One-year Deep Space Flight Results of the World s First Full-scale 50-kg-class Deep Space Probe PROCYON and Its Future Prospects

Transcription

1 ISSL One-year Deep Space Flight Results of the World s First Full-scale 50-kg-class Deep Space Probe PROCYON and Its Future Prospects Earth imagers captured during Earth re-encounter 67P/Churyumov Gerasimenko comet *Ryu Funase, Takaya Inamori, Satoshi Ikari, Naoya Ozaki, Shintaro Nakajima, Kaito Ariu, Hiroyuki Koizumi (Univ. of Tokyo), Shingo Kameda (Rikkyo Univ.), 1 Atsushi Tomiki, Yuta Kobayashi, Taichi Ito, Yasuhiro Kawakatsu (JAXA)

2 Small spacecraft development at Univ. of Tokyo XI-V (2005): 1kg XI-IV (2003): 1kg for tech. demo. The first CubeSat Still operational (>9yrs) Still operational (>12yrs) PRISM (2009): 8kg for remote sensing (20m GSD) Still operational (>6yrs) Nano-JASMINE: 33kg for Astrometry (space science mission) Awaiting launch PROCYON(2014): 65kg The first interplanetary micro-spacecraft 60kg micro-sats for remote sensing (6m GSD) Hodoyoshi-1 Hodoyoshi-3 and Hodoyoshi-4 (2014) 2

3 Beginning of PROCYON mission Rideshare interplanetary launch opportunity with Hayabusa-2 was announced. Joint mission proposal by U of Tokyo and JAXA was approved (small sat experiences + deep space exploration experiences) How small auxiliary payloads are mounted on the rocket Hayabusa2 PAF Micro satellites can be installed here JAXA Support structure to implement micro satellites 3

4 Trajectory plan to flyby asteroid 2000 DP107 12/03/2014 Launch 12/03/2015 Earth swingby (Sun-Earth fixed rotational frame) 2016/05/12 Asteroid flyby What is the asteroid 2000 DP107? Binary asteroid (asteroid with satellite ) PHA (Potentially Hazardous Asteroid) 4

5 Real-time Line-of-sight image-feedback control to track asteroid direction Rotate +Z +X +Y 1-axis Rotatable Telescope (for Optical Navigation and flyby observation) Observable Star Magnitude: 12 Surface resolution: Rotational speed: <55[deg/s] 5

6 Mission of PROCYON 3. Asteroid flyby (Jan or later) SUN 2. Earth swingby (Dec. 2015) 1. Launch (Dec. 3, 2014 together with Hayabusa-2) Primary mission Demonstration of a micro-spacecraft bus system for deep space exploration (including propulsion, deep space communication and orbit determination system) Secondary (advanced) missions GaN-based high efficiency SSPA Demo of a novel DDOR (Delta Differential One-way Range) orbit determination method ( Chirp DDOR ) Deep space maneuver to perform Earth swing-by and trajectory change to target an asteroid flyby Optical navigation and guidance to an asteroid Automatic Line-of-sight image-feedback control to track asteroid during close fast flyby [Scientific observation mission] Wide-view observation of geocorona (ultra-violet emission from hydrogen atmosphere) with Lyman alpha imager from a vantage point outside of the Earth s geocorona distribution 6

7 External View of PROCYON SAP HGA (25dBi) LGA (CMD) RCS (Xe cold gas) 1.5 m 1.5 m LGA (TLM) +Y +Z +X RCS (Xe cold gas) RCS (Xe cold gas) Telescope MGA(14dBi) 0.55 m Ion thruster (Xe) Star Tracker Geocorona Imager (LAICA) RCS (Xe cold gas) +Y +Z LGA (CMD) LGA (TLM) RCS (Xe cold gas) +X 7

8 Actual outlook of PROCYON (SAP stowed) (SAP deployed) 8

9 Internal configuration 0.55 m 9

10 One-year development schedule Year Month Schedule Launch approval Start of S/C Development Conceptual study & System design (05/2013~) EM: Engineering Model STM: Structure and Thermal Model FM: Flight Model EM/STM test FM (component)fabrication Thermal Vacuum test Vibration/Shock test Table sat test FM integration & test I/F test Ion thruster test Thermal Vacuum test Vibration test Separation shock test Very small team (20~30 staffs and students at one place) enabled quick decision making for quick development. Do not try to optimize the design. Find a feasible solution. S/C Delivery Launch (Dec. 3) 10

