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 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 § Sensor / Timing System Development § Fidelity of Test Article § Test and Analysis Results § TOF-D/CFD-D 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-D and CFD-D ASIC development 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) § 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 p. 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 Consider removing slide? 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 p. 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 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 Data being taken now! If data no Available use slide as-in 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 § Electron Dispersion: 200 p. S § TOF-D ASIC: 200 p. S § CFD-D: 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 Can use slide as-is 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 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 CFD-D V 0 performance § Does not include TOF-D ASIC § Prototype anode board is close to flight configuration § HV isolation in imbedded capacitance § Start delay line covers two sensors § Does not mechanically fit flight design § 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-D and Electron optics contributions), which meets our requirements. The next version of the CFD-D 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

CFD-D test results Solar Probe Plus A NASA Mission to Touch the Sun § CFD-D extensively tested § Tests performed using CFD-D test board § CFD-D 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-D 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-D chip and first version of CFD-D chip fabricated and tested § Flight Fabrication - Third version of TOF-D chip and second version of CFD-D chip fabricated and tested § Temperature testing from -40°C TO 70°C § Supply tested from 3. 0 V to 3. 6 V § TOF-D 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-D, CFD-D ASICs § Complete qualification with external test house § Complete 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 § Finish testing EM SSD § 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 23 ISIS PDR – 07 – EPI-Lo Technology Development 05 - 06 NOV 2013

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