BioSentinel - A Deep Space Radiation BioSensor Mission Bob Hanel – Project Manager James Chartres – Mission Systems Engineer Hugo Sanchez – Spacecraft Bus Systems Engineer CubeSat Developers Workshop 2017 Cal Poly, San Luis Obispo, CA 4/26/17 Authors Affiliated with NASA Ames Research Center, Moffett Field, CA BioSentinel Project Objectives • Advanced Exploration Systems (AES) selected BioSentinel to fly on the Space Launch System (SLS) Exploration Mission (EM-1) as a secondary payload • Payload selected to help fill HEOMD Strategic Knowledge Gaps in Radiation effects on Biology • Delivery to Dispenser Integrator, Tyvak, by 4/30/18 • Current EM-1 Launch Readiness Date (LRD): 9/30/18 • Key BioSentinel Project Objectives • Develop a deep space nanosat capability • Develop a radiation biosensor useful for other missions • Define & validate SLS secondary payload interfaces and accommodations for a biological payload • Collaborate with two other AES selected missions(non-biological) for EM-1 • Near Earth Asteroid (NEA) Scout (MSFC) • Lunar Flashlight (JPL) CubeSat Developers Workshop 2107 – April 26, 2017 2 BioSentinel Science Concept • Quantify DNA damage from space radiation environment – Space environment cannot be reproduced on earth – Omnidirectional, continuous, low flux with varying particle types – Health risk for humans spending long durations beyond LEO – Radiation flux can spike 1000x during a Solar Particle Event (SPE) • Correlate biologic response with LET Spectometer data – BioSensor payload uses engineered S. cerevisiae yeast – Measures rate of Double Strand Breaks (DSB) in DNA – Linear Energy Transfer (LET) Spectrometer measures particle energy and count • Yeast assay uses microfluidic arrays to monitor for DSBs – Three strains of S. cerevisae, two controls and engineered strain – Wet and activate multiple banks of micro-wells over mission lifetime – DSB and associated repair enable cell growth and division – Activate reserve wells in event of a Solar Particle Event (SPE) CubeSat Developers Workshop 2107 – April 26, 2017 3 Secondary Payload Location on SLS EM-1 6U Dispenser Orion Multi-Purpose Crew Vehicle (MPCV) MPCV Stage Adapter (MSA) Interim Cryogenic Space Propulsion Stage Launch (ICPS) Bracket & System Shelf (SLS) Launch Vehicle Adapter (LVSA) Core Stage • 13 - dispenser locations that each support a 6U (14 kg) secondary payload • 1 - bracket location allocated to a sequencer • EM-1 only accommodates 6U payloads; EM-2 may accommodate 12U payloads CubeSat Developers Workshop 2107 – April 26, 2017 4 BioSentinel EM-1 Mission Lunar Transfer & BioSentinel: Escape Launch into Heliocentric Orbit Fly-by Mission Orbit Lunar Transit 3-7 days Launch Secondary P/L Deployment (L+4-5 hrs) ArKst’s rendering • Up to 13 secondary payloads deployed and • Final orbit of secondary's to be determined of the Space powered within the same 2 hour window • Will likely be Earth-interior, heliocentric orbit Launch System • Low relave velocity between secondary payloads • Far outside the LEOs typically occupied by • BioSennel will not perform a delta-V maneuver, CubeSats will follow ICPS into disposal orbit – Range to Earth of 0.73 AU at 18 months – Far outside the protecKve shield of Earth’s magnetosphere CubeSat Developers Workshop 2107 – April 26, 2017 5 BioSentinel FreeFlyer Spacecraft: Physical Overview Low-Gain Antenna Avionics, Power, and Solar Array Gimbal Transponder Stack Solar Arrays BioSensor Payload Propulsion Radiaon Sensor Payloads: System TID + LET spectrometer (CF3)2CH2 Baeries Integrated Guidance Navigaon & Control Unit Medium-Gain Antenna Only showing 2-Panel Gimbaled Solar Array CubeSat Developers Workshop 2107 – April 26, 2017 BioSensor – Optical Measurement of Yeast in Fluidic Card Well 6U Spacecraft ~4U BioSensor Payload Microfluidic cards (x18) Fluidic Card with Optical Detection System Fluidic Card cross section of a single well Fluidic Card Detector & LED Boards CubeSat Developers Workshop 2107 – April 26, 2017 7 BioSensor Payload Hardware 9-Card Manifold with Bubble Traps & Desiccant Nutrient Supply Manifold with Electronics BioSensor 9-Card Manifold Assembly CubeSat Developers Workshop 2107 – April 26, 2017 8 BioSentinel – LET Spectrometer Radiation LET spectrometer supplied by JSC RadWorks • Both LET EDUs have been delivered to ARC • LET EDU#1 will be used to support a EDU spacecraft bus level vibe and thermal test. • LET EDU#2 used in Flatsat testing • First Flight Unit delivery to Ames scheduled for 5/31/17. C&DH Processor LET Spectrometer Simulator RS-422 Interface EDU CubeSat Developers Workshop 2107 – April 26, 2017 9 Solar Array: 2-Panel Gimbal, Adding 2-Panels BioSentinel 2-Panel Gimballed Solar Array EDU 1-Panel deployment test 2-Panel gimbal test BioSentinel with 4-Panel Solar Array. The