11 Deep space flight results 11

12 0.12 Primary mission results Demonstration of micro-spacecraft bus system for deep space exploration (requires 2~3 months) Unloading maneuver Norm of the angular momentum/nms SUN 366±3 μn T. coefficient: Doppler shift/mm s -1 Launch Ion beam current/ma (Dec. 3, 2014, together with Hayabusa-2) 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) Deep space communication & navigation from ~60,000,000 km Earth distance Deep space micro propulsion system RCS for attitude control/momentum management (8 thrusters) Ion propulsion system for trajectory control (1 axis, Isp=1000s, thrust>300un) 12

13 Secondary (advanced) mission results 3. Asteroid flyby (Jan or later) SUN 2. Earth swingby (end of 2015) 1. Launch (Dec. 3, 2014 together with Hayabusa-2) Completed Completed GaN-based SSPA (Solid-State Power Amplifier) with the world s highest RF efficiency (>30%) Demonstration of a novel DDOR (Delta Differential One-way Range) orbit determination method ( Chirp DDOR ) to improve conventional DDOR orbit determination accuracy Deep space maneuver for Earth swing-by and trajectory change to target an asteroid flyby Optical navigation and guidance to an asteroid Automatic Line-of-sight image-feedback control to track asteroid during close fast flyby [scientific observation mission] Wide-view observation of geocorona with Lyα imager from a vantage point outside of the Earth s geocorona distribution 13

14 Secondary (advanced) mission results 3. Asteroid flyby (Jan or later) TCM (Trajectory Correction Maneuver) experiment using RCS to a virtual target Guidance Accuracy will not be improved by TCM4: ~ 90[km]@3σ on B-plane, which SUNsimulated the final stage of the Earth swing-by. 2. Earth swingby (end of 2015) 1. Launch (Dec. 3, 2014 together with Hayabusa-2) Completed GaN-based SSPA (Solid-State Power Amplifier) with the world s highest RF efficiency (>30%) Completed Demonstration of a novel DDOR (Delta Achievement of deep space maneuver by the Differential One-way Range) orbit ion thruster (Transition of the closest approach determination method ( Chirp DDOR ) to distance to Earth projected on the B-plane) improve conventional DDOR orbit determination accuracy <100km Deep accuracy space maneuver (3σ) was for achieved, Earth swing-by and which trajectory satisfied change the requirement to target an for asteroid flyby 2000 Optical DP107 navigation flyby guidance and guidance to an asteroid Automatic Line-of-sight image-feedback control to track asteroid during close fast flyby [scientific observation mission] Wide-view observation of geocorona with Lyα imager from a vantage point outside of the Earth s geocorona distribution 14

15 Secondary (advanced) mission results 3. Asteroid flyby (Jan or later) SUN 2. Earth swingby (end of 2015) 1. Launch (Dec. 3, 2014 together with Hayabusa-2) Completed Completed GaN-based SSPA (Solid-State Power Amplifier) with the world s highest RF efficiency (>30%) Demonstration of a novel DDOR (Delta Differential One-way Range) orbit determination method ( Chirp DDOR ) to Several improve stars conventional darker than 12th DDOR magnitude orbit were successfully determination detected accuracy by the telescope, which satisfied the requirement for the optical navigation Deep space and guidance maneuver to for an Earth asteroid. swing-by and trajectory change to target an asteroid flyby Optical navigation and guidance to an asteroid Automatic Line-of-sight image-feedback control to track asteroid during close fast flyby [scientific observation mission] Wide-view observation of geocorona with Lyα imager from a vantage point outside of the Earth s geocorona distribution 15

16 Secondary (advanced) mission results 3. Asteroid flyby (Jan or later) SUN 2. Earth swingby (end of 2015) PROCYON 1. Launch (Dec. 3, 2014 together with Hayabusa-2) Completed Completed Attitude maneuver profile to simulate the motion of an asteroid. Distance: km GaN-based SSPA (Solid-State Power Amplifier) with the world s highest RF efficiency (>30%) Demonstration of a novel Earth DDOR (Delta Differential One-way Range) orbit determination method ( Chirp DDOR ) to improve conventional DDOR orbit determination accuracy Deep space maneuver for Earth swing-by and trajectory change to target an asteroid flyby Optical navigation and guidance to an asteroid Automatic Line-of-sight image-feedback control to track asteroid during close fast flyby [scientific observation mission] Autonomous Wide-view observation Earth tracking of geocorona error angle with was Lyα <0.4deg imager from in this a particular vantage point environment, outside of which the satisfied Earth s geocorona the accuracy distribution requirement when the flyby altitude is a dozen kilometers. 16

