4 cots components gass

8/12/2019 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

0

1000

2000

3000

4000

5000

6000

7000

8000

9000

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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