plan is to keep the 2-panel Gimbaled Hawk array deployed from the 1x3 U sides (trifolds) and then add 2 – 2x3U panels that are also hinged to the gimbal housing CubeSat Developers Workshop 2107 – April 26, 2017 10 Propulsion System, XACT, & Battery Packs XACT ADCS unit sandwiched between 2 battery packs (top & bottom) Propulsion System CubeSat Developers Workshop 2107 – April 26, 2017 11 Spacecraft Subsystem Fit CheckFit Initial fit check of Structural Panels, Propulsion System, XACT, 2 Battery Packs, Iris Transponder Thermal Simulator, Sun Sensor, Dispenser Separation Connector CubeSat Developers Workshop 2107 – April 26, 2017 12 Thermal System Analysis Thermal challenge is to keep warm spacecraft bus subsytems isolated from BioSensor (4-6°C). Cards raised to 23°C during cell growth phase CubeSat Developers Workshop 2107 – April 26, 2017 13 BioSentinel Mission Phases Phase Entry Exit Duration Summary & Objectives Pre-Launch Loading of biology L/V Lift-off ~6 months • Configure BioSentinel for launch, then power-off Launch L/V Lift-off Launcher Deploys ~5 hours • Powered off BioSentinel • Survive launch environments and deployment Initialization BioSentinel Complete S/C ~14 days • Power-on, reduce tip-off rates, separates from checkout deploy solar arrays, transition SLS to safe mode • Ground station initial acquisition and tracking • Check-out of S/C systems • Lunar fly-by likely to occur Science Nominal Spacecraft Final BioSensor 365 days (goal • Collect data from all payloads SOH card is expired of 540) • Execute card experiments per science timeline • Respond to SPE events • Collect Spacecraft SOH Decommissioning End of Nominal Final pass with ~7 days • Ensure all data downlinked (note, not same as Science Operations decommissioning • Solar array switches open to Project Phase F) command ensure battery never recharges CubeSat Developers Workshop 2107 – April 26, 2017 BioSentinel Link Margin (dB) vs. Mission Days CubeSat Developers Workshop 2107 – April 26, 2017 15 BioSentinel Month-in-the-Life ConOps Monitor Bus Functions Transmit to DSN (Daily, 30 minute contact, ATS) 3 1 Media A: 4 weeks 1 Media B: 2 weeks 2 2 Wet new cards with Media A Wet cards with Media B (2 fluidic cards every 6 weeks, ATS) Collect science data (4 weeks after Media A, RTS) (Continuous, RTS) Major Functions Sub-functions Major Functions Sub-functions Major Sub-functions 1 2 3 Functions Select card • Determine fluidic card Readout • Determine fluidic card Align • Determine vector to • Select µ-controller BioSensor • Select u-controller spacecraft Earth • Select pump and valve (15 min cadence) • Select and power well • Slew to Earth vector set LEDs • Select and readout sensor Power Tx • Power transmitter Apply Fluids • Open inlet valve • Iterate all wells • Open plate valve • Open nutrient valves Readout TID • Apply power to sensor Broadcast data • Broadcast SOH • Activate Pump sensor • Wait for stabilization • On CFDP command, (5 min cadence) • Sample analog readouts transmit BioSensor, Configure • Apply cold set points to LET, TID data Thermal Control other cards Readout LET • Acquire binned data • Warm set points for Spectrometer • Store data in file system Deactivate Tx • Power off transmitter Media B sensor (1 hour cadence) Realign • Slew back to sun Close System • Close inlet valve spacecraft vector • Close plate valve Monitor for SPE • Sample TID readout • Close nutrient valves • Sample LET shutter info • De-activate pump • Wet new card if SPE detected CubeSat Developers Workshop 2107 – April 26, 2017 Ground System Architecture Space Communication and Mission Operations Center - ARC Navigation (SCaN) Networks NASA Deep Space Network Telemetry & Command TLM and Activity Planning (DSN) Command Sequencing X-band CMDS System Goldstone 34-m BWG (x3) System System TLM, CMD Station Status and TRK Goldstone 34-m HEF (x1) Packets Canberra 34-m BWG (x3*) Canberra 34-m HEF (x1) Stored TLM Flight Dynamics Engineering Plotting & Madrid 34-m BWG (x2) Files System Analysis System Trending System X-band Madrid 34-m HEF (x1) Tracking Files TLM, CMD Morehead St 21-m (x1) (in dev.) and TRK Ephemeris/Acq (early Simulation Monitor & Short-Term Data Files mission) NASA Near Earth Network System Alerting System Archival System (NEN) Scheduling Hawaii 13-m (x2) Files Wallops 11-m (D/L only) File & Data Management Dongara 13-m / 7-m Hartebeethok 10-m (D/L only) Productivity Tools TLM and CMDS Networking International Space Station (ISS) Infrastructure Stored TLM Mission Files and SPE Planning e HK TLM v ISS On- Science Planning Inputs Input r e Ground board HOSC Products S Dist. Payload Env. TLM o i Network TLM and and CMDS B Science Data Center - ARC CMDS Science Data Plotting & Short-Term Data Delayed Async. Ground Control Facility - ARC Calibration