1. Mission Definition Review November 27th 2015
CELESTA
Mission Definition Review
November 27th 2015

2. Outline for morning session
Introduction of the Project Group and the Review Group
General presentation of the project
Mission definition
Mission analysis
System Description
Preliminary technical budgets
Performance drivers, data, link budget, mass budget, power budget …
Management Plan
Documentation Plan
Schedule
Open issues synthesis

3. Outline for afternoon session
Review Group Questions – Project Group Responses
Steering Committee

4. Project Group Laurent DUSSEAU Markus BRUGGER CSU Director
Project Manager
Markus BRUGGER
Nuclear Engineer
Project Manager
Paul PERONNARD
Electronics Engineer
Payload Coordinator
Raffaello SECONDO
Ph. D student
Instrument Engineer
Anne-Sophie MERLENGHI
Cooperation Associate
Mission Engineer
Muriel BERNARD
PA Manager
Mission Manager
Ruben GARCIA-ALIA
Fellow
Scientific Mission Responsible
Salvatore DANZECA
Radiation Test Engineer
Latch up Experiment
Charles-Hubert ANDRIEU
Intern
Project Assistant
Gilles FOUCARD
Research Engineer
Layout and Implementation

5. Project Presentation

6. Scientific Objectives: SEE Qualification Approach
Selection of components which have been broadly qualified against heavy ions and protons
Estimation of the SEE rate by folding the responses with the respective environments (available tools: CREME96, OMERE…)
Calculation of the deposited energy through MC simulations (CRÈME MC, FLUKA…) and consideration of a response in the deposited energy phase-space (typically also requiring experimental data as input)

7. Scientific Objectives: Alternative Qualification Approach
Space Environment models
Device Response
Standard
Heavy Ion Cross Section
SV dimensions
Heavy Ions (LET spectrum)
Protons
(Energy spectrum)
Proton Cross Section
Deposited Energy Spectrum
CELESTA/
CHARM
Mixed-field cross section
SV dimensions

8. Scientific Objectives: Standard Qualification for CELESTA
A broad set of commercial components are available which have been qualified for SEE (mainly SEL and SEU) in recent years by the R2E team
Components with relatively large cross sections are targeted in order to obtain statistically meaningful SEE counts for the considered orbits (LEO) and mission lifetime (2 years)
Example candidates shown in this presentation: two SEL sensitive SRAMs, one with a medium sensitivity (~10-8 cm2 high energy proton cross section) and one with a high sensitivity (~10-7 cm2)
SEL sensitivity can be altered by a factor ~5 for the same component by applying a different bias ( V range)
Other candidates have likewise been qualified and are CELESTA compatible

9. Scientific Objectives: Heavy Ion Response
SRAM A – Medium Sensitivity
SRAM F – High Sensitivity

10. Scientific Objectives: Proton Response

11. Scientific Objectives: SEL rate calculation (CREME96)
Orbits:
LEO circular polar (600 km, 98o)
LEO elliptic polar ( km, 98o)
Solar minimum
AP8MIN proton + CREME96 GCR model
100 mils of aluminium shielding – Creme96 TRANS/ UPROP transport model
IRPP SEE rate calculation method: folding cross sections with spectra (considering the path-length distribution in the case of heavy ions)

12. Scientific Objectives: Spectra
Protons
Carbon
Argon
For heavy ions, the spectra are not affected by the orbit
For trapped protons, the elliptic orbit has a significantly larger flux as it enters the inner belt

13. Scientific Objectives: Expected SEL counts
(Over two years of mission)
SRAM
Circular (protons)
Circular (heavy ions)
Elliptic (protons)
Elliptic (heavy ions) A 36 37
520 41 F
550
270
7800
370
Protons and heavy ions have similar contributions
Proton dominated

14. Scientific Objectives: Proton and Heavy Ion Contributions
Proton SEEs concentrated in SAA, heavy ion SEEs mainly in polar region

