sams-ii: decimation of a project
Post on 23-Oct-2021
5 Views
Preview:
TRANSCRIPT
SAMS-II: Decimation of a Project
Tom SutliffNASA Glenn Research Center
Knowledge SharingFebruary, 2004
Outline
• Project Background• Realities of being an “ISS project”• Cuts: The ‘Big One’• Pain, suffering, and …survival• A new awakening• Conclusion
Project BackgroundSpace Acceleration Measurement System-II
(a 2nd generation system)
• Measures vibratory acceleration disturbances in support of the Microgravity Research Program research experiments (Code UG)– Over a dozen STS and Mir missions were supported
with SAMS• Develop a system for 10+ years of operation on
a Space Station (Freedom, Alpha, ISS, …)
STS ISS
ISS Research- New Era, New Vehicle
• ISS will provide new opportunities for on-orbit research studies
• Microgravity environment is key component being investigated
Desired Research Environment
• Vibratory:– Ranges from
milli-g to sub-µg
• Quasi-Steady:– Below 1 µg
0.1 1 10 100 1000
Frequency (Hz)
0.01
10-5
10-3
Vib
rato
ry
A
ccel
erat
ion
leve
ls (g
/g0)
10-2
10-4
10-7
10-6
10-1
SSP 41000D
Some materials research should be done at this level, but will not be done on ISS.
300
Each line represents a family of experiments
ISS vibratory requirement
Fluid Physics
Low-temperature Microgravity Physics
Materials Science
Combustion Science
Biotechnology
Measure the Environment for Research
• SAMS-II– A vibratory environment measurement system
• 0.01 Hz to 300 Hz; 1 µg to 0.1 g • Multiple sensors distributed to payloads• Centralized control computer• Ground data dissemination• Data analysis and trending
Interim Control Unit RTS (typ)
ISS MRL Network
ISS Downlink Stream
SAMS-II Ground Operations Equipment (at TSC)
Investigator’s Research Site
Internet
SAMS-II Deployments
• Control Unit– NASA EXPRESS Rack
• Remote Triaxial Sensors– EXPRESS Rack shelves– Drawers– Facilities– Locker Payloads
The Customers:NASA Microgravity Science Disciplines
Other research areas (life science, space products)
Vehicle dynamicists
Vehicle Maintenance and � Sustaining Engineering
SAMS for Space StationSAMS-II
• SAMS-II is a modular, distributed architecture acceleration measurement and analysis system
– Control Unit- data storage and analysis– Remote Triaxial Sensors- variable frequency
ranges– Ground Operations- PI command and control
access• Payloads integrate sensors at experiment location
– Digital sensors, programmable frequency ranges• General purpose acceleration measurement system
– Consistent hardware for multiple increments and multiple experiments
– Facility Racks, EXPRESS Racks capability– Provides on-orbit data analysis capability for
experiment decision-making and control• Milestones
– First flight Electronics unit delivered 5/ 99– Flight Control Unit delivered 11/99– On-orbit Operations begin 7 / 00
SAMS-II is a versatile, general purpose acceleration measurement system
But I’m getting ahead of myself...
All is well… or is it?
• Space Station development – A treacherous path
• Payloads are (were) subservient to the vehicle development– Requirements– Budgets
A Typical ISS payload development19991999
DJ F M A M J J A S O N- - - - - - - - - - -20002000
DJ F M A M J J A S O N- - - - - - - - - - -20012001
DJ F M A M J J A S O N- - - - - - - - - - -20022002
DJ F M A M J J A S O N- - - - - - - - - - -20032003
DJ F M A M J J A S O N- - - - - - - - - - -20042004
DJ F M A M J J A S O N- - - - - - - - - - -20062006
J F M A- - -19981998
DO N- - -20052005
DJ F M A M J J A S O N- - - - - - - - - - -
Rev C Assembly Sequence (9/97)Rev C Assembly Sequence (9/97)
Rev D Assembly Sequence (5/98)Rev D Assembly Sequence (5/98)
10/2/98 Assembly Sequence Planning Reference10/2/98 Assembly Sequence Planning Reference
Rev B Assembly Sequence (9/96)Rev B Assembly Sequence (9/96)
OMB Passback (Feb 99)OMB Passback (Feb 99)
9 months9 months
34 months34 months9 months9 months
UF13/99
UF28/99
UF312/00
UF41/01
1J/A6/00
UF59/01
UF6
2/02 11/02
UF75A
USL
Com
bust
ion
Rac
k (C
IR)
ARISC
ore
Rac
k (S
AR
)ARIS
Flui
dsR
ack
(FIR
)
ARIS
5A
USL
UF1
1/00
UF23/00
UF39/01
UF41/02
UF56/02
UF6
8/03 10/03
UF7CAM 16A
12/03
FIR
ARIS
CIR
ARIS
SAR
ARIS
5A
USL
UF1
4/00
UF28/00
UF32/02
CIR
ARIS
UF45/02
UF59/02
FIR
ARIS
11/03
UF7CAM 16A
1/04
SAR
ARIS
5 months5 months
3 months
3 months1 month1 month
5A
USL
UF1
11/00
UF23/01
UF310/02
CIR
ARIS
UF411/02
UF56/03
FIR
ARIS
17A9/03
UF6
4/04 5/04
UF7CAM 16A
7/04
SAR
ARIS
8 months8 months 9 months
9 months6 months6 months
Rev E Assembly Sequence (6/99)Rev E Assembly Sequence (6/99)
UF12/99
UF26/99
UF38/00
UF41/01
1J/A1/00
UF58/01
UF6
1/025A
USL
Com
bust
ion
Rac
k
ARIS Cor
e R
ack
ARIS Flui
ds R
ack
ARIS
6-30 SSAIT Approved Assembly Sequence (6/94)6-30 SSAIT Approved Assembly Sequence (6/94)
8 months8 months18 months18 months
5A
USL
UF1
1/01
UF25/01
UF32/03
CIR
ARIS
UF45/03
UF59/03
FIR
ARIS
17A3/04 8/04
UF7CAM
SAR
ARIS
4 months4 months
3 months
3 months23 months23 months
LF-?
