Solar Probe Plus A NASA Mission to Touch

Solar Probe Plus A NASA Mission to Touch the Sun Integrated Science Investigation of the Sun Energetic Particles EARLY DRAFT Preliminary Design Review 05 – 06 NOV 2013 EPI-Lo Technology Development Reid Gurnee

Outline Solar Probe Plus A NASA Mission to Touch the Sun § EPI-Lo Technology Developments to TRL 6 § Performance requirements and derivation § Energy System Development § Fidelity of Test Article § Test and Analysis Results § Transition to Flight Update to matc § Sensor / Timing System Development § Fidelity of Test Article presentation § Test and Analysis Results § Transition to Flight § TOF/CFDD ASIC Development § Fidelity of Test Article § Test and Analysis Results § Transition to Flight 2 ISIS PDR – 07 – EPI-Lo Technology Development 05 - 06 NOV 2013

EPI-Lo Technology Developments to TRL 6 Solar Probe Plus A NASA Mission to Touch the Sun § Species composition driven by two systems, energy system and timing system § Energy and TOF performance to meet 3 He / 4 He separation § Validate one anode covering two quadrants has adequate timing performance § Validate SSD has adequate energy performance § 3 He, 4 He: 0. 5 FWHM AMU for incoming energies between ≤ 0. 2 Me. V and ≥ 2. 0 Me. V § TOF and CFD ASIC development Some slides use TOF and CFD, some use TOFD and CFDD. What does the extra “D” stand for? 3 ISIS PDR – 07 – EPI-Lo Technology Development 05 - 06 NOV 2013

EPI-Lo Performance Modeling Solar Probe Plus A NASA Mission to Touch the Sun § Two independent models used § Monte-Carlo § Inputs are timing noise, SSD noise, and path length variation § Inputs can by any distribution (not limited to Gaussian) Bullet demoted § Analytical § Inputs are timing noise, SSD noise, and path length variation § All inputs are Gaussian § The two models have been compared and shown to give identical results § Does not include foil losses (not significant for 200 ke. V He) § Modeling shows 400 n. S FWHM, 15 ke. V FWHM performance comfortably meets requirements 4 ISIS PDR – 07 – EPI-Lo Technology Development 05 - 06 NOV 2013

22. 5 degree aperture Solar Probe Plus A NASA Mission to Touch the Sun § Mass is calculated by § Therefore uncertainty is mass measurement is He separation requirement 5 ISIS PDR – 07 – EPI-Lo Technology Development 05 - 06 NOV 2013

Track Simulations Solar Probe Plus A NASA Mission to Touch the Sun § Monte-carlo model for all species with 400 n. S FWHM timing and 15 ke. V FWHM energy resolutions 1 Me. V 100 ke. V 10 n. S 6 ISIS PDR – 07 – EPI-Lo Technology Development 100 n. S 05 - 06 NOV 2013

He 3/He 4 separation Solar Probe Plus A NASA Mission to Touch the Sun § Monte-carlo model shows separation of He 3/He 4 over 200 ke. V to 2 Me. V with 400 n. S FWHM timing and 15 ke. V FWHM energy resolutions 1 Me. V 100 ke. V 10 n. S 7 ISIS PDR – 07 – EPI-Lo Technology Development 05 - 06 NOV 2013

Energy System Development Solar Probe Plus A NASA Mission to Touch the Sun § Solid State Detector is fabricated and mounted to carrier board § Energy board is fabricated and populated § All components nearly identical to flight – no design changes expected Expect SSD tested with energy board by early Oc Add photos of hardware 8 ISIS PDR – 07 – EPI-Lo Technology Development 05 - 06 NOV 2013

RBSPICE DATA with 60 ke. V X-ray source FWHM in ke. V Solar Probe Plus A NASA Mission to Touch the Sun § SSD performance base-lined on RBSPICE instrument tested with 60 ke. V Xray § Performance is ~11 ke. V FWHM Expect SSD tested with energy board by early Oct Add test data f data not available use puck test d 9 ISIS PDR – 07 – EPI-Lo Technology Development 05 - 06 NOV 2013

Timing performance: Timing Budget Solar Probe Plus A NASA Mission to Touch the Sun § CFD: 200 p. S § TOF ASIC: 200 p. S § Electron Dispersion: 200 p. S § Total: 350 p. S (requirement is 400 p. S) 10 ISIS PDR – 07 – EPI-Lo Technology Development 05 - 06 NOV 2013

Timing budget – secondary electron dispersion simulatoins Solar Probe Plus A NASA Mission to Touch the Sun § 250 ps Time Markers § Electron dispersion is less than 200 p. S Updates expected from Joe Westlake 11 ISIS PDR – 07 – EPI-Lo Technology Development 05 - 06 NOV 2013

