CHALLENGES AND SOLUTIONS FOR LUNAR ICECUBE BIRCHES- FIRST GENERATION CUBESAT LUNAR ORBITER SCIENCE PAYLOADS Pamela Clark (JPL) Ben Malphrus (Morehead State) Cliff Brambora, Terry Hurford, Dave Folta, Paul Mason, Matt Grubb (GSFC) Kris Angkasa (JPL) Mike Tsay (Busek) Lunar IceCube Selected for Launch on EM-1 in 2020 Currently Under Development at Morehead State NASA GSFC JPL Busek NASA IV&V Clark etal ISmallSat 2015 IceCube 2 Lunar IceCube Project Team The Team consists of university, NASA, and private sector partners: • Morehead State University Space Science Center Ben Malphrus (PI), Jeff Kruth, Kevin Brown, Michael Combs, Jose Garcia, Graduate and Undergraduate students • The Busek Company Mike Tsay, John Frongillo, Josh Model • NASA Goddard Spaceflight Center BIRCHESTeam: Pamela Clark, Dennis Reuter, Robert MacDowall, Clifford Brambora, Deepak Patel, Navigation and Tracking: David Folta Ian Banks, and Terry Hurford • NASA IV&V FSW: Matt Grubb, Scott Zemerick, Justin Morris • JPL Pamela Clark (Science PI), Kris Angkasa 8/9/2018 FY17 - AES Mid-Year 3 Lunar IceCube Objectives & Technical Approach •A 6U CubeSat mission to prospect for water in ice, liquid, and vapor forms and other lunar volatiles from a low-perigee, highly inclined lunar orbit using a compact IR spectrometer in attempt to lend insight into the transport physics from mid-latitudes to PSRs Lunar IceCube 6U will: •Be deployed during lunar trajectory by the SLS on EM-1 •use an innovative RF Ion engine to achieve lunar capture and a science orbit of 100 km perilune IAA 2016 Lunar IceCube 3/1/2016 4 NextSTEP - Lunar IceCube Status Mission Description and Objectives Lunar IceCube is a 6U small satellite whose mission is to prospect for water in ice, liquid, and vapor forms and other lunar volatiles from a low-perigee, inclined lunar orbit using a compact IR spectrometer. 1.) Lunar IceCube will be deployed by the SLS on EM-1 and 2.) use an innovative RF Ion engine combined with a low energy trajectory to achieve lunar capture and a science orbit of 100 km perilune. Strategic Knowledge Gaps 1-D Polar Resources 7: Temporal Variability and Movement Dynamics of Surface- Correlated OH and H2O deposits toward PSR retention 1-D Polar Resources 6: Composition, Form and Distribution of Polar Volatiles 1-C Regolith 2: Quality/quantity/distribution/form of H species and other volatiles in mare and highlands regolith (depending on the final inclination of the Lunar IceCube orbit) Technology Demonstrations Current Status • Busek BIT 3 - High isp RF Ion Engine Team is preparing for acceptance and • NASA GSFC - BIRCHES Miniaturized IR Spectrometer - characterize water integration of Flight Hardware and other volatiles with high spectral resolution (5 nm) and wavelength FlatSat with non rad-hard subsystems and range (1 to 4 μm) emulators is in development • Space Micro C&DH- Inexpensive Radiation-tolerant Subsystem • JPL Iris v. 2.1 Ranging Transceiver Trajectory, navigation, and thermal models • BCT- XACT ADCS w/ Star Tracker and Reaction Wheels along with communications links, mass, Critical• Custom MilestonesPumpkin- High Power (120W) CubeSat Solar Array volume and power budgets evolving PDR Phase 