_O_ O0.1'T#,ililmil l_i'#

m

"film {llll)


The figure above shows a SAMS Unit G TSH A spectrogram showing the extent of the first part of the

FCS checkout. The activation of APU1 is identified at about 3 minutes into the plot by a sudden change in

acceleration characteristics. Of particular note is the appearance of a 1.3 Hz signal and several upper

harmonics. These signals remain in the data throughout the checkout period, with slight shifts in the

frequencies about 13 and 18 minutes into the plot. Broadband excitation of the microgravity environment

about four minutes into the plot appear to be correlated with changes in APU1 turbine activity, as are the

shorter excitations between 20 and 27 minutes into the plot.





URL: http ://www.lerc. nasa.gov/WWW/MMAP/P IMS/

[(zI-I/:_)°E3oO_pmm_I_I SS_[


TETHE R SATELLITE

SYSTEM DEPLOY

MISSION


SOURCE OR ACTIVITY

The deploy operation of the Tether Satellite

System (TSS) deployed the experiment

approximately 12.8 miles (20.7 km) overhead of the

orbiter Columbia.


_ MEt am J 001_0_ i S_ m_

ACCELEROMETER

_SAMS [-'] OARE

Unit F, Head A, 10 Hz



D Spacelab Module _ ,,

r-G d ook f tl l/ I


The deploy of the satellite and tether caused two primary effects in the microgravity environment. The

first effect is illustrated by the variable frequency disturbances in the spectrogram between 5 and 20 Hz.

These disturbances were caused by the various pulleys used in the cable deployment mechanism.

The other effect is the gradually increasing quasi-steady levels primarily seen in the Zo-axis. These

changing levels are due to the gradual motion of the vehicle (Orbiter and TSS) center of mass location from

within the Orbiter cargo bay to a position between the Orbiter and TSS. Gravity gradient and centripetal

accelerations were then introduced into the SAMS measurements. At a separation distance of 20 km, the

quasi-steady acceleration level was increased by about 50 mg.





URL: http://www.lerc.nasagov/WWW/MMAP/P IMS/

TSS-IR Deployand Breakllr_clw_ Co_'_m

-7

15

10'

O-

003100:00 003/01:00 003/02:00 003/03:00 003/D4:00 003/05:00 003/06:00MissionEIapeedTime (Day/Hour:Minute)

-8

-9

-i0

-If

-12

-13

ge_& to.o Ss

lo.o_mtoke pR moHd

4-

I°-4

-8

MET Startat003/00:00:00.155 _.qMt- 3It

_ Nceid [l_r_l A_

10-s TSS-1R Deploy and BreakI i I I

Time (Imp)lO -s

8

4-

--4-

-40

$ 10-s t

4-

-4-

-8 i

o 1

-i!

I I I I I

' IiTime (hrs)

I I I I

2 3 4 5Time (hrs)



MISSION


SOURCE OR ACTIVITY

The ergometer is a bicycle-type of exerciseequipment in that pedaling is the primary means ofgetting exercise. This equipment has been configuredwith various forms of isolation systems on differentshuttle missions.

(1) Hard-mounted - No isolation is employed, it isbolted directly to the middeck or flight deck.

(2) Inertial Vibration Isolation System (IVIS) - Thisisolation system is primarily aimed at combatting theside-to-side motion of the person who is exercising.Counter-weights are driven by the pedal shaft to be 180 °out of phase with the side-to-side motion.

(3) Passive Cycle Isolation System (PCIS) - Thissystem attempts to "free-float" the exercise equipmentvia four braided cable, wire-rope isolators.

(4) Ergometer Vibration Isolation System (EVIS) -This is a three-axis vibration isolation system. Theergometer Z-axis isolation is an active system ofcounterweights which react to the motion of the crewmember. The ergometer X- and Y-axis isolation isaccomplished by a two-axis slide on the floor themounting assembly.

(5) Bungee isolation - In this configuration, arecumbent bicycle is suspended by a system of elasticbungee cords. These cords are secured to various pointson the surrounding shuttle structure. The suspensionsupport is primarily in the XY plane of the ergometer.

ACCELEROMETER

[_SAMS F] OARE




_. Spacelab Module .._

F-1 SPACEHAB Module tt/

[_ Middeck f t/

Keel Bri dge _ :'_

IIV,_


e. MEt _ it 0I_11:$1_Q,_ _ k,- 219

'Pm_ (m 1,1



about 1 to 4 Hz and last for the duration of the exercise. Depending on the particular crew member and the

vibration isolation used, typical acceleration levels in this frequency range can vary between 50 t.tgms to

about 1 mgms.

The exercise period may be seen in this plot beginning shortly after minute 10, and ending around

minute 40. This plot not only shows the primary exercise frequency (_2.5 Hz, related to the pedaling), but

also shows the sub-frequency (_1.25 Hz, related to shoulder rocking). This exercise was conducted with an

ergometer in the crew cabin, while the SAMS unit was located on the MPESS cartier.





URL: http ://www.lerc. nasa.gov/WWW/MMAP/PIMS/

t,o t..o

Frequency (Hz)

.....I oo

!

O

¢D t.o

e-F

i....a

0_

W-A

t.tt

RSS Magnitude [logl0(g2/Hz)]

I I I II

ooI

.-..I

Microgravity Environment Description Handbook I III. 1

CENTRIFUGE

MISSION

STS-60, February 1994, SPACEHAB-2

SOURCE OR ACTIVITY

A centrifuge was used in a Detailed

Supplementary Objective (DSO-202) conducted

during SPACEHAB-2. This was a joint

U.S./Russian metabolic investigation into the effects

of microgravity on body fluids.


ACCELEROMETER

[_SAMS _] OARE

TSH B, 50 Hz


MEASUREMENT LOCATION /_

O Spacelab Module _ _

k mbMgr _ttn it 0030_ _ ate, _lammtll _

_mm

104 i I _ I * * I I I

tO _

tO _

10"*

tO _

t0 -m

1o_t I

lO-_

m


During centrifuge operation, a strong, tightly controlled, 16.5 Hz disturbance with acceleration levels

around 14 lag_s was evident in all three structural axes.





URL: http://www.lerc, nasa.govAVWW/MMAP/PIMS/

Hid B. _(_O Hz

_. 0._2 Hz

104

iO -s

10 -6

lO_?

>_ 10 4

r_

a_ i0 -9

tO-lo

10-"

10 -t2

0

MET Start at 005/22:30:00.669. Hanmng k=54 _Actm_-_

Centrifuge _,w,._ cmtem.T- 29,m_9 mm

I I l I I I I I I

I l I I I I I I I

2 4 6 8 tO 12 14 16 18 20

Frequency (Hz)

15

MLrl"Start at 005/22:30:00.669. Harming k= 54

Cmaffage

SPAC_'L6_-2

C_dm

-5

-7

-8

-9

-10

-11

-t2

-13

-14

5 I0 15 20 25

Time (rain)

[ Microgravity Environment Description Handbook

REFRIGERATOR/FREEZER (SOR/F)

MISSION


SOURCE OR ACTIVITY

The Stifling Orbiter Refrigerator/Freezer

(SOR/F) was used on SPACEHAB-2. The

refrigerator has a compressor which contains a

piston driven by a linear motor.

I III. 2

ACCELEROMETER

Head B, 50 Hz



D Spacelab Module _,3_

I¢lii!ij Ae ':: oau o 2 l/ :/N

O Keel Bridge



The dominant source of vibrations in this cryocooler is its compressor which contains a piston driven by

a linear motor. Operation of the compressor during SPACEHAB-2 produced an intense oscillatory

disturbance around 60 Hz and its second harmonic (120 Hz). This pump was the dominant oscillatory

disturbance during its operation. It has been seen to produce accelerations in the 59.9 - 60.3 Hz region in

excess of 2000 _tgR_s.