4/06
UF6
9/04
16A
11/04
Changes in FCF Deployment due to Assembly Sequence Revisions, OMB Passback & POP 99-1
Final POP 99-1 MarksFinal POP 99-1 Marks POP 99-1 Marks
CIR: 18 mo. push (2 yr. Period)
9 mo. push (1 yr. Period)
5 mo. push (9 mo. Period)
4 mo. push (9 mo.)
8 mo. push (5 mo.)
SAMS-II Redirection Realities
• ISS-budget driven SAMS-II project constraints– traffic model (customers and timing)– Budget– scope... Realities-->
• ISS Problems ($500M over budget, facilities delay)– SAMS-II budget bar chart
• What it means for SAMS-II ...
(from All-Hands charts on 10/11/96)
Decimate the project
SAMS-II Redirection Realities (10/96)
What it means for SAMS-II ...• CLOSE-OUT ALL NON-RTS RELATED WORK
– CU redesign efforts to be documented and closed out– CU related procurements stopped– Q-SICA effort is stopped– GOE designs and procurements to be put on hold– CU-GSE efforts stopped– CU, GOE, CU-GSE Software, RFAs, design put on hold
• EXCEPTIONS: – Complete the MSS Thermal POC evaluation– Complete the Coldplate fabrication capability development study– ISSUES: Long lead VME procurement must be assessed– Other?
SAMS-II Redirection Realities (10/96)
What it means for SAMS-II ...
• CONTINUE RTS WORK– Demonstrate the RTS functionality (boot, configure, collect and transmit
data) using the Engineering Model hardware RTS– Develop and test at qualification levels an RTS system– Develop and test flight RTS systems to support user requirements– Support flight hardware deliveries to EXPRESS Rack (flight RTS-EEs: 2
at 1/97, 2 at 4/97)– Develop the support systems later (CU, GOE) that allows usage of the
RTS as provided• Will require early creation of key functional elements of CU, GOE to ensure
adequate checkout of RTS functions
BUT
SAMS-II Redirection Realities (10/96)
What it means for SAMS-II ...• OTHER APPROACHES TO BE CONSIDERED BY PROJECT/ BY
MANAGEMENT:– Eliminate a CU configuration (either Eng. Model or Qualification Unit) to
decrease program cost and still maintain a FY01 ship date– Redefine SAMS-II operational configuration (eg. a more independently
operating RTS capability)– Change project operating paradigm (fast-track, different controls and
reporting methods, all civil servant implementation team, additional risk acceptance)
• Alternate funding sources- partnering with NASDA, partnering with AMES/Centrifuge project (a sharing of development costs as well as recurring costs for hardware to be provided)
• Open to suggestions on creative ideas to save money, decrease complexity, do more with less, accomplish the same functions with less development costs
… A core system
GSE Laptop
Remote Triaxial Sensor
Electronics Enclosure
Sensor Enclosure
Remote Triaxial Sensor
• Implementation Approach– Distributed measurement system (multi-user)– Minimize sensor head size (RTS-EE + RTS-SE)
– Maintain performance• Status
– CDR 4/97; Phase 1/2 Safety Review 12/97– Qual Unit completed testing 6/98– Prepare EE Flight Unit #1 to Ship to EXPRESS
Remote TriaxialSensor System
GSE / Interim Control Unit• Implementation Approach
– Rely on existing ISS Laptop (PCS) hardware heritage– Deploy SAMS-II-specific software in Laptop for RTS
operations– House components in a standard ISIS drawer
• Status– Prel. Design Review (engineering model)– Flight unit shipment planned for 11/99.