1 CDR/∆CDR Phase 2 Phase 3 FRR/ORR Launch Mission Ops Mission Duration Project Closure 05/16/17 05/19/2016 06/20/2016 04/26/2018 11/28/2018 04/15/2019 2020 2020-2022 2 years incl. ext. 2022-23 3/14/18 8/9/2018 FY17 - AES Mid-Year 5 EM-1 Space Launch System: SLS + Orion ISS, Moon, NEAs and Beyond… EM-1 Scheduled for 2020 Uses an Innovative Propulsion Sytem and Low Energy Trajectory 7 Design and Development Challenges •Many Aspects of Interplanetary CubeSat Missions Do Not Scale- •Require Complex Subsystems, Complex Ops, Complex FSW •Significant ∆V Requirement Dictates Complex Low Energy Manifold Trajectory •Mass and Volume Constrained •Few COTS Radiation-Tolerant Components/Subsystems Exist for CubeSats •COTS Systems at Low TRL and without Flight Heritage •Thermal Management is a Challenge- BIRCHES requires cooling to cryogenic temperatures, spacecraft has limited Radiating Surfaces •Complex Attitude Control Requirements •Power Budget Requires nearly 100 W prime power •COTS Systems Produce 72 W •Complex Ground Data Systems Required to Communicate with DSN and Process Science Data •Constrained Resources •Highly Compressed Development Timeline B. Malphrus IAA 2016 Lunar IceCube 3/1/2016 8 Lunar IceCube- Requires Complex Subsystems Pumpkin Solar Arrays Cryocooler Electronics Box GNC: BCT XACT Solar Arrays Gimbals Proton 400K Lite (Under Transponder) X-Band Transponder Pumpkin EPS UHF Deep Space Beacon UHF Dipole Antenna Busek Bit-3 RF Ion Thruster Iodine Tank BIRCHES IR Spectrometer Battery Module Cryocooler X-Band LNA X-Band SSPA 8/9/2018 FY17 - AES Mid-Year 9 Morehead State 6U CubeSat Bus B. Malphrus IAA 2016 Lunar IceCube 3/1/2016 10 Lunar IceCube Subsystems MEL v. 4.26.2016 System Mass Volume (in Us) Power Use CAD Model Source Structures, Thermal 0.85 kg 6U Exterior & Rings N/A MSU- M. MSU Management 239 x 366 x 116mm Combs C&DH: Proton 400K 0. 15 kg 0.2 U 9.3 W Space Micro Space Micro BCT XACT for ACS Control BCT XACT Harnesses, cables, coatings… 0.34 kg (est.) Conformal w/in structure 0.1 U N/A Estimated MSU Solar panels & Gimbals 1.8 kg Deployable panels intrude 10 mm N/A Pumpkin MSU + Custom Pumpkin 120W Array into structure (each) Pumpkin Solar Panel Drive Articulators Included above 120 x 88 x 20 mm (0.2U) 5 W Requested Pumpkin + Custom Pumpkin w/ Faulhaber from MMA Faulhaber Stepper motors EPS + Batteries 0.6 kg (est.) 0.25 U Quiescent Draw = EPS and MSU Pumpkin 10 mW Batteries BIT-3 Busek RF Ion Iodine 1.5027 kg <2U 65 W Busek Draft Busek 180 x 102 x 88 mm CAD model Propellant 1.2 kg Contained within Above N/A Busek CAD Busek ACS/GNC: BCT XACT + Two 50 0.92 kg 0.5 U 6.3W Cont. BCT- XACT and BCT mN RWAs 100 x 100 x 50mm (3RW@ Max) NST Comms: JPL Iris 0.90 kg 100.5 x 101.0 x 56.0 mm 27.7 W X-Band Tx Iris 2.1 JPL Power Amplifier (SSPA) 0.150 kg 86.6 x 42.7 x 17.8 mm 11.6 W- Rx LNA, LGAs 0.08 kg 0.1kg 69.4 x 47.5 x 13 mm 31.8 W Transpond UHF Beacon- AstroDev Li 0.25 kg 0.1 U 6 W Tx AstroDev MSU Quad Array 0.25 W Rx BIRCHES- Spectrometer 0.8 kg 80.33 mm x 104.87 mm x 79.38 50 mW Draft CAD GSFC Optical Box mm from GSFC BIRCHES DRE 1.02 kg 35.925 x 150 x 88 mm 25W GSFC GSFC Cryocooler 0.75 kg 80.33 mm x 68.05 mm x 79.38 mm 12W Needed GSFC