15. Scientific Objectives: Alternative CELESTA SEE Qualification (1/3)
Experimental and space environments are both represented in the deposited energy phase space
Realistic SV dimensions are provided as input
LETth corresponds to the deposited energy divided by the SV thickness
Similar distributions above ~1 MeVcm2/mg
Space proton SEE rate can be derived directly through a single measurement at CHARM
Similar approach can be applied to a high energy proton beam
Proton space environment

16. Scientific Objectives: Alternative CELESTA SEE Qualification (2/3)
Heavy ion space environment
Environments are of very different nature: energetic heavy ions in space and energetic hadrons at CHARM
The indirect energy deposition from mixed-field hadrons yields equivalent LET values that follow a similar distribution (within a factor 3 for a 1-20 MeVcm2/mg range)
Ions actually depositing the charge in the experimental case have much smaller energies than environmental ones, but so is the case in standard ground-level HI tests (~10 MeV/n)

17. Scientific Objectives: Alternative CELESTA SEE Qualification (3/3)
Main advantages of CHARM qualification approach:
A single measurement can be used to estimate the overall space SEE rate (protons + heavy ions) as opposed to a broad set of measurements typically involving at least two facilities
The nature of the mixed-field enables the performance of batch tests (a large number of components tested in parallel) and full system testing
The range of the mixed-field is very large compared to the several tens of micros typically available at low energy heavy ion facilities, therefore enabling the access the otherwise not reachable areas in components and systems
Main limitation:
Mixed-field deposited energy does not follow space distribution for LET > 20 MeVcm2/mg, therefore critical components would need complementary high LET heavy ion testing
However, CHARM approach can be useful for a first screening of components or characterization of low impact parts

18. Scientific Objectives: Conclusions
The CELESTA mission will serve as a validation for the CHARM alternative characterization for SEEs, both for protons and heavy ions
Measurements though calibrated detectors such as the RadMON SRAM and RadFET will allow for benchmarking with different environment models and SEE rate prediction codes
The high expected error SEE count and measurement time resolution will allow for correlation between error rate and coordinates, space weather, etc.

19. MISSION SPECIFICATION A MISSION SPECIFICATION B
Mission Definition
USER’S NEED 1
Prove Equivalence between Charm and LEO environment
USER’S NEED 2
Entrance Rad Mon system by showing its in-flight performance on LEO mission
USER’S NEED 3
Promote Robusta-1U platform on LEO
PROJECT OBJECTIVE 1
CHARM and LEO environment characterization with the same measurement chain
PROJECT OBJECTIVE 2
CERN Rad Mon evaluation on LEO
PROJECT OBJECTIVE 3
CSU Robusta-1U platform evaluation on LEO
MISSION OBJECTIVE A
TID and SEE measurement
MISSION OBJECTIVE B
Platform telemetry analysis
MISSION SPECIFICATION A
Rad Mon and latch up experiment shall be monitored during 2 years on LEO and transferred to MCC
MISSION SPECIFICATION B
Bus performance and constraints shall
Be monitored during 2 years on LEO and compared to bus specification

20. Overview of the Concept (1/2)

21. Overview of the Concept (2/2)

22. Work Logic Philo des modèles MURIEL
ECSS-E-HB-10-02A_17December2010_Verification guidelines

23. Mission Analysis 3 main constraints: French Satellite LOS compliancy
Piggy-back  Orbit in the Launch Manifest
 Launch date (> 2018)
Mission  polar orbit (inclination)
 2 year mission duration
 Relevant SEE frequency

24. Launch Manifest Oct 2015
Space Flight
ILS Launch Manifest

25. Possible orbits Orbit 1: LEO 500 km Orbit 2: LEO 600 km Orbit 3:
LEO 400 x 600 km
Orbit 5:
LEO 300 x km
All orbits considered are polar.

