Mission to Earth Moon Lagrange Point by a 6U CubeSat: EQUULEUS

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Cory Fields
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Ryu Funase Associate Professor, EQUULEUS project

1 Mission to Earth Moon Lagrange Point by a 6U CubeSat: EQUULEUS (EQUilibriUm Lunar-Earth point 6U Spacecraft) Ryu Funase Associate Professor, EQUULEUS project manager, Univ. of Tokyo EQUULEUS Project Team (U of Tokyo, JAXA)

2 Growing trend of nano/micro-satellites Now SpaceWorks 2

3 University of Tokyo s experience XI-V (2005): 1kg for tech. demo. Still operational (>12yrs) XI-IV (2003): 1kg The first CubeSat Still operational (>14yrs) PRISM (2009): 8kg for remote sensing (20m GSD) Still operational (>8yrs) Hodoyoshi-3 and 4 (2014) remote sensing (~6m GSD) Nano-JASMINE: 33kg for Astrometry (space science mission) Awaiting launch 3

4 6m GSD image taken by Hodoyoshi-4 satellite 4

5 Next frontier for small satellites is... deep space! 5

6 The First Interplanetary Micro-Spacecraft PROCYON

7 Piggyback launch with Hayabusa2 on Dec. 3, 2014 ISSL Hayabusa-2 (~600kg) H-IIA rocket PROCYON (~65kg) JAXA JAXA 7

8 Achievements of PROCYON [Primary mission] Demonstration of the deep space microsatellite bus Power generation/management (>240W) Thermal design to accommodate wide range of Solar distance (0.9~1.5AU) and power consumption mode (electric prop. on/off, 137W/105W) Attitude control (3-axis, <0.01deg stability) SSC16-III-05 (2016) 8

9 Achievements of PROCYON SSC16-III-05 (2016) [Primary mission] Demonstration of the deep space microsatellite bus (cont d) communication & navigation in deep space Communication from ~60,000,000 km Earth distance X-band GaN-based SSPA (Solid-State Power Amplifier) with the world s highest RF efficiency (>30%) Propulsion system for micro spacecraft RCS (8 thrusters) for attitude control/momentum management Ion propulsion system for trajectory control (1 axis, Isp=1000s, thrust>300un), ~220hr operation Trajectory guidance, control, and navigation experiment in deep space (<100km, 3σ) 9

Achievements of PROCYON [Secondary mission] Scientific observation Wide-view imaging observation of geocorona with Lya imager from a vantage point outside of the Earth s geocorona distribution

10 Achievements of PROCYON [Secondary mission] Scientific observation Wide-view imaging observation of geocorona with Lya imager from a vantage point outside of the Earth s geocorona distribution Imaging observation of the hydrogen emission around the 67P/Churyumov Gerasimenko comet (the target of ESA s ROSETTA mission) to evaluate water release rate from the comet Hydrogen emission around 67P/Churyumov Gerasimenko comet was observed on Sep. 13, This comet is the destination of the European Space Agency's Rosetta mission. [Shinnaka et al., 2017] 10

11 What PROCYON demonstrated: Possibility of deep space exploration by small satellite Out next challenge is 11

12 EQUULEUS ISSL The first CubeSat to go to Lunar Lagrange point and explore the cis-lunar region 12

Enhance the mission capability in deep space Not only obtaining the tricky deep space trajectory guidance, navigation, and

13 Why we started EQUULEUS? (The goal behind the EQUULEUS mission) 1. Going back to CubeSat again by downsizing our deep space bus Adapt to as much as deep space launch opportunities in the future 2. Enhance the mission capability in deep space Not only obtaining the tricky deep space trajectory guidance, navigation, and control techniques itself, but also enhancing our overall capability to conduct deep space missions such as: astrodynamics, mission planning and analysis, s/c system design, and s/c operation 13

15 Missions of EQUULEUS 1. [Engineering] (primary mission) demonstration of the trajectory control techniques within the Sun-Earth-Moon region by a nanospacecraft through the flight to the Earth-Moon Lagrange point L2 (EML2) 2. [Science] Imaging observation of the Earth s plasmasphere 3. [Science] Lunar impact flash observation 4. [Science] Measurement of dust environment in cis-lunar region 15