URL: http ://www.lerc. nasa.gov/WWW/MMAP/PIMS/

He_l O. _.o HI

fa.- Z'SO,O_ialplm ipm"f_,_

_: _L_ 104 Ht

10 -+

iO s

jO -6

. i0 -_

lO-'

tO-9

|0 tl

i0-tz

b..2_0,0m Fw lind

dl'=0.2931m

120'

100"

80"

40-

20-

0 o

0

MET Start at 002/13:00:00.747, Harming k=109

Stifling Orbiter Rofrigerator/Free'zer

I I I

SpA_DI AIB 2

_a_ Coa_dml_

T- 2_Mli man

I

I I I

20 40 60

Frequmcy (Hz)

I

80I !

100 120

MET Start at 002/13:00:.00.747, Hazming k= 109

Stitling Orbiter Rettigetator/Ftee'zet

SP&C_4AJ-2

Smlcmad Cuonllnmm

-6

-7

-S

-9

-lO

-II

-12

-13

25

-14

5 10 15 20

Time (rain)

III. 3

Ku-BAND ANTENNA

MISSION


SOURCE OR ACTIVITY









ACCELEROMETER

[_SAMS ['7 tARE

Head B, 50 Hz



O Spacelab Module

["'] Cargo bay/Spacelab MPES.S g_/_ _

O

lff I I i [ i i I i i I _i

; ! !!

i_ i*,

:::::::::::::::::::::: ::::L::::::::::i :::::::::[::::::: :!:::: .... i .......... i ..........

....._............i.........:,:i::i":"iZ:Z:::i:: ":.... : '

lO !0





from this 17 Hz component are typically about I00 Bg_s. Its second and third harmonics at 34 and 51 Hz

are often quite prominent and 85 Hz has been seen.





URL : http ://www.lerc.nasa.gov/WWW/MMAP/P IMS/

Kw_ B. _0 Hs

dF_ _104 Hz

i0-_

MET Startat003/03:30:00.182,Harming k=36 se,cs_-2

MEDS: Ku-Band Antenna Dither (SPACEHAB Measurement) s_,,_,4 c**,_m

I 1 I I 1 I I I I

....... 7 .................... " .........

iiiiiiiiii iiii ;ii iiiiiiilLilliii

1.08 :::::::::::::::::::::::::::::::::::::::::.:_::;..........:;........................................ ...........

........... ! ......................... ! ....... _............ : ............ ! .............. ! .........................

_ 10-

1040

10 "n

' 3o '0 5 I0 15 20 25 35 40 45 50

Frequency (l:!z)

15

O"

0 I 2 3 4 5 6 7 8 9

_me(mm)

-10.5

Nlicrograxity En'_ironment Descri _tion Handbook

Microgravity Environment Description Handbook ] IV. 1

CREW SLEEP

MISSION

STS-43, August 1991

SOURCE OR ACTIVITY




ACCELEROMETER

[_SAMS ['--] OARE

Head A, 50 Hz



['_ Spacelab Module .......::::.:;:..:::::::_

i=]C_o_ayL___ss_/-/J 'IEl.s__::_o_o f//__:=_ N 2//A

b

:Yz: ! ?I• . -.- .............. . .... .

::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::::: -= - ::: : :: .... ::.

1o" ;::;::::;:: ::::::i ;;;:: ::iZ:: :::: : Z;::;:: :;;i : :;;::: ; :;:; ; :;: :::: : : :

_!i::!. !i

io _ .

ta 4n .


Sleep during a single shift mission such as STS-43 results in acceleration levels in the 1 to 4 Hz range

below about 20 Bg_s. Vehicle structural modes and the Ku-band antenna are the primary disturbance

sources during crew sleep.





URL: http ://www.lerc. nasagov/WWW/MMAP/PIMS/

45

4O

35

0"

001/ 2:00 0011 [3:00 001/ I.:O0

Mission Elapsed Ttme (Day/Hoer:Minme)

-10

-11

-12

-13

141aia A. m0 I_

i_= _tO o_lNm lag mmiI

4t= 0._2 Ha

10'

MET Sta_ at 001/12.'00:00.050,Hawmlg k=36 m_Stnntaa_ Caamiam

MEDS: Crew Sleep (Midkleck Measurement)

I I I I I I I I

.... . ...... ii . ii . .i ii . .

10 7 ........................................... : ........ : : ,--::.--::---::--:-: .... 3:. .: --::.- : .... :: -:: !......... . ............... , ......... , . .

. . : ..... . .... ; .. ; ..........

lO s :i i .

........ ....... .... !!iii!! :!!iii!iiii!!iii!i i!! :: ::

! i

10 L:

0 5 I0 15 20 _ 30 35 40 45 50Frequency (Hz)

I0 _

Microgravity Environment Description Handbook I IV. 2


MISSION

STS-66, November 1994, ATLAS-3

SOURCE OR ACTIVITY

The ergometer is a bicycle-t_9e of exercise equipmentin that pedaling is the primal" means of getting exercise.This equipment has been configured with various formsof isolation systems on different shuttle missions.

(1) Hard-mounted - No isolation is employed, it isbolted directly to the vehicle.

(2) Inertial Vibration Isolation System (IVIS) - Thisisolation system is primarily aimed at combatting theside-to-side motion of the person who is exercising.Counter-weights are driven by the pedal shaft to be 180 °out of phase with the side-to-side motion.

(3) Passive Cycle Isolation System (PCIS) - This

system attempts to "flee-float" the exercise equipmentvia four braided-cable wire-rope isolators.

(4) Ergometer Vibration Isolation System (EVIS) -This is a three-axis vibration isolation system. Theergometer Z-axis isolation is an active system ofcounterweights which react to the motion of the crewmember. The ergometer X- and Y-axis isolation isaccomplished by a two-axis slide on the floor of themounting assembly.

(5) Bungee isolation - In this configuration, arecumbent bicycle is suspended by a system of elasticbungee cords. These cords axe secured to various pointson the surrounding shuttle structure. The suspensionsupport is primarily in the XY plane of the ergometer.


ACCELEROMETER

[-_'SAMS [-10ARE

Head A, 10 Hz



D Spacelab Module .......=:::i..:ii.i#:¢.::i::i::_

Cargo bay / Sp...._::_ESS_] ....-.'-.-.-':i:i:':i:i:':i:i::::""

w_

"L'_ C_)



about 1 to 4 Hz and last for the duration of the exercise. Depending on the particular crew member and the

vibration isolation used, typical acceleration levels in this frequency range can vary between 50 l-tg_s to

about 1 mg_,_s.





URL: http://www.lerc, nasa.gov/WWW/MMAP/P IMS/


INTERLIMB RESISTANCE DEVICE

(crew exercise)

MISSION


SOURCE OR ACTIVITY

This device consists of bungee tethers used to

suspend a low-mass harness in the middeck. The

ILRD provides variable resistance exercise by

working one limb against another.


ACCELEROMETER

Head A, 10 Hz



r-] Spacelab Module ...........:::_i_

1"7 Car-o ba,, S"ac__:_:S_S _ff//_

['"] Keel Bridge

7:".............li1_ J]

t

i

h9

I 2 t 4

1_ _j


This non-aerobic form of exercise has much less of an impact on the environment than does the

ergometer, or treadmill equipment. Typical levels for this activity are less than 30 btgp_,_s.





URL: http :Hwww.lerc. nasagov/WWW/MMAP/PIMS/

II

e_

if,

(zH/z_)s_v-x

(_)s!xvA

i.....

...... r....... i........ r .......

(ZHA_) s!xv-z

-=if

(_) s_V-Z

I1

e,

t,,I

i

v

Cq

t ¸', ,"


PAO EVENT

MISSION


SOURCE OR ACTIVITY

Scheduled demonstration or question and answer

events with some or all of the crew gathered in a

single area.


