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

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

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

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

Project Presentation

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)

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

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 (2.5-5.5V range) Other candidates have likewise been qualified and are CELESTA compatible

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

Scientific Objectives: Proton Response

Scientific Objectives: SEL rate calculation (CREME96) Orbits: LEO circular polar (600 km, 98o) LEO elliptic polar (300-1400 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)

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

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

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

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

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)

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

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.

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

Overview of the Concept (1/2)

Overview of the Concept (2/2)

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

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

Launch Manifest Oct 2015 Space Flight ILS Launch Manifest

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

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

STELA Calculations Space object Mass: 1.0 kg Reflecting area: 0.015 m² Reflectivity coefficient: 1.5 Drag area: 0.015 m² Drag Coefficient: Constant Cd: 2.2 Atmospheric drag Atmospheric model: NRLMSISE-00 Solar activity: Mean constant Initial state Nature: Mean parameters Type: Perigee/Apogee Frame: CIRF Orbit parameters Date: 2018-04-30 Zp: - Orbit perigee - km Za: - Orbit apogee - km i: - Orbit inclination - ° Ω: 0 ° ω: 0 ° M: 0 °

STELA Calculations Orbit 1: LEO 500 km

STELA Calculations Orbit 2: LEO 600 km

STELA Calculations Orbit 3: LEO 700 km

STELA Calculations Orbit 4: LEO 400 x 600 km

STELA Calculations Orbit 5: LEO 300 x 1 400 km

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

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)

OMERE Results Orbit 1: LEO 500 km

OMERE Results Orbit 2: LEO 600 km

OMERE Results Orbit 3: LEO 700 km

OMERE Results Orbit 4: LEO 400 x 600 km

OMERE Results Orbit 5: LEO 300 x 1 400 km

Total dose received over two years depending on shielding

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 12 krad LEO 600 km 160 Gy 16 krad LEO 700 km 210 Gy 21 krad LEO 400 x 600 km 98 Gy 9,8 krad LEO 300 1 400 km 548 Gy 54 krad

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: 100 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

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

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.

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 1.1.1.1: TID shall be monitored with 1 radfet 100 nm. MIS 1.1.1.2: Radfet threshold voltage reading will have a precision of 1 mV. MIS 1.1.2: Single Event Upset shall be monitored. MIS 1.1.2.1: SEU shall be monitored with 1 Cypress SRAM. MIS 1.1.2.2: 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 1.2.1.1: SEL shall be monitored with 1 Brilliance SRAM. MIS 1.2.1.2: 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 1.7.3.1: Communication between OBDH and Payload shall be bidirectional.

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 2.3.1.1: Accumulator performances shall be monitored. MIS 2.3.1.2: Solar cells performances shall be monitored. MIS 2.3.1.3: EPS shall provide an average power of 1W. MIS 2.3.2: OBDH performance shall be monitored. MIS 2.3.2.1: Log of event shall be recorded. MIS 2.3.2.2: Log of events shall be downloaded once a day. MIS 2.3.3: TT&C performance shall be monitored. MIS 2.3.3.1: Satellite shall comply with ITU and IARU regulations. MIS 2.3.3.2: 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.

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

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

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)

System Description: First CHARM Tests (Nov 2014) Board - 0001 V5 Deported Module Board - 0002

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.

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

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

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.

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

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

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

Action Management

Risk Management

Conclusion Acceptable orbits: - SSO 500 km - SSO 600 km - SSO 700 km - LEO 400 x 600 km - LEO 300 x 1 400 km Preferred orbits regarding mission interest:  Selected orbit: LEO 600 km but the design shall be compatible with the 300 x 1 400 km orbit

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Data Budget ROBUSTA-1B

Power Budget ROBUSTA-1B

Mission Definition