wvu sounding rocket student project critical design … 2011... · • validate field measurements...

RockSat 2010 WVU CDR 1

WVU Sounding Rocket Student Project Critical Design Review

West Virginia University Students: N. Barnett, M. Gramlich, C. Griffith, J. Gross,

S. Majstorovic, D. Parks, B. Pitzer, E. Wolfe Advisors: D. Vassiliadis, Y. Gu, D. Pisano, E. Scime

11/18/2009


Mission Overview: Objectives

1. Education and outreach. •  Students practice technical skills •  Students enroll in S2010 credit course and attend June 2010 launch •  Project serves to develop collaborations with WFF, rocket community •  Project grows alongside existing space-related WVU programs

2. Undergraduate research. •  Students will measure fundamental physical variables (temperature, magnetic

field, plasma density) and use them to characterize the upper-atmospheric environment

•  They will become familiar with data analysis techniques and statistical inference so as to analyze and later to physically interpret their data.


Mission Overview: Science – Atmospheric and plasma science:

•  Measured variable: temperature. •  Processes: atmosphere heating/cooling mechanisms. •  Objective: identify layers based on temperature profile

•  Measured variable: terrestrial magnetic field. •  Processes: field controls charged-particle motion. •  Objectives:

–  Measure vector B, dependence on latitude, geocentric distance. –  For high S/N: detect low-frequency waves

•  Measured variable: plasma density. •  Processes: solar UV produces ionosphere >85 km. •  Objectives:

–  Emit radio pulse which is reflected where index of refraction=0 –  Measure density profile; identify E layer peak –  For high-activity conditions: high-density patches descend to E-

layer altitudes (“spread-F” effect)

Echo

Refracted rays

Refracted rays

n=0 n>0

n<0


Expected Results in Education and Research

–  STEM direction: Engineering and computer-science skills. Students will:

•  Practice designing, building, and calibrating instruments •  Develop programming skills using a microprocessor •  Practice circuit and mechanical design •  Learn key characteristics of sensors and other components. •  Be familiar with aerospace mission requirements (cost, mass, volume, etc.) and

related NASA guidelines.

–  STEM direction: elements of atmospheric and ionospheric physics. Students will:

•  Learn about the upper atmosphere and its neutral+charged components. •  Practice data analysis techniques and apply them on lab measurements. •  Validate field measurements against atmospheric and B-field models.


Payload and Canister Requirements

Requirement Method Status

WVU payload must not exceed a weight of 1.5 kg. Design, Test

Payload must operate on 3W or less. Design, Test

Payload CG at <0.25” of the geometric central axis of ICU. Design, Analysis

Allowable static envelope: cylindrical right prism with diameter of 6.98” (17.7 cm) and height of 1.8” (4.5 cm).

Design

Payload must survive 25-g acceleration Design, Test

Payload must operate in [-40C,+50C] temperature range Design, Test

Magnetometers must be calibrated for payload static fields Design, Test

Gyroscope DA rate must exceed 1000deg/s Design, Test

Payload must be capable of meeting all science objectives Design, Test

Canister payloads must meet WFF no-volt requirement Design, Test

Canister payload weight must be less than 13 lb (5.9 kg) Design, Test

Canister CG at <12” above satellite interface plane (SIP) Design, Analysis

6

RockSat 2010 WVU Payload CONOPS*

h=0 km (T=00:00) Launch; G-switch activation

h=75 km (T=01:18) Radio pulse ON

h=5.7 km (T=00:10) Payload, minus radio, fully activated

h=75 km (T=04:27) Radio pulse OFF

h=117 km (T=02:53) Apogee

h=0 km (T=15:00) Splashdown

* Time (altitude) estimates based on RockOn 2009 telemetry.

7

WVU SRP Functional Block Diagram

Power Supply Power Supply

Thermistor

uMag

G

uController

Flash Memory

RBF

ADC

Swept-f Pulse Tx

Controller /Clock

Power flow

Comm/Con

Data flow

Z Accel

Gyro

Main Board Plasma Board

Optical port

A D C

Legend

Fixed-f Pulse Tx Pre-amp &

Power filter

Super het LO

Amplifier

IF

Inertial Sensor

Reg

G

Reg ANT

Power/Reg

Comp/Store

Sensors

RF in

8

SolidWorks Drawings

Main Board

Power Supply 1

Power Supply 2

Plasma Board

G switch

Z Accel


Shared Can Logistics Plan

3 payloads in canister: -  WVU: Upper atmospheric physics (1/4 can; on 1 Macrolon plate) -  Temple U.: vibration isolation mechanism (original request: ½ can) -  U. Louisiana: Expanded RockOn payload with GPS, altimeter (½ can)

Canister budget after 11/3 telecon: –  Payload mass requirement:

•  WVU: 1.1 kg •  TU: 1 kg •  UL: 2. kg

–  Total: 4.6 kg; below the 13-lb (5.9-kg) limit

–  Payload volume requirement: •  WVU: 1/5th (1 plate); TU: 2/5ths (2); UL: 1-2/5ths (2)

–  Total: 1 canister


Shared Can Logistics Plan (cont.)