Vendor Cryocooler Electronics 0.75 kg 30.48 mm x 91.44 mm x 91.44 mm TOTALS: 14.00 kg 6U: Envelope 239 x 366 x 116mm Varies by Mode 0.00 kg margin Clark etal ISmallSat 2015 IceCube 11 Significant ∆V Requirement- BIT-3 RF Ion Engine • Busek BIT-3 cm RF Ion Engine • Radiation Tolerant PPU Design • Mini-RF Cathode Innovation • Test Fired with Xenon, Iodine • Solid Iodine Propellant • Projected Performance on Lunar IceCube: ISP: 1906 sec BIT-3 Thruster Firing at the Busek Facilities Thrust: > 0.8 mN 0.90 3600 ∆v = 1.2 km/s Thrust System Isp 0.80 3200 0.70 2800 RF cathode operating together with the BIT-3 0.60 thruster, both on xenon propellant 2400 0.50 2000 0.40 1600 Thrust, mN Thrust, 0.30 1200 System Isp, sec 0.20 800 0.10 400 0.00 0 40 45 50 55 60 65 Power Input to Propulsion PPU, W Estimated Performance of a New, Scaled-Down Iodine BIT-3 12 Lunar IceCube BIT-3 Final Design Thruster; Isp Includes Neutralizer Flow Significant ∆V Requirement Dictates Use of Interplanetary Superhighway (IPS) Developed by M. Lo and S. Ross at JPL, the IPS uses low energy manifold trajectories based on stable and unstable manifolds and ballistic capture. Manifolds are created by Lagrange points through n-body effects and can now be modeled for realistic interplanetary trajectories Interplanetary Superhighway Makes Space Travel Simpler // NASA 07.17.02: "Lo conceived the theory of the Interplanetary Superhighway. Lo and his colleagues have turned the underlying mathematics of the Interplanetary Superhighway into a tool for mission design called "LTool," ... The new LTool was used by JPL engineers to redesign the flight path for the Genesis mission" Malphrus 2015 IceCube 13 Significant ∆V Requirement Dictates Complex Low Energy Manifold Trajectory L3 IceCube utilizes a minimal DV transfer trajectory harnessing expertise of GSFC flight dynamics. B. Malphrus IAA 2016 Lunar IceCube 3/1/2016 14 Complex Science Orbit Transition • Capture into a long-term weakly-stable lunar orbit (based on energy and dynamics) • Sequentially lowering apoapsis to achieve inclined science orbit with equatorial periapsis o Spiral; Spiral then apoapsis lowering; or Capture then Periapsis/Apoapsis reduction • Spiral transfer orbit shown with ~6 month decreasing periapsis altitude over 80 days – dependent on thrust / mass ratio, on-time, shadows, and efficiency • Orbit design goal to minimize shadows, achieve stable orbit, minimize fuel Shadow Transfer to Science in blue Shadow Transfer to Science in blue Capture in red Capture in red 15 Science Orbit • 100 km Periapsis Altitude at Equatorial Crossing o Drives Argument of Periapsis at Ascending Node • High Inclination (70-90) • Overlap of groundtracks for calibration o Drives semimajor axis (period of 7 hrs) o Yields a candidate orbit with a 100 km periapsis and 5000 km apoapsis altitude • Maximize Lifetime with no stationkeeping maneuvers o Dependent on inclination, placement of ascending node wrt Earth, Initial periapsis altitude, and eccentricity Three 1-month orbits Groundtrack Overlap 11/19/15 L-IC Science Orbit Dictates Complex ACS 17 Lunar IceCube BIRCHES Instrument Description and Objectives • Broadband InfraRed Compact High Resolution