ACCELEROMETER

Head A, 10 Hz



Spacelab Module ............._

F-1Cargobay/

O Keel Bridge

I I * i I i i , * /

i!)!!! !!!!!!!!!!!!!! !!! !!!!!!!

]

to"

................................... ? ...................... !

1o '_ , , ,


It _s common that when PAO events take place, the microgravity environment becomes quieter. The

crew is typically not moving about or impacting the spacecraft structure, they are usually free-floating in

front of a camera. Also, experiment operations involving crew interaction are not being conducted for the

duration of the PAO event. This tends to reduce the overall acceleration background level below 10 I-lz to

less than 50 _g_,_s Vehicle structural modes and the Ku-band antenna are the primary disturbance sources

during PAO events


NASA Lewis Research Center, Cleveland, Ohio

e-mail: pims@lerc nasa gov

Telephone: 216-433-8394 Facsimile: 216-433-8660

URL: http://www lerc nasagov/WWW/MMAP/PIMS/

4

lO I I

'1

0.5

_ O-,U<

.MET Start at 004/2_0:09:59.999

MEDS: PAO Event {Middeck Measurement)

1 I I I I I

-0.5

-1 i I I i i

0.5 1 1.5 2 2.5

Time (ram)

I ! I

3.5 4 4.5 5

10 -_

10 -_;

., .... , ........ , . . . , . . ., .............

1 I i i 1 1 l I I I

1 2 3 4 5 6 7 8 9 10

Frequency (Hz)


TR EAD MI L L (crew exercise)

MISSION

STS-43, August 1991

SOURCE OR ACTIVITY

This piece of exercise equipment is hard-

mounted to the orbiter middeck. Exercise comes

mainly from walking/jogging/running on this

passive rotary treadmill. The primary disturbance

(2-2.5 Hz) is created by the footfall frequency. This

frequency is generally constant throughout the

exercise period, with the exception of the warm-up

and cool-down at the beginning and end of the

exercise.


_ !:!! i !!!!! i!! !! ::

Z; 7Z_;::; ; ZZ; : Z:;;:; " "'_" ";:ZZ::: Z ;]2, _ ::''" " ; ....

o : : I

to _ .

5 10 _ lO 2_ _o _ 4_ _ 50

ACCELEROMETER

N's s

Head A, 50 Hz



Spacelab Module .......O . ..:.::::i:iiii_i_:_i:i::::""

f"l Cargo baY£ii_ii_::_SS

Vliiii aae k f I/

_mm


The 2 - 2.5 Hz band was excited by 1,500 gg_s. This measurement was made by a sensor head on a

locker door approximately 6 feet away from the treadmill.


NASA Lewis Research Center, Cleveland, Ohio




.MET Start at 001/07:14:59,996, Hamung k=18MEDS: Trcadmall Exercise (Middeck Measuremem_

I i |

10 9

0

::.. . . .............. !!! .............. : .......

.......... ! .....

1 | I I I I I I

10 15 20 25 30 35 40 45 50Frequency (Hz)

,MET Start at 001/07:05:59.996. Hamung k= 292

MEDS: Treadmill Exexcise (Middeck M_ement)

g't_ 43

_'lem d C_,_uidm

-4

-6

-8

-9

-10

-11

-12

k_

0"

0 5 10 15 20 25 30 35

Time (nun)


Ku-BAND ANTENNA

MISSION

STS-43, August 1991

SOURCE OR ACTIVITY









ACCELEROMETER

Head A, 50 Hz



Spacelab Module ..............__

_ Cargo bay / Spac_!_i_S_S" _ _

['-]"Keel Bridge





from this 17 Hz component are typically about 100 [tg_s. Its second and third harmonics at 34 and 51 Hz

are often quite prominent, and the 85 Hz harmonic has also been seen.






_-,_ _." tit

10 _

10 ?

_10 _

:_ 10 °.,¢

10 lO

10 u

ME'T Start at 007/17:30:00.378. Harming k=20

Mt-I)S: Ku-Band Antenna _ther _.X,hddeck Measurement)

I I I I

_T541

Y I'b_ m_

I

I I I I I [ r I ]

5 10 t 5 20 25 _ 35 40 45 50

Frequency (Hz)

.MET Start at 007/17:30:00.378, Harming k= 40

MEDS: Ku-Band Antenna Dither (Middeck Measurement)

0

0 2 3 4 5 6 7 8 9 10Time (rmn)

Microgravity Em,'ironment Description ttandbook

Microgravity Environment Description Handbook I V. 1

ATlVlOSPHERIC DRAG -Circular orbit

MISSION


SOURCE OR ACTIVITY

Atmospheric drag accelerations are caused by

the Orbiter vehicle passing through the rarefied

atmosphere at the orbital altitudes. The amount of

drag is primarily determined by the Orbiter frontal

area, which is dependent on the attitude of the

Orbiter relative to its direction of flight. This area

is a minimum when the Orbiter is oriented nose or

tail forward and is a maximum when the Orbiter

belly or cargo bay is forward.

The atmospheric density is not constant around

the Earth, thus causing a variable amount of drag as

the Orbiter traverses its orbital trajectory. For an

orbital trajectory of nearly constant altitude, the

major variation in density is due to solar heating of

the atmosphere on the light side of the Earth and

radiative cooling on the dark side.


ACCELEROMETER

Frequency Range: 1 x 10 -5 - 0.1 Hz



1"-] Spacelab Module

_-] Cargo bay/Spacelab MPESS r__

1

_o ', t

l_ i i J h

i.

EFFECT ON MICROGRAVITY ENVIRONMENT ---

The effects of the atmospheric drag on the microgravity environment are seen in the quasi-steady

frequency regime as a constant acceleration vector with a variable component. The variable component has

a frequency based on the orbital period of the vehicle (approximately 90 minutes).

The figure shows the acceleration levels measured while the Orbiter was oriented with its -Zb-axis in the

direction of travel (i.e., with the cargo bay forward). The major component of the drag acceleration is in the

Zb-axis. The variable acceleration due to the atmospheric density variations is seen in the Zb-axis with aperiod of about 90 minutes.






OARE. Trinmaed Mean Filtered

OARE LocationMET Start at 007/06:00:06.840

Frame of Reference: Inertial

USMP-2

Body Coordinates

2

"-" 1

,=.2

0

<I

X-1

-2

I I J

Circular OrbitI I I I I

! I I I I I I I I

II

0 1 2 3 4 5 6 7 8 9

2/ I I I 1 I I I I I

/0

-2 1 , , , , , , , , ,

0 l 2 3 4 5 6 7 8 9

H

2

,--, 0

<I

-2

I I I I I I I I I

I I I I I I I

"I

II

0 1 2 3 4 5 6 7 8 9

Time (hrs)

_:_-i::_:vJ [ Microgravity Environment Description Handbook I

ATMOSPHERIC DRAG-Solar inertial attitude

MISSION


SOURCE OR ACTIVITY










A solar inertial attitude orients the Orbiter

ACCELEROMETER


_] SAMS [_'OARE

Frequency Range: 1 x 10-5 - 0.1 Hz



D Spacelab Module W_

["7 Cargo bay / Spacelab MPESS _ r

D[-7 Middeck ..............................................._::::::::::::::_,_ A

B_IIII_I $:00:16. _0

Sd_hmt¼1 Am_,

2'' ' ' ' i , , , ,

attitude relative to the sun, as opposed to an Earth- _' _oriented attitude. The solar inertial attitude then I_results in a variable frontal area during its orbital __,

period, thus causing a variable atmospheric drag _2acceleration. 0 , , , , , , , , ,

The atmospheric density is not constant around ..........[ ' n_l ' ' ', ' ' ' I

the Earth, thus causing a variable amount of drag as _ _ _ ]_ , _,.. A ,,,._ l,J[ ,_,A d_a0

the Orbiter traverses its orbital trajectory. For an i__

orbital trajectory of nearly constant altitude, the _,I ......... II

major variation in density is due to solar heating of ..........

the atmosphere on the light side of the Earth and ..........[ ' ' ' ' ' ' ' ' ' I

radiative cooling on the dark side. _1.1 Ill A JtJ[I _t h,f

_°lr_ll_ ll¢__i_l'_/_

' 'I1 -21 ' I . '11

o t 1 _ 4 _ _ 7 $ 0

EFFECT ON MICROGRAVITY ENVIRONMENT --




The figure shows the acceleration levels measured while the Orbiter was oriented in a solar inertial

attitude. The major variation in the acceleration levels are due to the large variation in frontal area as the

Orbiter tumbles relative to the Earth and the atmosphere.






