4 cots components gass
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Use of COTS Components
in Academic Space Projects
Prof. Dr. Volker GassFederico BelloniSEREC event, Dbendorf, June 28, 2013
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Swiss Federal Institute of Technology
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1946 - 1968 EPUL - Ecole Polytechnique de
lUniversit de Lausanne
Since 1969 EPFL - Ecole Polytechnique Fdralede Lausanne
1853 Creation of the Ecole spciale dela Suisse Franaise based on Ecole
Centrale Paris
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EPFL in numbers (2012 figures)
9306 Students - of which 2041 Ph.D.
358 Professors
2982 Administrative and Technical Staff
Federal Budget 575 Million CHF
External Financing 228 Million CHF
Total Budget 803 Million CHF
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A steady increase
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1990 1992 1994 1996 1998 2000 2002 2004 2006 2008 2010
2012 : 9306 studentsNb of students *
2012
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Activities 2013
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Academic activities Minor in space technologies Master in space
technologies Doctoral activities Educational outreach andtraining
Technological activities Space Technologydevelopment Mesure de positionnement Review of Swiss scientificneeds Technology verificationstudies
Promotion & Representation Promotion of space activities, e.g. executive report 2012 Survey of Swiss academic and industrial competences Support to the Swiss space community ESA THAG Swiss delegation ESA/ESTEC mandate
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Swiss Space Center Members
8Status: 03.2013
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Projects
CHEOPS- Exo-Planet Characterization
CleanSpace One- Orbital Debris Removal
CubETH- ultra high displacement measurement using GNSS- High level of miniaturization
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Space Environment
Vacuum- ~108 Pa- Outgassing problem
Thermal- In LEO ~16 thermal cycles/day- -50 to + 80 C
Radiations- Van Allen Belts with trapped electrons and protons- South Atlantic Anomaly
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Radiation Effects
Total Ionizing Dose - TID- Charge generation in insulating layers. Due to electrons and protons.- Parameter drift, increased leakage currents. Eventual functional failure
Displacement Damage Dose - DDD- Disruption of crystal lattice due to protons.- Reduced gain, increased ON resistance,
reduced charge transfer efficiency in CCDs Single Event Effect SEE
- Dense path of localised ionization from asingle particle hit due to cosmic rays and highenergy protons.- Variety of transient and permanent SEE
Single Event Latch-up - SEL Single Event Upset - SEU Single Event Burnout - SEB Single Event Transient - SET
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COTS, Rad Tolerant and Rad Hard
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COTS Rad Tolerant Rad Hard
Design and
production
Process and designlimit the radiation
hardness,No lot radiation
controls
Design assures rad hardnessup to a certain level,
No lot radiation controls
Designed and processed forparticular hardness levelWafer lot radiation tested
Total Dose 2 to 10 krad 20 to 50 krad > 200 krad to >1 Mrad
SEU Threshold LET
SEU Error Rate
5 Mev/mg/cm2
10-5 errors/bit-day20 Mev/mg/cm2
10-7 to 10-8 errors/bit-day80-150 Mev/mg/cm2
10-10 to 10-12 errors/bit-day
Risk Customer performs radtesting, evaluate and
assumes all risk
Usually tested for functionalfail only
Customer evaluate risk
Mitigated by the design
Cost Low1-100$
Medium100-1000$
High1000-10000$
Source: NASA - Space Radiation Effects on Electronic Components in Low-Earth Orbit
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COTS vs. Rad Hard BoardsGomsapce
NanoMind A712DTyvak
Intrepid Pico-ClassBAE Systems
RAD750 extended 6U-220 cPCI single board
computer
Application CubeSat CubeSat Curiosity rover (MSL)
CPU ARM736DMIPS@40MHz
Atmel AT91SAM9G20440 DMIPS@400Mhz
RAD750260 DMIPS@133 MHz
Memory 2 MB RAM2 GB Flash
128 MB SDRAM512 MB Flash
36 MB SRAM4 MB EEPROM
Radiation Not specified Not specifiedLatch-up protection
>100 kradLatch-up immune
Size [mm2]
Mass [kg]
Power [W]
96 x 600.050< 0.3
83 x 940.055< 0.3
233x2202.0
< 25
Cost 6000 CHF ~6600 CHF ~200000 CHF (in 2002)14
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Swisscube
Developed in 2005 2009, by EPFL, HES-SO, FHNW and UniNE students Launched in September 2009 still active
- Only a sun sensor died in October 2011 Four MSP430F1611
- 8 MHz 16 bit microcontroller- Very reliable in space Power supply
- Direct Energy Transfer, simple and reliable- No latch up protection- Redundant batteries design
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Swisscube Batteries
Batteries doesnt like extreme temperatures, thermal cycles and vacuum COTS Lithium Polymer Varta batteries Reliable design with:
- Two independent batteries- Thermal control to maintain constant temperature (-5 to 20 C)- Box to avoid batteries inflation- Low DOD to avoid fast degradation- Redesigned battery protection circuit
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CubETH Avionics
New CubeSat in development for GNSS Earth Observations:- ETHZ Science- HSLU and HSR payload- EPFL with HES-SO satellite
Reuse as much as possible of Swisscube design- MSP430 for critical functions- Same power and batteries system
Some new development to increase performances- New CDMS design with 48 MHz ARM cortex M3 microcontroller- New CDMS flight software C/OS same as Curiosity rover (MSL)- Improved communication board (for highest data rate)
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COTS Limits ?
In 2013 NASA has successfully flown two Nexus One mobile phones- With 1 GHz ARMv7 processor
Many high performances FPGA, DSP andMicrocontroller has flown in CubeSat showingtheir reliability for short term mission
Educational satellite can assume high risk- Allowing to test in space components and technologies that can be used in realsatellites
The only limitation is the time to test and validate the designs
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Terms and abbreviation
CDMS -> Control and Data Management System DOD -> Deep Of Discharge DMIPS -> Dhrystone Million Instructions Per Second DSP -> Digital Signal Processor FPGA -> Field-Programmable Gate Array LET -> Linear Energy Transfer SEU -> Single Event Upset
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Backup
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Our world begins where most peoples world ends
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