26. LOS requirement European Code of Conduct for Space Debris Mitigation
ECSS-E-HB-10-02A 26

27. STELA Calculations Space object Mass: 1.0 kg Reflecting area: 0.015 m²
Reflectivity coefficient: 1.5
Drag area: m²
Drag Coefficient: Constant
Cd:
Atmospheric drag
Atmospheric model: NRLMSISE-00
Solar activity: Mean constant
Initial state
Nature: Mean parameters
Type: Perigee/Apogee
Frame: CIRF
Orbit parameters
Date:
Zp: - Orbit perigee - km
Za: - Orbit apogee - km
i: - Orbit inclination - °
Ω: 0 °
ω: 0 °
M: 0 °

28. STELA Calculations
Orbit 1:
LEO 500 km

29. STELA Calculations
Orbit 2:
LEO 600 km

30. STELA Calculations
Orbit 3:
LEO 700 km

31. STELA Calculations
Orbit 4:
LEO
400 x 600 km

32. STELA Calculations
Orbit 5:
LEO
300 x km

33. OMERE Calculations 1/2 Mission Launch date: 2018-04-30
Apogee: - Orbit apogee - km
Perigee: - Orbit perigee - km
Inclination: - Orbit inclination - °
Argument of periapsis: 0 °
RAAN: 0 °
True anomaly: 0 °
Segment duration: 2 years
Number of orbits: 100
Step per orbits: 100

34. OMERE Calculations 2/2 Environment Trapped particles
Electrons: AE8 MAX
Protons: AP8 MIN
Solar flares particles Mean event
Cosmic rays
Model: CREME 96
Elements: H
Dose
Flux: from mission data
Calculation parameter: STANDARD
Geometry: solid sphere (WCA)
Option
Calculation each: 1 orbit step
Aluminium shielding: 1 mm (expected value on board ROBUSTA-1D bus)

35. OMERE Results
Orbit 1:
LEO 500 km

36. OMERE Results
Orbit 2:
LEO 600 km

37. OMERE Results
Orbit 3:
LEO 700 km

38. OMERE Results
Orbit 4:
LEO
400 x 600 km

39. OMERE Results
Orbit 5:
LEO
300 x km

40. Total dose received over two years depending on shielding

41. OMERE Results Orbit comparison Orbit
Expected TID at the payload level (Behind 1 mm eq Al)
2 years cumulated dose
LEO 500 km
120 Gy krad
LEO 600 km
160 Gy krad
LEO 700 km
210 Gy krad
LEO 400 x 600 km
98 Gy ,8 krad
LEO km
548 Gy krad

42. CREME Calculation (1/2) Trapped Proton Calculation (TRP)
New trapped proton spectra calculation with these orbital parameters
Apogee: Orbit apogee - km
Perigee: Orbit perigee - km
Inclination: - Orbit inclination - °
initial longitude: 0 °
initial displacement from RAAN: 0 °
displacement of perigee from RAAN: 0 °
number of orbits:
trapped proton spectra for: Whole orbit
Trapped proton model: AP8MIN
Geomagnetic transmission function (GTRN)
New geomagnetic transmission function with these orbital parameters
[Orbital parameters identical as above]
Magnetic weather conditions: Quiet

43. CREME Calculation (2/2)
External space ionizing-radiation environment (FLUX)
Atomic number of lightest species: 1
Atomic number of heaviest species: 1
Environmental model
GCR version: CREME96
Solar conditions: Solar minimum
Spacecraft location: Inside earth’s magnetosphere
GTRN file: *.gtf file created by GTRN
Trapped proton file: *_ave.tr file created by TRP

44. CREME Results
Flux mainly identical for Energies above 1 GeV on all orbits.
However for energy below 1 GeV the highly elliptical orbit has a significant larger flux as it is the only orbit that enters the inner radiation belts.