OARE, Trimmed Menu Filt_'ed

OARE LocationMET Start at 010/18:00:16.920

Frame of Reference: InertialUSML-2

Body Cogrd2natea

" 1_0I

o

I

X-1

Solar Inertial AttitudeI I I I I I I

-2 I I I I I I I I I

0 1 2 3 4 5 6 7 8 9

I I

2

4%.0

-2

I I I I I I I I I

I I I ! I I I I I

0 1 2 3 4 5 6 7 8 9

L.,

il

I I I 1 I I I I I

-2 , i i i i i i i i

0 I 2 3 4 5 6 7 8 9

Time (hrs)


ATMOSPHERIC DRAG-

Elliptical orbit

MISSION


SOURCE OR ACTIVITY










The atmospheric density gradually decreases

with altitude above the Earth. When the Orbiter has

an orbit which is not at a constant altitude, the

density variation causes a variable amount of drag

acceleration as the Orbiter traverses its orbital

trajectory.

The atmospheric density is not constant around

the Earth, thus causing a variable amount of drag as

the Orbiter traverses its orbital trajectory. For an

orbital trajectory of nearly constant altitude, the

major variation in density is due to solar heating of

the atmosphere on the light side of the Earth and

radiative cooling on the dark side.

ACCELEROMETER

r-] SAMS [_OARE




-'] Spacelab Module

'-]Cargo bay / Spacelab MPESS

[_ SPACEHAB Module

Middeck ....................._;_ii_iJ:_:_::::_:_;*

0 1 l ) 1 _ 6 7 | 9

Largeri "I, ,,,o,3" v v v v ¥ k [i o,,

° ' ' ' ' ' ' ' ' ' reverse

:1o 1 1 ] ,1 .i.imbaSflT_l) _ 7 | 9

EFFECT ON MICROGRAVITY ENVIRONMENT ---




The figure shows the acceleration levels measured while the Orbiter was in an elliptical orbit of 138

nautical miles (perigee) and 105 nautical miles (apogee). The attitude was such that the Orbiter +Yb-axis

was oriented in the direction of flight so the drag variation is seen primary in the Yb-axis data. The peak-to-

peak acceleration variation (about 3 _tg) is approximately ten times the variation experienced due to

atmospheric density variations in a circular orbit.)






OARE, Trtmmed Mean Filtered

OARE Location

MET Start at 013/08:00:20.160

2

I

o¸

-2

-3

-ZLV/+YVV Elliptical OrbitI I I I I

Frame of Reference: Iaei'tial

USMP-2

Body Coordinat_

I I

I I l I I I I I I

--0H

0 1 2 3 4 5 6 7 8 9

2

Io 1

"4 0

--2-

-3

I I I I I I I I I

I I I I I I I I I

II

0 1 2 3 4 5 6 7 8 9

2

etO

I 1

2 0

N

--2-

-3

I I I I I I I I I

0I I I I I I I I

1 2 3 4 5 6 7 8

Time (hrs)

9

t-q

II

ra_ 't Microgravity Environment Description Handbook I V. 4

FLASH EVAPORATION SYSTEM

MISSION


SOURCE OR ACTIVITY

On-orbit heat rejection is provided by radiator

panels; however, during orbital operations the

combination of heat load and spacecraft attitude

may exceed the capacity of the radiator panels.

Further heat rejection is provided on-orbit by the

flash evaporator system (FES). FES operations

provide heat rejection by vaporizing excess water as

it contacts a core filled with hot Freon® The

resulting vapor is vented out two opposing nozzles

on the aft portion of the Orbiter.


ACCELEROMETER

["] SAMS [_OARE


fs = 10 samples per seconds

MEASUREMENT LOCATION //_/

O Spacelab Module _t___

0 Cargo bay/Spacelab MPESS I_ _

O Middeck .....................................................

J i h i

__1 ' ' _. , JJ0 1 Z :_ 41 S 6 1

12_2 i i i n i i h!-, i-_1 ii

o 1 z I 4 _ 6 ,

o t Z ) _ _ 6 7

Ttgm (lit)

EFFECT ON MICROGRAVITY ENVIRONMENT --

The FES was designed to provide a balanced vapor expulsion in the +Yb-and -Yb-axes. The resultant

effect is typically less than 0.5 Bg in any axis.



e-mail: [email protected]


URL: http://www. Ierc. nasa. govAVWW/MMAP/P IMS/

OARE, Trm_med Mean

OARE Location

I I

MET Start at 001/04:00:18.000

FES OperationsI

Prame of RefeteII_: Orbitea"

LMS

Body Coordinates

t

0 1 2 3 4 5 6 7

t_

"4 0

I

>_-1

-2

I I I I I I I

I 1 I I I I I

1 2 3 4 5 6 7

8

0

I

N-1

-2

I I I I I I

1 I I I I I I

CJ

0 1 2 3 4 5 6 7

Time (hrs)

Microgravity Environment Description Handbook I V. 5a

MISSION LOW-FREQUENCY

ENVIRONMENT

(Two crew shift - Spacelab Module)

MISSION


SOURCE OR ACTIVITY

The low-frequency or quasi-steady microgravity

environment is a complex combination of many

factors such as atmospheric drag, vehicle attitude,

centripetal accelerations, gravity gradient

acceleration, crew activity, vehicle venting, location

within the vehicle, etc. Many of these factors will

change during a mission and, therefore, so will the

microgravity environment.

As explained elsewhere in this handbook, the

atmospheric drag varies during each orbit.

Periodically throughout a mission, gases and waste

liquids are vented from the Orbiter which produce

quasi-steady accelerations due to reaction forces.

The requirements for some missions result in a crew

split into two working shifts to maintain around-the-

clock operations.

The STS-65 mission was devoted to one

primary payload, the IML-2. The Orbiter utilized

several attitudes to maintain microgravity

conditions as required by the IML-2 experiments.


ACCELEROMETER

Ds = glo

Frequency Range: 1 x 10-5- 0.1 Hz



["'] Spacelab Module __,.

r-] cargo bay / Spacelab MPESS __t

r-I MJddeck ...................................._ _(/I ]t

o 5o lOO IJo

t.II

2_ )¢+¢ 3J0


The low-frequency microgravity environment for the mission is shown in the figure. The major events

affecting this environment for the mission are identified in the figure on the reverse side+ For a detailed look

at these activities, consult the pertinent pages in this handbook. Due to the two crew shifts and the nearly

constant attitude, the levels are fairly consistent throughout the mission. This is in contrast with single-shiftcrew missions.





URL: http ://wwwlercnasa'g°v/WWW/MMAP/PIMS/

j_i¢

m

I I I

(_-o._.rtu) s!xv-x (_'-o._.tm) s.rxv-z

0

Microgravity Environment Description Handbook I V. 5b

MISSION LOW-FREQUENCYENVIRONMENT

(Two crew shift - Spacelab Module)

MISSION


SOURCE OR ACTIVITY















split into two working shifts to maintain around-the-

clock operations.

