New techniques for Radiation testing of CubeSats

Transcription

1 The most important thing we build is trust ADVANCED ELECTRONIC SOLUTIONS AVIATION SERVICES COMMUNICATIONS AND CONNECTIVITY MISSION SYSTEMS New techniques for Radiation testing of CubeSats Jiri Hofman, Richard Sharp Cobham RAD solutions, United Kingdom Jiri Haze Brno University Of Technology, Czech Republic

2 Key services of Cobham RAD solutions Radiation testing, not only for space Engineering assessments and design advice for equipment operating in radiation environments Covering space, nuclear and industrial applications Materials and component testing Total ionising dose (TID) testing Single event effects (SEE) testing Irradiation with gamma rays, electrons, protons, neutrons, alpha particles and heavy ions Comprehensive test and measurement capabilities Detailed test reports with all measurement data Aim to deliver excellent customer service 1 icubesat conference, Cambridge, May 2017

3 Standard radiation testing for space 1/2 Component level testing RHA driven requirements TID - Total Ionising Dose test 1. Pre-irradiation test/characterisation 2. Device Under Test (DUT) to be irradiated using Cobalt 60 source to a particular total dose 3. Post-irradiation DUT test 4. GOTO 2 until target dose reached or DUT damaged 5. Annealing (accelerated) 6. Post-annealing DUT test SEE - Single Event Effects 1. DUT is prepared (de-lidded, thinned) 2. DUT is mounted on a special test PCB 3. DUT is exposed to particular beam (protons, heavy ions ) 4. SEEs are measured in-situ 2 icubesat conference, Cambridge, May 2017

4 Standard radiation testing for space 2/2 Challenges in standard testing Limited access to radiation sources True space environment? Accelerating (dose rate, ELDRS) Complexity of electrical test, software Preparation of the samples (SEE) Bias and timing conditions => Cost, long duration Standard radiation testing could be rather too complex and expensive for the CubeSat class missions. 3 icubesat conference, Cambridge, May 2017

5 Advanced radiation testing for CubeSats 1/2 Opportunities for improvements and cost reductions in ground testing System level test, satellite level test? Bias and test as you fly In-situ testing, self testing + external DAQ TID test: can be done both at system (PCB) and satellite level (volume limits - rotation) SEE system level test: high energy protons yes, heavy ions complicated delidding SEE satellite level test: complicated, new facilities (CERN CHARM)? 4 icubesat conference, Cambridge, May 2017

6 Advanced radiation testing for CubeSats 2/2. Opportunities for testing in the real space environment Ground testing versus real space? In-orbit/in-flight testing? Yes, but: On-board dosimetry, temperature Radiation hardened tester (redundancy?) Limited amount of telemetry data, power CubeSats are an ideal platform (cost, low shielding, shorter development time) System level and in-flight radiation testing could be a solution for CubeSat class missions. 5 icubesat conference, Cambridge, May 2017

7 PhD research Jiri s PhD research goals High resolution data acquisition for space A/D conversion, voltage references versus radiation Calibration/metrology in space Advanced radiation testing of data acquisition systems Can we fly modern industrial high-resolution systems in space? COTS?! Can we model the radiation induced degradation of the measurement accuracy using ground TID test data? In-mission life estimation of the degradation using dose data 6 icubesat conference, Cambridge, May 2017

8 RadEx2 project CubeSat compatible radiation experiment - overview RadEx2 - a miniature Radiation Experiment, version 2 Measurement of mission dose (IV of TYNDALL RADFET, PMOS) High precision temperature measurements Four independent voltage references 32-bit and 24-bit ADCs, TDAC Power: 5V analog, 3.3V digital Exposure mode: zero power Active mode: <50mW for 3min SPI bus, 2x GPIOs RadEx2 package: Schematics, COTS BOM for EM Components for FM C code Mission data to be analysed by author 7 icubesat conference, Cambridge, May 2017