16 Trajectory all the way to EML2... EQUULEUS will perform ~6 months flight to EML2 with V of as low as ~10m/s (deterministic), by using multiple lunar gravity assists. Lunar flyby sequences DV2 LGA3 Earth-Moon L2 libration orbit Capture to EML2 libration orbit Sun DV1 Insertion to EML2 libration orbit using Sun-Earth week stability regions LGA1 LGA2 DV3 Earth Moon *LGA: Lunar Gravity Assist, EML2: Earth-Moon L2 point 16

control techniques within the Sun-Earth-Moon region by a

17 Missions of EQUULEUS (2/4) 1. [Engineering] (primary mission) demonstration of the trajectory control techniques within the Sun-Earth-Moon region by a nano-spacecraft through the flight to the Earth-Moon Lagrange point L2 (EML2) 2. [Science] Imaging observation of the Earth s plasmasphere 0.5U Detector (MCP) Metal thin film filter 10cm Mechanical shutter Primary mirror (multilayer film optimized for He+(30.4nm) 17

the Sun-Earth-Moon region by a nano-spacecraft through the flight to the Earth-Moon

18 Missions of EQUULEUS (3/4) 1. [Engineering] (primary mission) demonstration of the trajectory control techniques within the Sun-Earth-Moon region by a nano-spacecraft through the flight to the Earth-Moon Lagrange point L2 (EML2) 2. [Science] Imaging observation of the Earth s plasmasphere 3. [Science] Lunar impact flashes observation 0.5U 10cm 10cm 5cm 18

19 Missions of EQUULEUS (4/4) 1. [Engineering] (primary mission) demonstration of the trajectory control techniques within the Sun-Earth-Moon region by a nano-spacecraft through the flight to the Earth-Moon Lagrange point L2 (EML2) 2. [Science] Imaging observation of the Earth s plasmasphere 3. [Science] Lunar impact flash observation 4. [Science] Measurement of dust environment in cis-lunar region Dust impact sensors installed within spacecraft thermal blanket (MLI) 19

30cm X-Band LGA Water resistojet thrusters Attitude control unit

20 Solar Array Paddles with gimbal Ultra-stable Oscillator Propellant (water) Tank Transponder X-Band MGA X-Band LGA Battery CDH & EPS 20cm 30cm X-Band LGA Water resistojet thrusters Attitude control unit PHOENIX (plasmasphere observation) DELPHINUS (lunar impact flashes observation) 20

21 Technological challenge/advancement Miniaturization of the deep space bus (e.g. deep space communication transponder) into the CubeSat form factor XTRP demonstrated in PROCYON (2014) XTRP being developed for CubeSat (EQUULEUS) * Miniaturization * Modularization * Reduction of RF output * Reduction of power consumption Digital Processing Module &Rx Module *XTRP: X-band Transponder Power Amplifier & XTx Module 21

Transponder * Miniaturization * Modularization * Reduction of RF

22 Technological challenge/advancement Miniaturization of the deep space bus (e.g. deep space communication transponder) into the CubeSat form factor XTRP demonstrated in PROCYON (2014) *XTRP: X-band Transponder * Miniaturization * Modularization * Reduction of RF output * Reduction of power consumption XTRP being developed for CubeSat (EQUULEUS) Spec. of our CubeSat X-band deep space transponder Bit Rate: /125/1k [bps] (CMD) 8 ~ k [bps] (TLM) (<50) [mm], ~0.5U < 500 [g] <13 [W] (@Tx ON) Dimension: Mass: Power: RF output:1 [W] (+30 dbm) Navigation: RARR, DDOR Digital Processing Module &Rx Module Power Amplifier & XTx Module 22

23 Technological challenge/advancement Development of the new resistojet (warm gas) propulsion system using water as the propellant. Water is perfectly safe, non-toxic propellant, which is advantageous when we consider piggyback launch. (In-situ space resource utilization age in the future is also in my mind...) 4 x RCS thrusters ~2.5U Water tank 2 x Delta-V thrusters Vaporization chamber 23

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25 ISSL 25

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27 Summary University of Tokyo has started to challenge deep space exploration by nano/micro satellite, based on the successful nano/micro satellites development and operation in Low Earth Orbit. The first deep space micro satellite PROCYON successfully demonstrated the deep space micro-satellite bus system in After that, we have proposed and started the development of a 6U CubeSat mission to Earth - Moon Lagrange point "EQUULEUS" in the summer of The primary mission of EQUULEUS is the trajectory control demonstration in cis-lunar region, and some scientific observation missions are also carried. These missions are enabled by downsizing the deep space bus system to fit the CubeSat standard and also by developing the new propulsion system. The development of the spacecraft started in the summer of 2016 and the engineering model integration and testing was completed. The flight model development will be completed by the spring of 2018, to be ready for the launch by SLS first flight in

Jet Propulsion Laboratory, California Institute of Technology

Jet Propulsion Laboratory, California Institute of Technology MarCO: Early Flight Status Andrew Klesh, Joel Krajewski MarCO Flight Team: Brian Clement, Cody Colley, John Essmiller, Daniel Forgette, Anne Marinan, Tomas Martin-Mur, David Sternberg, Joel Steinkraus,