The STS-73 mission was devoted to one

primary payload, the USML-2. The Orbiter utilized

several attitudes to maintain microgravity

conditions as required by the USML-2 experiments.


ACCELEROMETER

D SAMS ZOARE

Frequency Range: 1 x 10 -5- 0.1 Hz


MEASUREMENT LOCATION_D Spacelab Module

["-] Cargo bay / Spacelab MPESS ___l _

S AC . o u,o r

k "_"_"::::::....


The low-frequency microgravity environment for the mission is shown in the figure. The maj or events

affecting this environment for the mission are identified in the figure on the reverse side. These events

include water dumps and attitude changes. For a detailed look at these activities, consult the pertinent pages

in this handbook.



e-mail: pims@lerc, nasa.gov.


URL: http://www.lerc, nasa.gov/WWW/MMAP/P IMS/

r-:tt-)

[-

|

]_ _]" I- = _I_I 8d 6gSiYO-- = tmaI_I

¢q

¢q C',I..,.,

tt_

V

Microgravity Environment Description Handbook V. 5c

MISSION LOW-FREQUENCY

ENVIRONMENT

(One crew shift - Spacelab MPESS)

MISSION


SOURCE OR ACTIVITY















which works in one shift.

The STS-62 mission was devoted to two

primary payloads: the USMP-2 and the OAST-2.

The USMP-2 payload operated with higher priorityfrom MET 000/10:00 until 009/16:45 and the

Orbiter utilized several attitudes to maintain

microgravity conditions. The OAST-2 payload

operated with the higher priority from MET

009/16:45 until 013/00:00 and the Orbiter operated

in many different attitudes and elliptical orbits.

This was a very dynamic acceleration environment

compared with the USMP-2 operations, as can be

seen in the figure.

ACCELEROMETER

r---] SAMS [-'_'OARE



MEASUREMENT LOCATION __1._

[--1 Spacelab Module _/_._ ,.

D ay,Spa.,a VDs A. o ulo

"Larger plot on reverse

0 50 100 1-I0 20O 2.50 _0 _0

4 I I I I I i

0 _0 100 L.50 200 ;LSO 300 _0

, . , .....O :5O too UO 200 2..50 _03 _50

_me Ihml _.


The low-frequency microgravity environment for the mission is shown in the figure. The maj or events


include PRCS thruster firings, attitude changes, crew active time, crew sleep time, and elliptical orbit. For a

detailed look at these activities, consult the pertinent pages in this handbook.






|

(_-oi_._) s!xv- _

k_-::: =_i_',_ '_,;j I Microgravity Environment Description Handbook I V. 5d


(Two crew shift - Spacelab MPESS)

MISSION


SOURCE OR ACTIVITY





acceleration, crew activity, vehicle venting,

location within the vehicle, etc. Many of these

factors will change during a mission and, therefore,

so will the microgravity environment.







split into two (and sometimes three) working shifts to

maintain around-the-clock operations.

The STS-75 mission was devoted to two primary

payloads: the reflight of the Tether Satellite System

(TSS-1R) and the USMP-3. The TSS-1R payload

operated with higher priority from MET 000/00:00

until 005/00:15 while the Orbiter operated in

several different attitudes and deployed the tether

satellite system. The USMP-3 payload operated with

ACCELEROMETER

Frequency Range: 1 x 104 - 0.1 Hz


MEASUREMENT LOCATION ,_.j

F] Spacelab Module __

r] SPACEHAB Module ............J::::J/.-::i./_

Larger plot on reverse_

t,i .... J.......... ,

. . . '-ll-l!rllrlr'" 11111oo 1_o _o 150 _00 I_0

! !Idllllll.Jll.i,lt, ,lli.I,II!tI,Ll,1,11IILII[,J:.Ii lIY i 1]11.rFl"q-.1I-' l-Tr!tii i-LlULillll[l liL_II'lL,,iJld' [,:V ", ..... '

o _ too 150 2oo iao i_ i_

the higher priority from MET 005/00:15 until 013/14:00, and the Orbiter utilized several attitudes to maintain

microgravity conditions as required by the USMP-3 experiments. The TSS-1R payload operation was a very

dynamic acceleration environment compared with the USMP-3 operations, as can be seen in the figure.




include water dumps, attitude changes, tether satellite deployment and PRCS thrusters. For a detailed look

at these activities, consult the pertinent pages in this handbook.





URL http://www. !erc. nasa. govAVWW/MMAP/P IM S/

I I I I

E

_ _-T-,.-g.

----.la,a

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.I i

i

I I I

(_'-olo!w)s!_-A

I I

C*3

t"e3

ttbC'4

0oq,-_

g

Microgravity Environment Description Handbook V. 5e


ACCELEROMETER

F'] SAMS _'OARE

MISSION


SOURCE OR ACTIVITY















split into two (and sometimes three) working shifts

to maintain around-the-clock operations.

The STS-78 mission was devoted to one primary

payload, the LMS. The Orbiter utilized several

attitudes to maintain microgravity conditions as

required by the LMS experiments.


Frequency Range: 1 x 104 - 0.1 Hz



_'] Spacelab Module _ .,,

D Cargo bay / Spacelab MPESS/__ _

Middeck ................_::_::_ ____i_i::!::--::_:-_i_:_:_iii_:_............................

__ t_n_tge

1

[:5Ulllllllllllllllt 21 I I_, ,r i

0 _0 tOO I_0 _ _O loO 15o ,too

i i i ,

o _0 l_ IJO lm _0 I00 I:I0 40O

o _0 lm t_O _._ _ _o0 I_0 am

Tiem (t_m)



affecting this environment for the mission are identified in the figure on the reverse side These events

include crew activities and attitude changes. For a detailed look at these activities, consult the pertinent

pages in this handbook.





URL http://www.lerc, nasa.gov/WWW/MMAP/PIMS/

Attitudes: A: -ZLV/-XVV

B: -XLV/+ZVV

OARE, Trummecl Mean Ptlt_red

OARE Lo e._tioa

MET Start at 000100:13:17.040Frame of Refetmce: Orbite¢"

LMS

Body Coordinate*

-3

0

Attitudes:

3 i

5O

A

I

!

50

LMS Quasi-Steady Acceleration EnvironmentI 1

100 150

B A

1iI

10{ 150

200 250 300 350

B A

I I

crew crewactive sleep

200 250I

300 350

il

400

fl

400

5OI

100 150 200 250

Time (hrs)300 350

r_

II

4OO

Microgravity Environment Description Handbook I V. 6

ORBITER ATTITUDE

MISSION


ACCELEROMETER

["] SAMS [_OARE



SOURCE OR ACTIVITY



factors such as atmospheric drag, centripetal

accelerations, gravity gradient accelerations, crew

activity, venting, etc. The attitude of the Orbiter has

an effect on the acceleration level of many of these

components, such as atmospheric drag, centripetal

acceleration, and gravity gradient acceleration. To a

lesser degree, the attitude also affects the amount of

water dumping required for thermal control.

------ _4 ......... -====-zt,v/. _ v,,-,z-vv_ "ertmm.

° " t; I .....

° " l'1 .....ii] i i_i I


MEASUREMENT LOCATIOI_ __. •D Spacelab Module

'-]Cargo bay / Spacelab MPESS ....

[-7 SPACEHAB Module

_:_::_::iiii#::::i::iiiiiiiii}ii_iiii_i}iiiii::iiiii::i_::i_.......................f_._s4"-_::I f:_

[._ii _ Bridge


........ I t

{ i-2t r I II

........ I 'r

-'f :; ,; ,_ 'o!A_,L lJ.... I l ---

The low-frequency microgravity environment during two attitude transitions are shown in these figures.