9 RadEx2 project CubeSat compatible radiation experiment block diagram 8 icubesat conference, Cambridge, May 2017

10 FEES the first flight opportunity for RadEx2 System Description 1 FEES (Flexible Experimental Embedded Satellite) - Physical properties: - Dimension: 100x100x30 mm - Mass: 300 g - Telecommunications: - Bidirectional link 435 MHz - SDR downlink 435 MHz - Uplink 1260 MHz - PCB embedded antenna - IRIDIUM Short Message Burst modem & antenna - Power Ah LiPo - 4 x 1W CIC solar cells (2 each 100x100 side) - 4 experimental 2x2 cm solar cells (payload) - Electronics architecture - STM32L4 microcontroller - 40 MHz - Low power functions - Integrated electronics (one board-all subsystems) 9 icubesat conference, Cambridge, May 2017

11 FEES the first flight opportunity for RadEx2 System Description 2 FEES (Flexible Experimental Embedded Satellite) - ADCS - 3 axis gyro, mag, accel - coarse sun sensor (photodiodes) - 2 x fine sun sensors (30 FOV) - 3 x Magnetotorquers embedded in PCB - 1 x GPS module and antenna - Rough location provided by IRIDIUM module - Payloads - RadEx2 experiment - Multispectral camera (RBG-NIR) - 2x2 cm solar cells Partners: consortium of companies and institutions led by GP Advanced Projects, Italy. Launch: Q from Yasny (Russia) Dnepr launcher (G.A.U.S.S. Launch service) Orbit: LDN SSO, inclined, slightly eccentric, semi-major axis of 6974 km Mission goals: in-orbit test of attitude determination/control architecture, commercial GPS receivers, IRIDIUM signal exploitation, test of a Software Defined Radio, Earth imaging with a multispectral camera 10 icubesat conference, Cambridge, May 2017

12 FEES the first flight opportunity for RadEx2 Estimation of 1 year mission dose using SPENVIS and OMERE 11 icubesat conference, Cambridge, May 2017

13 Typical mission doses Practical data presented by CNES Source: Radiation Design Margins 2015, Robert Ecoffert, CNES 12 icubesat conference, Cambridge, May 2017

14 RadEx2 project CubeSat compatible radiation experiment radiation testing TID component level tests: RADFET (Vth shift and temperature coefficients) PMOS (Vth shift and temperature coefficients) VREF (Vref, functional and temperature coefficients) TID system level tests: DEMO TID experiment proof of concept (in progress): First test of the whole HW including ADC from the FM lot Target dose 5krad, extended to 10krad (6 to 12 days) 36 rad/hr low dose rate test, approx. 100x faster RadEx2 powered/tested every 30 minutes In-situ test + external DAQ system using 7.5 digit multimeter Calibration TID (Q4 2017): Three RadEx2 modules, final HW/SW Statistical data FM TID calibration (Q1 2018) - short exposure of FM HW 13 icubesat conference, Cambridge, May 2017

15 RadEx2 DEMO TID experiment Interior of the irradiation container 14 icubesat conference, Cambridge, May 2017

16 RadEx2 project Preliminary results of DEMO 5krad - dosimeters 15 icubesat conference, Cambridge, May 2017

17 RadEx2 project Preliminary results of DEMO 5krad VREF ratio 16 icubesat conference, Cambridge, May 2017

18 RadEx2 project Preliminary results TID 5krad ADCs reading TDAC 17 icubesat conference, Cambridge, May 2017

19 Conclusions Standard space radiation testing presented including its advantages and challenges Techniques for in-situ and higher level testing for CubeSats discussed: better cost/performance, but some limits In-orbit testing presented RadEx2 experiment introduced FEES mission presented, mission dose calculations RadEx2 DEMO TID experiment successful, it works! First in-orbit data available Q RadEx2 packages ready to fly with you Papers available on IEEE/ request 18 icubesat conference, Cambridge, May 2017

20 Acknowledgements The author wish to thank Cobham RAD Solutions for use of the irradiation facility and test equipment. A special thanks goes to Tyndall Works for providing the RADFETs. Research described in this talk was financed by the National Sustainability Program under grant LO1401. For the research, infrastructure of the SIX Center was used. 19 icubesat conference, Cambridge, May 2017

21 Aeroflex RAD Europe Ltd, trading as Cobham RAD Solutions Phone: Maxwell Avenue Harwell, Oxfordshire, OX11 0QT, United Kingdom