ICU Components
Power Control Box
Air inlets (both sides)
PCS Laptop(on slides)
Fan and FilterISIS- PoweredDrawer
- custom- standard
ICU Components
• ISIS Drawer (ISS standard)
• ThinkPad 760XD Laptop (ISS standard)
• Power Control Box (PCB)• Fans (Drawer & PCB)• Circuit Breakers• Designed with Military and Industrial
Electronics for Reliability
Interim Control Unit
Remote TriaxialSensor System
Flight Unit #1
More with Less...
• Upon approval of the approach SAMS-II was solicited to provide support to:– First Fluid Physics Experiment (EXP-PCS)– A vehicle Risk Mitigation Experiment (ARIS-
ICE), – The Microgravity Science Glovebox, and – General vehicle characterization… – And others…
S-II ISS Traffic_Rev_D(5-98)Acceleration Measurement Program
ISS Traffic ModelCurrent Scope (SAMS-II)
BASELINE
Interim Control Unit
Control Unit
Remote Triaxial Sensors
EXPRESS Rack EE
SE (PCS) (TBD) (TBD) (TBD)
Fluids & Combustion EEFacility
SE
Material Science EEResearch Facility
SE
Glovebox (MSG) EE
SE
Biotechnology Facility (BTF) EE
SE
Low Temperature EEMicrogravity PhysicsFacility (LTMPF) SE
UF 14/00
UF 28/00
UF 32/02
UF 59/02
1E10/02
17A11/02
HTV22/03
UF 68/03
UF 710/03
Future
(7/04)
S-II ISS Traffic_Rev_D(5-98)Acceleration Measurement Program
ISS Traffic ModelAdded Scope (SAMS-II)
1E10/02
17A11/02
HTV22/03
UF 68/03
UF 710/03
Future
OPPORTUNITIES
MAMS
Remote Triaxial Sensors
ARIS RME EE (2)
SE (3)
EXPRESS Rack EEGround Simulator
SE (2/99)
Multi Phase Flow and EETransport Facility(MPFTF) SE
NASDA EE (4)
SE (5) (8-10/01)
(2005)
UF 14/00
UF 28/00
UF 32/02
UF 59/02
And we did it!
• SAMS-II system elements were successfully launched aboard STS-100 (ISS flight 6A), April, 2001.
• First data was acquired and downlinked on June 5, 2001
• SAMS-II has accumulated over 16,000 hours of on-orbit operational time and data.
ICU (on orbit, in EXPRESS 4)
SAMS RTS-D onboard ISS(10_01).JPG
RTS-Drawer (on orbit)
First SAMS-II Data (June 5, 2001)1st_S-II Data_Graph.jpg
Key Points• Communicating bad news can be done.
– Projects and people are resilient. • Focus on what is still viable.
– Teams just need a little positive reinforcement to remind them that the glass usually half full.
• Remember that change usually has a positive element, too.
• SAMS-II was destined to be a success.– Success comes in many forms.
Epilogue
• And as is typical of success stories, I was promoted.– So, on to my next challenge...
�Combustion Science Program(my next challenge)
• Science – Fundamental research
• Flight Projects – To conduct the investigator’s science
Combustion Science on ISS
Combustion Payloads
Multi-User DropletCombustion Apparatus
ISS US Lab Module
Combustion Experiment inFluids and Combustion Facility
Combustion Chamber
Multi-User Solid FuelCombustion Apparatus
Cool FlamesCombustion Investigation
SIBALFIST TIGER-3DREEFSATHINASTF-Pello
Commercial/ International Partner Apparatus
Water MistCatalytic Comb.Hi-Pressure
Multi-User GaseousFuel Combustion Apparatus
V-FlameFlame DesignS-FlamesPUFF
Principal Investigator (PI)Droplet Combustion
Experiments
BCDCEDCE-2
SEDC DDCE
Combustion Experiment in the
Microgravity Science Glovebox
SmokeSPIDERSALSA
2 Facilities, 15 PIs,3 partner investigations, Future research capability
An Annihilation of the Program Content(~2001)
But that’s another story.
Backup Information
SAMS-II: Decimation of a Project (how to save a project)
(and build a team)(and surpass expectations)
(and garner new customers)
SAMS-II History• SAMS-II initiated in 1991• Requirements gathered from UG disciplines• Architecture defined CU, multiple RTS
– System Hardware PDR held 11/95
• CU delayed (10/96), ICU concept developed • RTS proceeding towards multiple deliveries
– RTS CDR held 4/97; status of RFAs
• Operations to begin at 6A (4/00) [rev Rev D]
11/18/98 T. Sutliff 4
top related