45. Mission 1 Specifications
MIS 1.1: CERN Radmon module shall be part of CELESTA payload.
MIS 1.1.1: Total Ionizing Dose shall be monitored.
MIS : TID shall be monitored with 1 radfet 100 nm.
MIS : Radfet threshold voltage reading will have a precision of 1 mV.
MIS 1.1.2: Single Event Upset shall be monitored.
MIS : SEU shall be monitored with 1 Cypress SRAM.
MIS : SEU shall be counted 10 times per orbit.
MIS 1.2: CERN Latch up experiment module shall be part of CELESTA payload.
MIS 1.2.1: Single Event Latch up shall be monitored.
MIS : SEL shall be monitored with 1 Brilliance SRAM.
MIS : SEL shall be monitored continuously.
MIS 1.3: Orbit shall be LEO.
MIS 1.3.1: Orbit shall comply with space debris mitigation laws.
MIS 1.3.2: Orbit shall be highly elliptical.
MIS 1.4: Payload shall operate in LEO for 2 years.
MIS 1.4.1: Payload shall be able to sustain a radiation environment corresponding to 2 years in LEO.
MIS 1.5: A Product Assurance manager shall be assigned to the project.
MIS 1.6: Mission shall take place between 2018 and 2020.
MIS 1.7: Payload telemetry shall be sent to MCC.
MIS 1.7.1: Payload telemetry shall be sent to MCC through TT&C subsystem.
MIS 1.7.2: Payload data shall be fully downloaded to MCC in one satellite flyover.
MIS 1.7.3: Payload shall not directly communicate with MCC. Its data shall be sent via OBDH.
MIS : Communication between OBDH and Payload shall be bidirectional.

46. Mission 2 Specifications
MIS 2.1: CELESTA shall be developed following the frame of CSU’s ROBUSTA 1U development.
MIS 2.1.1: CELESTA development shall involve students in the frame of their education program (internship, PhD, post doc …).
MIS 2.1.2: CELESTA bus shall comply with CDS.
MIS 2.1.3: Project shall be divided into 7 phases.
MIS 2.1.4: A make strategy shall be preferred to a buy strategy.
MIS 2.1.5: A ProtoFlight Model strategy shall be adopted.
MIS 2.2: Cubesat attitude shall be random tumbling.
MIS 2.3: Bus performance shall be monitored.
MIS 2.3.1: EPS performance shall be monitored.
MIS : Accumulator performances shall be monitored.
MIS : Solar cells performances shall be monitored.
MIS : EPS shall provide an average power of 1W.
MIS 2.3.2: OBDH performance shall be monitored.
MIS : Log of event shall be recorded.
MIS : Log of events shall be downloaded once a day.
MIS 2.3.3: TT&C performance shall be monitored.
MIS : Satellite shall comply with ITU and IARU regulations.
MIS : Communication between TT&C and MCC shall be bidirectional
MIS 2.4: Bus constraints shall be measured.
MIS 2.4.1: Temperature sensors shall be embedded.
MIS 2.5: Bus shall be operated on LEO for 2 years.
MIS 2.5.1: Bus shall sustain a radiation environment corresponding to 2 years in LEO.
MIS 2.6: Bus specifications shall be described.
MIS 2.6.1: EPS specifications shall be described.
MIS 2.6.2: OBDH specifications shall be described.
MIS 2.6.3: TT&C specifications shall be described.
MIS 2.7: Bus specifications and bus performance shall be compared.

47. System ROBUSTA 1D CELESTA SYSTEM Satellite 1 Payload 1.1
Satellite 1
Payload
1.1
RadMon + SEL Exp
1.1.1
Platform
1.2
EPS
1.2.1
OBDH
1.2.2
S&M
1.2.3
TT&C
1.2.4
MCC 2
Ground Facilities 3
Functional Test Benches
3.1
Solar Cell Test Bench
3.1.1
Emulator
3.1.2
Environmental Test Benches
3.2
EMC/EMI
3.2.1
Vibrations
3.2.2
Shocks
3.2.3
CHARM
3.2.4
PSI
3.2.5
Co60
3.2.6
Software

48. Operational scenario LEOP: Comisionning 1 -3 jours Mission:
Rad Measurement Mode
Silent Mode
Low Consumption Mode
Post-Mission:
Passivated Mode
Out of service