–  CG requirement: •  Payloads will be tested individually •  Corrections will be made using ballasts during integration at WFF

–  Structural interfacing: •  All payloads will use RockOn-type (Macrolon) plates and mounting.

–  Electrical interfacing: •  No electrical connection between payloads •  UL: Request for high voltage; will use conformal coating on all parts of

experiment

–  Canister communications: •  No signals exchanged between payloads


Schematics: Plasma Board

Super-heterodyne circuit for the MHz receiver


Schematics: Plasma Board (cont.)

The receiver IF amplifier

Output to detector/ADC


–  The payload is composed of two subsystems: 1.  Main board and inertial/temperature/B-field sensors. 2.  Radio board with pulse transmitter and receiver.

–  Main-board (subsystem 1) requirements: •  Provide power to microprocessor and flash memory •  Power to, control of, and communication with main-board sensors •  Operating voltage: <18 V •  Data acquisition and storage of main-board sensors (Memory: 50 ΜΒ) •  Mass <400 g •  Gyroscope range maximum: >1000 deg/s •  Magnetic field resolution: 10-8 T

–  Radio-board (subsystem 2) requirements: •  Provide power to transmitters and receiver •  Receiver range: 0.5-2.0 MHz at a resolution of 10 kHz •  Operating voltage: <45 V •  Mass <600 g

Subsystem Requirements


–  Mutual requirements: •  Main board: control, communication, data acquisition of radio board •  Main board: memory needed for radio data, 20 min, Δt=1 ms, Δω=40 kHz: 144MB

–  Requirements common to both subsystems: •  Operation time: 30 min following launch •  Survive launch and impact accelerations: 25g •  Temperature range: -40C < T < +35C •  Total payload weight: 1/4th of net canister payload weight (13 lb), or 1.477 kg

–  Design drivers: •  The following sensors have a high time resolution:

–  Z-accelerometer and gyroscope: 0.01-s –  Radio receiver and micromagnetometer: 1 ms –  [All other sensors sampled at lower (0.1-s) time resolution.]

•  Minimize fixed magnetic field on payload: <1x10-4 T (basis for mag calibration)

Subsystem Requirements (cont.)


Commands and Sensors

•  All sensors activated by TL+10 s (h=5.7 km) where TL is launch time.

•  Pulse Tx activated during ascent at TL+ 72 s (h=75 km) and returning to idle state at the same altitude during descent.

Temp Z accel Gyro B-field Hi-res

Radio Rec

40

400

2x40

0

3x40

00

100k

Data rates (baud) [Word: 4 bytes]

ADC1 ADC2

MOD5213 uC

Data Flow

DOSonCHIP

Max baud: 115.2k

Max storage: 32GB


Parts List


RockSat Payload Canister User Guide Compliance

–  Payload mass and volume

–  Payload activation •  Remove-Before-Flight (RBF) strap •  G-switches (compliant with WFF “no volt” requirement)

–  However, according to community feedback about G-switches, they can be unreliable; recommendations to instead use a) pairs of G switches or b) electronic switches

–  Rocket Interface •  Shorting wires: similar to RockOn payload

Estimated mass (kg)

Estimated volume (LWH, cm3)

Estimated volume (canister)

1 18 x 18 x 5 1/5


Plasma Board Requirements

Plasma-frequency measurement: –  A pair of radio transmitters (2x0.1 W) emit a pulse sequence with a

frequency difference close to the nominal plasma frequency (ωpe=1.6 MHz or electron density ne=3x105 cm-3). When the difference reaches the plasma (cutoff) frequency a reflected pulse is recorded by a receiver so the actual density is calculated.

– Duty cycle: to minimize EMI, transmitted signal is a square-hat pulse of δt=1 millisecond. Interval between pulses: Δt=99 ms.

– Receiver operates continuously: •  Measures the echo of the transmitted signal (active sounding) •  At low altitudes records the attenuation of medium- and short-wave

AM radio with height (passive sounding).

t

E(t) δt=1 ms Δt=99 ms


Plasma Board: RF Pulse Generation –  Sounding frequency ω1 (approx. ωpe=1.6 MHz) is generated via

heterodyning a swept-frequency signal ω+ω1 off a reference (“local-oscillator”, LO) signal at fixed ω with ω>>ω1.