The different quasi-steady levels are apparent between the three attitudes illustrated there. The ten minute

period in between attitudes (marked-offby the dotted lines) are the transition times. Some experiments are

sensitive to the effective direction of the quasi-steady acceleration vector. As can be seen from the Xb, Yb

and Zu components for the different attitudes, the direction of the quasi-steady acceleration vector is

dependent on the Orbiter's attitude.





URL http ://www.lerc. nasa gov/WWW/MMAP/PIMS/

i!J

¢11

¥

|

J_

ii4_Tg$O zI

++

+.

>>

+-

(_-oJoml)_!zV-X

lid 6991 O- = IIIopII I

i i I i

(_-o _mz )sncv-l_

I bLg"O- = eI I

(_-o._) +!x'_- Z

!

Microgravity Environment Description Handbook Vo 7

THRUSTERS

(Quasi-steady effects)

MISSION


SOURCE OR ACTIVITY

The forward and aft Reaction Control System

(RCS) thrusters provide the thrust for attitude

(rotational) maneuvers (pitch, yaw and roll) and for

small velocity changes (translation maneuvers).

The forward RCS has 14 primary and two vernier

engines. The aft RCS has 12 primary and two

vernier engines in each pod. The primary and

vernier RCS engines provide 870 and 24 pounds of

vacuum thrust each, respectively. They may each

be fired in increments of 80 milli-seconds. The

vernier RCS thrusters are normally utilized for

attitude control during the microgravity science

missions. In the case of vernier thruster failure, the

primary thrusters are used for attitude control.


ACCELEROMETER

I-'] SAMS _OARE

Frequency Range: 1 x 10-5 - 0.1 I--Iz



['7 Spacelab Module

['-] Cargo bay / Spacelab MPESS_

[--'] SPACEHAB Module J 7

I_]i!iii_i::]_:g_:I:I:::::::::'_.....................S:!:S:i......._:::i:!i:!ii_i_ii!i_S_S!!_!!i!::!?i::S::i::iii:.i!:i!ii!i:.i:_::_::_i_':"...................

v_ rankly _tnnm

io i z s * _ 6 _ i

+tloo

] + L . .:t4¢_

14:'21

¢ 1 !

+

+ i +, l + Tml_ mmJ + 7 I *


The low-frequency microgravity environment during two thruster firings are shown in the figure. The

event around 3 minutes, 30 seconds into the plot shows a 20 second duration simultaneous firing of two

vernier thrusters (L5D and R5D). The event around 7 minutes, 40 seconds into the plot was a single vernier

thruster (L5D), fired for about 20 seconds.

The effects on the microgravity environment do not occur solely in the quasi-steady frequency regime.

Since the event is impulsive by nature, there are disturbances experienced over a broad frequency range.

For further higher frequency information, see the PRCS and VRCS pages of this handbook.





URL: http ://www.lerc. nasagov/WWW/MMAP/PIMS/

OARK RAwOARE Loe_ion

15o

500

<l -50

-100,

MET Start at 014/19:20:00.037

Vernier Thruster Firings1 I I I I I I I I

Prame ot Reference: lnerlial

USML-2

Body Coordinates

--150 I I I I I I I I I

0 1 2 3 4 5 6 7 8 9

150

100

Io 50

N 0-

_ -50

-100

I I I I I I I I I

-150 i i | ! i ! ! i

0 1 2 3 4 5 6 7 8 9

i

150

100-

Io 50

0

_ -50N

-100-

-150

1 I I I I I I I I

I I I

0 I 2 3J I [ I | I

4 5 6 7 8 9Time (min)

:1

Microgravity Environment Description Handbook I Vo 8a

WATER DUMPS

(SUPPL Y WATER DUMPS)

MISSION



SOURCE OR ACTIVITY

The Orbiter food, water, and waste management

subsystem provides storage and dumping

capabilities for potable and waste water. Supply

and waste water dumps are performed using nozzles

on the portside of the Orbiter.

Supply water dumps typically cause a net

acceleration in the Yb-axis of the vehicle which

triggers thruster firings to maintain attitude. As

shown in the plots from the LMS mission, these

dumps can cause a net acceleration in the Zb-axis.

-,I ' I Ii

ACCELEROMETER

[--] SAMS _C, ARE

Frequency Range: 1 x 10-5 - 0.1 Hz



1"] Spacelab Module _

B '.Larger plots on reverse

1

_,1 II _21 Itzoo


The low-frequency microgravity environment for two missions are shown in these figures. The effect on

the Yb-axis is approximately 1.5 I,tg A similar effect of approximately 1.5 _tg is possible on the Zb-axis as

well.





URL: http ://www.lerc.nasa.govAVWW/MMAP/PIMS/

!

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JJJ_

o

I

(_--o_)[m)s_V-X

_1 L_lro - mr_i

Microgravity Environment Description Handbook Vo 8b

WATER DUMPS

(WASTE WATER DUMPS)

MISSION


SOURCE OR ACTIVITY





on the portside of the Orbiter.

Waste water dumps typically cause a net

acceleration in the Yb-axis of the vehicle which

triggers thruster firings to maintain attitude. As

shown in the plots from the LMS mission, these

dumps can cause a net acceleration in the Zb-axis.


ACCELEROMETER

['] SAMS _OARE




1"'] Spacelab Module

D Cargo bay / Spacelab MPESS t_i_

['] Middeck ........__

Wl_ Wster _

4o _o loo tso 20o

o _o _oo uo 2OO

!o

o _ too Do 1_"_ml (mini


The low-frequency microgravity environment for the LMS mission is shown in the figure. The effect on

the Yb-axis iS approximately 1.0 _tg. A similar effect of approximately 1.0/,tg is possible on the Zb-axis as

well.



e-mail: [email protected] gov.


URL http://www.lerc, nasagov/WWW/MMAP/PIMS/

OARE, Trtmmed Metro FilteredOARE Location

MET Start at 008/00:00: t 1.160

"-" 2I

o

4 ov

i1_-2-

I

I

Frame of Reference: Orbtter

LMS

Body Coordinates

Waste Water Dump! I I

I

I

I I

, I , I,

50 [ 100 t50 20(

I II I I I

I I

II

I II

o

_ o-r¢¢1

I_-2

o

_ o-¢Jl

iN-2

--4

I I

I

I I

I I! I I I

50 I lO0 [150 200

I II I I I

I

I

I

I

I

I

I

I

Ii

I I I I

II

0 50 100 150 200

Time (min)

II

Microgravity Environment Description Handbook I V. 8c

WATER DUMPS

(SIMO DUMPS)

MISSION



SOURCE OR ACTIVITY





on the port side of the Orbiter. The two level effects

observed in the figures results from the waste water

dump being cycled on and off while the supply

water dump stays on continuously. The term

"SIMO" refers to a simultaneous supply and waste

water dump.

This typically causes a net acceleration in the

Yb-axis of the vehicle which triggers thruster firings

to maintain attitude. As shown in the plots from the

LMS mission, these dumps can cause a net

acceleration in the Zb-axis.


ACCELEROMETER

["] SAMS [_OARE




[-'] Spacelab Module

[-'] Cargo bay / Spacelab MPESS_ _

['-] SPACEHAB Module _///_

l'-] ddeck .............................. /t

, s_o _ +w_ .,_mmm+/w,,,.I

.1 i ' UlJ

21 H

In, dom._ (w_ _,l _ w.,,..+

!_,I I|

o so i_o z_ 20O

+iL.+. •

!° !°

• m io_ l_o J,m • s# leo i_orll+ rm,_ 1'Ira rl,lll)


The low-frequency microgravity environment for two missions are shown in these figures. The effect on

the Yb-axis is approximately 3 _g. A similar effect of approximately 3 I,tg is possible on the Zb-axis as well.