49. System Description: CELeSTA TestBoard V1
GOAL: provide a first platform for the investigation of the technical constraints and requirements in view of a future Payload-like module
RADFET
BRILLIANCE
CYPRESS
SRAM BANK 1
SRAM BANK 2
RADFETS
P-i-n Diodes
CELeSTA Test Board V1
HEH fluence: Cypress CY62157EV.
TID: RadFet 100 nm.
SEL: Brilliance BS62LV1600EIP. Latchup Detection via 16 bit ADC.
Board Dimensions: 13.5cm x 10cm.
Communication via UART RS422, using MODBUS protocol.
All ICs on Board have been tested at PSI as on the RadMON.
Timings: SRAM + Radfet scanned every 2 minutes. ADC sampling at T = 500 us.
RadMON V6
TID: Measurement (RadFETs 100 nm and 400 nm)
Displacement Damage: (P-i-n Diodes)
HEH Fluence: Cypress and Toshiba SRAM
TID limit: 200 Gy (ADC is the limit)

50. System Description: First CHARM Tests (Nov 2014)
Board
V5 Deported Module
Board

51. System Description: Hardware Updates - ADC
ADC MAX11046 SHDN pin: if enabled 38 mA reduction on the ADC supply (40mA ·5V ≈ 200 mW).
PSI Campaign of Nov 2015: Failures already around ≈ 180 Gy with high dose rates.
With low dose rates degradation is mitigated by annealing.

52. System Description: Hardware Updates - SEL detection
SEL detection board
SEL detection circuit: Difference Amplifier (INA146) and Voltage Comparator. Current limited.
Tests at the CHARM patch panel location (Nov 2015):
LM139. withstand up to 500 Gy with RL = 5k. Subject to SETs.
LM339D out of specification worst case at 156 Gy. Tested with +/- 15V.
LM124: +5V and GND on the power rails. Lower sensitivity to SETs than LM111.
OPA227UA: Date code variability. No SETs, but can be subject to latchups.
Ongoing data analysis. TID reached was very low (< 10 Gy). No SETs observed

53. System Description: Hardware Updates – SEU (Cypress)
Implementation of a direct burst recognition algorithm. Tested at CHARM and PSI, currently under validation.

54. System Description: Summary of Activities
Ongoing research:
2014 CHARM tests on a prototype Test Board.
PSI campaigns: Cypress, ADC, OPA, BSI etc…
SEL detection: SEL board, research on components.
SEU: implementation of a real-time burst detection algorithm.
Work focused on reducing power consumption and ensuring TID goal  Mission specifications.
Near future activities:
RadFet: Temperature characterization. (Co60)
CAN transceiver tests at PSI.
Version 2 of the test Board (with Payload dimensions and connections)
Floating gate investigation for payload.

55. Technical Budget Mass budget: Satellite Mass 1 kg 1,3 kg
Bus Mass 900 g +/- 15%
Payload Mass 100 g +/- 15%
Link budget:
Link budget Feasibility: Yes 1W emission
Data budget:
Bus Data budget 142 bytes
Payload Data budget 8 kBytes (664 bytes/h sur 12h)
Power budget:
Satellite Power budget 0,65 W (Mean value)
PNE (no emission)=0.520 W during 57.7s/ minute (ROB-1B)
PE (Emission) = 4.01 W during 2.3s/ minute (ROB-1B)
Payload Power budget 1,3 W (Worst case)
Energy budget:
1350 W/m²- 2 SC – 28% - 0,8 dm² 3 W

56. Management Plan Internal communication Monthly Newscasts
Project communication Muriel-Anne-Sophie Weekly Skype meetings
Outreach (External Communication) Not started
Logo To be done
Student involvement Charles-Hubert ANDRIEU
Master 1 project in progress
Common tools/Software STELA, OMERE, MS Project, Office, DFS
Standards ECSS tailored

57. Documentation Management
Shared host server DFS
Documentation organization Management, Engineering, Product Assurance
Standards ECSS tailored
Naming CEL_X_ZZZ_YYYY-MM-DD_vK.K
Template Done by Muriel BERNARD on request

58. Action Management

59. Risk Management

60. Conclusion Acceptable orbits: - SSO 500 km - SSO 600 km - SSO 700 km
- LEO 400 x 600 km
- LEO 300 x km
Preferred orbits regarding mission interest:
 Selected orbit: LEO 600 km
but the design shall be compatible with the 300 x km orbit

61. BACK UP

62. Data Budget ROBUSTA-1B

63. Power Budget ROBUSTA-1B

64. Mission Definition