17 恒星 ISSL Secondary (advanced) mission results Paper under review ~400,000 km 3. Asteroid flyby Geocoronal emission (in Rayleigh) on Jan 9, 2015 Kameda et (Jan. al., in 2016 prep. or later) Apollo 16 [Carruthers et al., 1976] SUN 2. Earth swingby (end of 2015) 1. Launch (Dec. 3, 2014 together with Hayabusa-2) Completed Completed 67P/Churyumov Gerasimenko comet Completed GaN-based SSPA (Solid-State Power Amplifier) with the world s highest RF efficiency (>30%) Demonstration of a novel DDOR (Delta Differential One-way Range) orbit determination method ( Chirp DDOR ) to improve conventional DDOR orbit determination accuracy Deep space maneuver for Earth swing-by and trajectory change to target an asteroid flyby Optical navigation and guidance to an asteroid Automatic Line-of-sight image-feedback control to track asteroid during close fast flyby [scientific observation mission] Wide-view observation of geocorona with Lyα imager from a vantage point outside of the Earth s geocorona distribution 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. 17

18 Secondary (advanced) mission results 3. Asteroid flyby (Jan or later) SUN 2. Earth swingby (end of 2015) 1. Launch (Dec. 3, 2014 together with Hayabusa-2) Completed Completed Completed GaN-based SSPA (Solid-State Power Amplifier) with the world s highest RF efficiency (>30%) Demonstration of a novel DDOR (Delta Differential One-way Range) orbit determination method ( Chirp DDOR ) to improve conventional DDOR orbit determination accuracy Deep space maneuver for Earth swing-by and trajectory change to target an asteroid flyby Optical navigation and guidance to an asteroid Automatic Line-of-sight image-feedback control to track asteroid during close fast flyby [scientific observation mission] Wide-view observation of geocorona with Lyα imager from a vantage point outside of the Earth s geocorona distribution 18

19 Summary of the flight results Demonstration of deep space bus system success! Scientific mission (geocorona observation) success! All the mission were successful except for: long-time deep space maneuver by the ion thruster actual asteroid flyby Within the very limited development time and budget, we could demonstrated the capability of this class of spacecraft to perform deep space mission by itself and it can be a useful tool of deep space exploration. 19

20 Future prospects 20

21 Possible deep space missions by small sats Hayabusa/MINERVA( JAXA) InSight/MarCO( NASA/JPL-Caltech) PROCYON Nano-sat (1~10~20kg) Example of appropriate mission type: Mother-ship/daughter-ship mission Focused mission where Limited function/performance is/should be admitted (by limiting the scope of the mission and/or limiting the environment where the spacecraft should work (work only on-site ) Micro-sat (~50kg) Example of appropriate mission type: Precursor to a larger mission (Human planetary exploration, asteroid mining, etc) which requires high performance High comm. speed High power generation High propulsive capability High obs. performance/large aperture, 21 etc

22 Possibility of international collaboration Co-development of a single spacecraft Each country provide component(s) in which it has an advantage over others, and a country is responsible for the spacecraft integration e.g.) Japan has a solid expertise on: Miniature and high-performance deep space transponder Highly efficient SSPA (solid state power amplifier) Other bus component (especially for micro-sats) A single mission by mother-ship and daughter-ship provided by different countries e.g.) Mars satellite exploration with a mothership from Japan and CubeSats from other countries e.g.) Europa/Enceladus exploration with a mothership (for remote sensing) from US and CubeSats (for multiple low-altitude flyby observation of a plume?) from other countries Sharing of deep space launch opportunities Maximize the science return from limited number of deep space launch opportunities from limited countries (US, Europe, Japan, etc.) Explore and exploit every launch opportunity over the world to maximize science return as a whole science community e.g.) rideshare, piggyback (mothership/daughtership) Do not miss any chance to ride! 22

23 EQUULEUS (EQUilibriUm Lunar-Earth point 6U Spacecraft) onboard SLS EM-1 in 2018 Mission to Earth Moon Lagrange Point by University of Tokyo and JAXA

24 Summary ISSL Univ. of Tokyo and JAXA successfully developed the world s first 50kg-class micro-spacecraft PROCYON at very low-cost within very short time (~1year). PROCYON s one-year deep space flight was quite successful. Almost all the missions were and we could demonstrate that micro-spacecraft can be a useful tool of deep space exploration. Future prospects of deep space exploration by small sats Micro-satellite with high performance requirement Nano-satellite which is optimized for limited mission scope International collaboration is essential to maximize the outcome of deep space exploration Sharing ideas, components, sub-systems, spacecraft, launch opportunities We would like to contribute to extending our knowledge of the solar system. 24

25 CubeSat (2003,2005) 世界最小 10cm の超小型衛星バス開発 Challenging new space frontier by small satellites, Univ. of Tokyo