URL: http ://www.lerc. nasa gov/WWW/MMAP/PIMS/

M

|

c_

gC,

g

t|J_

|

CD¢'4

C,

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ioq

.q-

_r

2fl 8L! L'O- - tmeT_[ _ 00/,_'0- - twin

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Microgravity Environment Description Handbook VI. 2

MIR / GYRODYNE ACTIVITY

MISSION

Mir Space Station, September 1995

SOURCE OR ACTIVITY

Within each module of the Mir Station, there is

at least one bank of 6 gyrodynes, used to help

maintain station attitude. These operate at a

nominal rotational rate of 10,000 rpm (-166.6 Hz).

This is normally a very well controlled signal (i.e.

falling within a fight frequency band).

Occasionally, one or more of these gyrodyne banks

needs to be spun-down (i.e. turned-off), and then

spun-up again later. By analysis of SAMS data,

both the spin-up and spin-down operations take onthe order of 3 hours.


ACCELEROMETER

Head A, 100 Hz



[-7 Spacelab Module

D7q['-] Middeck

Keel BridgeMir, Kvant

Cargo bay / Spacelab MPESS

SPACEHAB Module


Due to the 100 Hz cutoff of the SAMS sensor head, SAMS data cannot be used to accurately determine the g_s

level of the accelerations above 100 Hz, including the 166.6 Hz gyrodyne disturbance. Additionally, the g_s level forthe disturbance would depend on the proximity of the sensor to the disturbance source. SAMS data from the Kvant

module have suggested that the disturbance is 500 _tg_s or more.

A spin-down operation may be seen in the figure, starting around DMT 249/17:05, where the diagonal tracebegins its downward slope from 166 Hz, towards 0 Hz around DMT 249/20:15. Close examination of this plot showsmultiple traces, each following different time vs. frequency paths, including one starting around DMT 249/18:40.However, all of the traces seem to converge at 0 Hz around DMT 249/20: 15. This suggests that the spin-downprocedure for the 6 gyrodynes in each bank is a well-controUed process, with a well-controlled end-time.






I

°.

Microgravity Environment Description Handbook VI. 6

MIR / SHUTTLE DOCKING

MISSION

Mir Space Station, November 1995

SOURCE OR ACTIVITY

The docking of the Orbiter to the h/fir Space

Station is achieved through use of the docking ring

adapter, attached to the extremity of the Kristall

module. The docking operation is conducted in

multiple steps, including a docking ring capture

(soft-mate), followed by a ring retraction, and then a

series of 12 latches are locked (hard-mate). This

plot was produced from data collected during the

STS-74 docking of Atlantis.

ACCELEROMETER

Ns s

Head A, 100 Hz



Spacelab Module

D Cargo bay / Spacelab MPESS

_'] SPACEHAB Module , i

D Middeck

Keel BridgeMir, Kristall


n Jam0 Jim Jml_ JIM ilm_ nwlom


The broad-baud impulse disturbauce around DMT 319/08:42 is believed to be the initial contact of Orbiter to Mir.

The impulse around DMT 319/08:47 is believed to be the hard-mate capture. Immediately following this dismrbauce,notice the addition of a 17 Hz signal to the environment. This is caused by the dither of the Ku-baud communicationantenna on the orbiter. Also notice a periodic 22-23 Hz signal (circled in black). This is due to the Enhanced OrbiterRefrigerator/Freezer (EORF) on the Shuttle. The EORF is similar in nature to the LSLE R/F, described in thishandbook.

The spectrogram on the right (produced from head B data) shows a clearer picture of the lower frequency region,including the vehicle structural modes. Notice how some structural modes change (2.0 Hz before docking, 2.5 Hzafter docking), and how other modes appear (4.5 Hz after docking).

These data show that the acceleration environment of the two vehicle complex results from the accelerationenvironment of both vehicles. In other words, microgravity disturbances are transmitted from one vehicle to theother.



e-mail [email protected]+


URL: http ://www.lerc.nasa.gov/WWW/MMAP/PIMS/

2O

0

319/08:00

9

0

319108:00

Atlantis-Mir (STS-74): Docking Even!

319/09:00

De_eed Moscow Time (1995/Day/Hour:Minute)

DMT Start at 319/08:07:58.004, Harming k= 328

MEDS: Mir-Shuttle (STS-74) Docking

319109:00

Time (nun)

319/10:00

319/10:00

-5

-6

-7

-8

-9

-lO

-11

-12

-6

-7

-8

-9

-10

-11

-12

-13


Appendix A: Accessing Acceleration Data via the Internet

SAMS and OARE data are available over the internet from the NASA LeRC file server

"beech.lerc.nasa.gov". Previously, SAMS data were made available on CD-ROM, but distribution of

data from current (and future) missions will be primarily through this internet file server.

SAMS data files are arranged in a standard tree-like structure. Data are first separated based

upon mission. Then, data are further subdivided based upon some portion of the mission, head, year (if

applicable), day, and finally type of data file (acceleration, temperature, or gain). Effective November 1,

1996, there has been a minor reorganization of the beech.lerc.nasa.gov file server. There are now two

locations for SAMS data: a directory called SAMS-SHUTrLE and a directory called SAMS-MIR.

Under the SAMS-SHUTTLE directory, the data are segregated by mission. Under the SAMS-MIR

directory, the data are segregated by year. The following figure illustrates this structure.

pub

II I I I I I

MMA-LMS OARE SAMS-SHUTI_E USERS UTILS SAMS-MIR

II I I I

spacehab-1 lms usmp-1 missionx

II

LMS_I_xI I

LMS_I_I LMS 1 2

I Ireadme.doc heada headb headc

I

I ] I Iday000 dayl001 day002 dayx

I l Igain accel temp

II I I

axm00102.15r aymO0101.35r other data files

I Iawhere.doc summary.doc

The SAMS data files (located at the bottom of the tree structure) are named based upon the contents of

the file. For example, a file named "axm00102.15r" would contain head A data for the x-axis for day

001, hour 02, file 1 of 5. The readme.doc files give a complete explanation of the file naming

convention.

A1


tARE datafiles are also arranged in a tree-like structure, but with different branches. The data

are first divided based upon mission, and then are divided based upon type of data. The tARE treestructure looks like this:

pub

I I I IMMA-LMS tARE UTILS USERS SAMS-MIR SAMS-SHUTIq.,E

II I I

iml-2 lms usml-2

, fJ ,ms -raw msfc-processed

canipus I Ifilename filename filename

Files under the canopus directory are trimmean filter data, computed by Canopus Systems, Inc. Files

under the msfc-raw directory contain the telemetry data files provided to PIMS by the Marshall Space

Flight Center Payload Operations Control Center data reduction group. Files under the msfc-processed

directory are raw files containing binary floating point values, listing the MET (in hours), and the x, y,

and z axis acceleration in micro-g's. Selected MMA data files are located in the MMA-LMS

subdirectory. See the readme fries for complete data descriptions.

Data access tools for different computer platforms (MS-DOS, Macintosh, SunOS, and MS-

Windows) are available in the/pub/UTILS directory.

The NASA LeRC beech file server can be accessed via anonymous File Transfer Protocol (ftp),

as follows:

1) Open an ftp connection to "beech.lerc.nasa.gov"

2) Login as userid "anonymous"

3) Enter your e-mail address as the password

4) Change directory to pub

5) List the files and directories in the pub directory

6) Change directories to the area of interest

7) Change directories to the mission of interest

8) Enable binary file transfers

9) Use the data file structures (described above) to locate the desired files

10) Transfer the desired files

If you encounter difficulty in accessing the data using the file server, please send an electronic

mail message to "[email protected]". Please describe the nature of the difficulty and also give a

description of the hardware and software you are using to access the file server.