TOF-D Test Results Solar Probe Plus A NASA Mission to Touch the Sun § TOF-D performance meets requirement § INL variations compensated for with look-up-tables § Same LUTs used to normalize path length for different apertures § Jitter is less than 1 LSB FWHM heck TOF range for He 3/He 4 separation requirement 12 ISIS PDR – 07 – EPI-Lo Technology Development 05 - 06 NOV 2013

Prototype Quadrant Sensor Testing Solar Probe Plus A NASA Mission to Touch the Sun § Timing performance testing completed on prototype sensor § End-to-end test includes variations due to electron dispersion, anode board performance, and CFDD V 0 performance § Does not include TOFD ASIC § Prototype anode board is close to flight configuration § HV isolation in imbedded capacitance § Start delay line covers two in sensors TOF-D used presentation 10, § Does not mechanically fit flight design not TOFD. Keep consistent. § Prototype sensor is similar to flight sensor – key sensor geometries are the same 13 ISIS PDR – 07 – EPI-Lo Technology Development 05 - 06 NOV 2013

Prototype Quadrant Sensor Testing Solar Probe Plus A NASA Mission to Touch the Sun § Initial results show about 300 p. S FWHM timing performance (CFD and Electron optics contributions), which meets our requirements. The next version of the CFD has lower jitter at low thresholds and reduced walk, which we expect will improve performance. 14 ISIS PDR – 07 – EPI-Lo Technology Development 05 - 06 NOV 2013

CFDD test results Solar Probe Plus A NASA Mission to Touch the Sun § CFDD extensively tested § Tests performed using CFDD test board § CFDD V 3 has improved performance 15 ISIS PDR – 07 – EPI-Lo Technology Development 05 - 06 NOV 2013

Technical Development: ASIC Progress Solar Probe Plus A NASA Mission to Touch the Sun § First version of TOF chip fabricated and tested § Temperature testing from -40°C TO 70°C § Supply tested from 3. 0 V to 3. 6 V § Functionality verified over 10 ps to 2 ns LSB § Successfully completed SEE testing at Texas A&M § Completed total dose testing § Second version of TOF chip and first version of CFD chip fabricated and tested § Flight Fabrication - Third version of TOF chip and second version of CFD chip fabricated and tested § Temperature testing from -40°C TO 70°C § Supply tested from 3. 0 V to 3. 6 V § TOF functionality verified over 10 ps to 2 ns LSB § Working with vendor final qualification of both ASICs 16 ISIS PDR – 07 – EPI-Lo Technology Development 05 - 06 NOV 2013

Transition to Flight Solar Probe Plus A NASA Mission to Touch the Sun § TOF, CFD ASICs § Complete qualification with external test house § Radiation testing on flight parts (prototype parts passed all radiation testing) § Sensor Development § Build and test EM sensor § Integrate sensor with SSD § EM design complete § Flight design will be identical 17 ISIS PDR – 07 – EPI-Lo Technology Development 05 - 06 NOV 2013

Notes Solar Probe Plus A NASA Mission to Touch the Sun § These will be removed from the final presentation 18 ISIS PDR – 07 – EPI-Lo Technology Development 05 - 06 NOV 2013

Solar Probe Plus A NASA Mission to Touch the Sun § Talked to Don § We are officially moving ahead with 0. 4 n. S FWHM, 15 ke. V FWHM. All model simulations are based on these performance numbers § Helium not much affected at 200 ke. V by foil losses § Something on efficiency? ? ? Not sure why this made it into Sw. RI’s spreadsheet for TRL 6 activities, but I think Ken has results on this 19 ISIS PDR – 07 – EPI-Lo Technology Development 05 - 06 NOV 2013

Solar Probe Plus A NASA Mission to Touch the Sun EPI-Lo Wedge Development Test type Efficiency Measurement of detector system Fabrication/testing of quadrant electronics Integration of dectector wedges to quadrant anode Demonstration of low TOF dispersion Performance demonstration of separation of 3 He 4 He Test location JHU/APL JHU/APL Notes Complete Complete TRL 6 achieved EPI_Lo TOF ASIC Development Test type Prototype ASIC Fabrication and Test Temperature testing Supply Voltage variation test TOF functionality 10 ps to 2 ns Radiation Testing Flight ASIC Fabrication and Test Temperature testing Supply Voltage variation test TOF functionality 10 ps to 2 ns Radiation Testing 20 Test location JHU/APL Texas A&M Notes Complete Complete Test of Flight ASICs for TRL 6 success JHU/APL Texas A&M ISIS PDR – 07 – EPI-Lo Technology Development 05 - 06 NOV 2013

EPI-Lo performance Model 21 ISIS PDR – 07 – EPI-Lo Technology Development Solar Probe Plus A NASA Mission to Touch the Sun 05 - 06 NOV 2013

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Solar Probe Plus A NASA Mission to Touch the Sun 24 ISIS PDR – 07 – EPI-Lo Technology Development 05 - 06 NOV 2013