–  Transmitted pulse is in 1-GHz range therefore: •  Linear dimension of transmitters is <10 cm •  Ionospheric absorption is negligible •  Signal frequency and duty cycle minimize impact on other payloads •  Pulse frequencies outside WFF93 telemetry range.

–  Sounding signal ω1 is in MHz range: •  Reflected by ionospheric medium beyond rocket sheath •  Measured by on-board receiver


Team: dp: D. Pisano, PHYS dv: D. Vassiliadis, PHYS es: E. Scime, PHYS jg: J. Gross, MAE mj: M. Jaraiedi, SGC mn: M. Napolitano, MAE st: student team, MAE/PHYS yg: Y. Gu, MAE ABL: Allegany Ballistics Lab MAE: WVU mech+aero dept PHYS: WVU physics dept SGC: Space Grant Cons.

PI dv

Instructors+ Assistants dv/yg/dp/jg

Department +College es, mj, mn

Logistics+ Procurement dv

External review

ABL

Testing+ Verification MAE,ABL

Design+ Implementation st

Project Orgchart


Project Schedule

– Schedule •  Student training •  F2009: Project •  S2010: 3-credit research course •  Testing: at WVU: MAE; external: ABL

22

RockSat 2010 WVU Project Timeline

•  The payload design period takes place primarily in the fall 2009 while implementation and testing are in spring 2010.

•  Students are increasingly involved at every aspect of the project, incl. design, implementation, calibration, and testing of payload components and, to some extent, programmatic and purchasing decisions.

•  Testing and validation will take place in WVU and ABL.

•  A small team including the highest-performing students will travel to the RockSat workshop to complete payload integration, hand over to WFF personnel, and attend the June 24, 2010 launch.

•  The payload instruments will be designed to yield measurements of sufficient length, resolution, and accuracy for students to analyze the flight data and compare with atmospheric/plasma models.


Project Management: Budgets

Mass, electrical power, RF power, and monetary* budgets:

* Not included here: S/H, consumables/supplies, testing costs.


Test Plans The hardware tests include: Mechanical: –  Vibration testing (sinusoidal and random) –  Externally-induced shock (related to launch) –  Strength test of plate and payload

EMI/RFI: -  Conducted emissions (entire payload) -  Radiated emissions (subsystem 2)

Electrical: -  Interface test -  Confirmation of no-volt requirement

Thermal: -  Ambient-pressure thermal cycle test (others not relevant due to

experiment duration)


Test Plans (cont.) Software tests and simulations will be undertaken by the

development group. Specialized software: PSpice (available), Proteus (to be purchased).

Component tests will take place in January and February 2010. Comprehensive and end-to-end tests will take place in March and April 2010.

Facilities/testing teams: –  Mechanical only: Dept. of Mechanical and Aerospace Engineering, WVU –  Hardware: ABL (after consultation) –  Software: development team


Concluding Remarks

The project has attracted physics, ME, and AE students who at this point (11/2009) have practiced C++ programming on a microprocessor, become familiar with circuit design and structural drawings, and worked on circuit and sensor integration.

As it develops into a research course in spring 2010 the project is expected to provide a significant education and research experience.


Appendix


Microcontroller: NetBurner MOD5213

Structural Drawing Block Diagram


Microcontroller: NetBurner MOD5213 (cont.)

Most MOD5213 pins can be programmed in several different ways.

Pinout information


Flash Memory: DOSonCHIP

Physical Dimensions

Pinout information


Inertial Sensor: ADIS16405

Physical Dimensions Pinout information


Micromag: Honeywell HMC2003

Physical Dimensions Pinout information

1”

0.75”


MHz-Band Receiver

UAF implementation


5.8-GHz Transmitter: AWM661TX

Physical Dimensions: 3.1”x1.0”x0.25” (LxWxH)

Circuit information

35 Existing Atmospheric Port

Payload Access Section

PL1

RockOn 2010 + RSPC Section RSPC Section Motor

Adapter Nose Cone

Terrier-Orion Rocket

Existing Optical Port

PL2

PL3

PL4

PL5

PL6

PL7

PL8

PL9

RockSat/RockOn 2010 Payload Manifest

Customer Manifest: Team 1: RockOn 2010

Team 2: RockOn 2010

Team 3: RockOn 2010

Team 4: RockOn 2010/RSPC

Team 5: RSPC

Team 6: RSPC

Team 7: RSPC

Team 8: RSPC

Team 9: RSPC

Existing Ports: 1.) One optical and one pressure port in aft payload section.

2.) Four optical ports for each can in forward payload section.

3.) Three static ports for forward payload section.

4.) One dynamic (RAM) port for forward section.

wvu sounding rocket student project critical design … 2011... · • validate field measurements...

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