A2


Appendix B: Bibliography

Summary Report of Mission Acceleration Measurements for SPACEHAB- 1, STS-57, NASA Technical

Memorandum 106514, March 1994, [launched 06/21/93]

Summary Report of Mission Acceleration Measurements for SPACEHAB-2, STS-60, NASA Technical

Memorandum 106797, [launched 02/11/94]

Summary Report of Mission Acceleration Measurments for STS-62, USMP-2, NASA Technical


Summary Report of Mission Acceleration Measurements for STS-65, IML-2, NASA Technical


Quick Look Report of Acceleration Measurements on Mir Space Station During Mir-16, NASA TecnicalMemorandum 106835

Summary Report of Mission Acceleration Measurements for STS-66, ATLAS-3, NASA

Technical Memorandun 106914, [launched 11/03/94]

Summary Report of Mission Acceleration Measurements for STS-73, USML-2, NASA Technical


Summary Report of Mission Acceleration Measurements for STS-75, USMP-3, NASA Technical


Further Analysis of the Microgravity Environment on Mir Space Station during Mir-16, NASATechnical Memorandum 107239

SAMS Acceleration Measurements on Mir From June to November 1995, NASA Technical

Memorandum 107312

Summary Report of Mission Acceleration Measurements for STS-78, LMS, NASA Technical


DeLombard, R.: SAMS Acceleration Measurements on Mir From November 1995 to June 1996, NASA

TM-107435, 1997

DeLombard, R. and Finley, B.D.: Space Acceleration Measurement System Description and Operation

on the First Spacelab Life Sciences Mission, NASA TM-105301, 1991.

B1


DeLombard, R.; Finley, B.D.; and Baugher, C.R.: Development of and Flight Results from the Space

Acceleration Measurement System (SAMS), AIAA 92-0354 (NASA TM-105652),

January 1992.

Blanchard, R. C.; Hendrix, M. K.; Fox, J. C.; Thomas, D. J.; and Nicholson, J. Y.:Orbital

Acceleration Research Experiment. Journal of Spacecraft and Rockets, Vol. 24, No. 6, 1987.

Blanchard, R. C.; Nicholson, J. Y. and Ritter, J. R.: STS-40 Orbital Acceleration Research

Experiment Flight Results During a Typical Sleep Period, Microgravity Science Technology,

Vol. V, No. 2, 1992.

DeLombard, R.: Compendium of Information for Interpreting the Microgravity Environment of the

Orbiter Spacecraft, NASA TM-107032, 1996.

Shuttle Reference Document on the World Wide Web at URL: http://www.ksc.nasa.gov/shuttle/technol-

ogy/sts-newsref/stsref-toc.html

DeLombard, R.; Moskowitz, M.E.; Hrovat, K.; and McPherson, K. M.: Comparison Tools for Assessing

the Microgravity Environment of Missions, Carriers and Conditions, NASA Technical Memorandum

107446, April 1997.

B2


Appendix C: User Comment Sheet

We would like you to give us some feedback so that we may improve the Microgravity Environment

Description Handbook. Please answer the following questions and give us your comments.

1. Did the Microgravity Environment Description Handbook fulfill your requirements for accelerationand mission information? Yes No

If not why not?

Comments:

2. Is there additional information which you feel should be included in this Microgravity Environment

Description Handbook? _.Yes No

If so what is it?

Comments:

3. Is there information in this report which you feel is not necessary or useful?

Yes No

If so, what is it?

Comments:

4. Do you have intemet access via: ( __ )ftp ( w )WWW

ready accessed SAMS data or information electronically?

Yes No

Comments:

( __ )gopher ( __ )other? Have you al-

Completed by: Name:

Address:

Telephone

Facsimile

E-mail address

Return this sheet to:

Duc Truong, PIMS Project Manager

NASA Lewis Research Center

21000 Brookpark Road MS 500-216

Cleveland, OH 44135

or

FAX to PIMS Project: 216-433-8660

e-mail to: [email protected].

http://www.lerc.nasa.gov/WWW/MMAP/PIMS/

C1

Form Approved

REPORT DOCUMENTATION PAGE OMBNo.0704-0188

Public re0otting burden for this collection of information is estimated to average 1 hour per response, including the time fo¢ reviewing instructions, searching e_dsting data sources.

gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regerc,ng this burden estimate or any olher aspect of this

collection of informatio¢l, including suggestions for reducing this burden, to Washington Headquarters Sentises, Directorate for Informetion Operations and Reports, 1215 Jefferson

Davis Highway. Suite 1204, Arlington, VA 2,2202-4302. end to the Off'me of Management end Bucket. Paperwod( Reduction Project (0704-0188), Washington, DC 20503.

1. AGENCY USE ONLY (Leave blank) 2. REPORT DATE 3. REPORT TYPE AND DATES COVERED

July 1997 Technical Memorandum5. FUNDING NUMBERS4. TITLE AND SUBTITLE


e.AUTHOR(S)

RichardDeLombard, Kevin McPherson, Kenneth Hrovat,MiltonMoskowitz,

MelissaJ.B.Rogers,and Timothy Reckart

7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES)

National Aeronautics and Space AdministrationLewis Research Center

Cleveland, Ohio 44135-3191

9. SPONSORING/MONITORINGAGENCYNAME(S)AND ADDRESS(ES)

National Aeronautics and Space Administration

Washington, DC 20546-0001

WU-963--60-4)D

8. PERFORMING ORGANIZATIONREPORT NUMBER

E-10782

10. SPONSORING/MONITORINGAGENCY REPORT NUMBER

NASA TM- 107486

11. SUPPLEMENTARYNOTESRichard DeLombard and Kevin McPherson, NASA Lewis Research Center; Kenneth Hrovat, Milton Moskowitz, Melissa

J.B. Rogers, and Timothy Reckart, Tal-Cut Company, 24831 Lorain Road, Suite 203, North Olmsted, Ohio 44070. Respon-

sible person, Richard DeLombard, organization code 6727, (216) 433-5285.

1241. DISTRIBUTION/AVAILABILITY STATEMENT

Unclassified - Unlimited

Subject Categories 20, 35, and 18

This publication is available from the NASA Center for AeroSpace Information, (301) 621--0390.

12b. DISTRIBUTION CODE

13. ABSTRACT (Maximum 200 words)

The Microgravity Measurement and Analysis Project (MMAP) at the NASA Lewis Research Center (LeRC) manages the

Space Acceleration Measurement System (SAMS) and the Orbital Acceleration Research Experiment (OARE) instru-

ments to measure the microgravity environment on orbiting space laboratories. These laboratories include the Spacelab

payloads on the shuttle, the SPACEHAB module on the shuttle, the middeck area of the shuttle, and Russia's Mir space

station. Experiments are performed in these laboratories to investigate scientific principles in the near-absence of gravity.

The microgravity environment desired for most experiments would have zero acceleration across all frequency bands or a

true weightless condition. This is not possible due to the nature of spaceflight where there are numerous factors which

introduce acceleration to the environment. This handbook presents an overview of the major microgravity environment

disturbances of these laboratories. These disturbances are characterized by their source (where known), their magnitude,

frequency and duration, and their effect on the microgravity environment. Each disturbance is characterized on a single

page for ease in understanding the effect of a particular disturbance. The handbook also contains a brief description of

each laboratory.

14. SUBJECT TERMS

Microgravity environment; SAME; OARE; Shuttle; Orbitor; Mir;Acceleration measurement

17. SECURITY CLASSIFICATIONOF REPORT

Unclassified

NSN 7540-01-280-5500

18. SECURITY CLASSIFICATIONOF THIS PAGE

Unclassified

19. SECURITY CLASSIFICATIONOF ABSTRACT

Unclassified

15. NUMBER OF PAGES

14116. PRICE CODE

A07

20. LIMITATION OF ABSTRACT

Standard Form 298 (Rev. 2-89)

Prescribed by ANSI Std. Z39-18

298-102

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