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Achievements of Hayabusa2: Unveiling the World of Asteroid by Interplanetary Round Trip Technology

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Achievements of Hayabusa2: Unveiling the World of Asteroid by Interplanetary Round Trip Technology Achievements of Hayabusa2: Unveiling the World of Asteroid by Interplanetary Round Trip Technology Yuichi Tsuda Project Manager, Hayabusa2 Japan Aerospace ExplorationAgency 58th COPUOS, April 23, 2021 Lunar and Planetary Science Missions of Japan 1980 1990 2000 2010 2020 Future Plan Moon 2007 Kaguya 1990 Hiten SLIM Lunar-A × Venus 2010 Akatsuki 2018 Mio 1998 Nozomi × Planets Mercury (Mars) 2010 IKAROS Venus MMX Phobos/Mars 1985 Suisei 2014 Hayabusa2 Small Bodies Asteroid Ryugu 2003 Hayabusa 1985 Sakigake Asteroid Itokawa Destiny+ Comet Halley Comet Pheton 2 Hayabusa2 Mission ✓ Sample return mission to a C-type asteroid “Ryugu” ✓ 5.2 billion km interplanetary journey. Launch Earth Gravity Assist Ryugu Arrival MINERVA-II-1 Deployment Dec.3, 2014 Sep.21, 2018 Dec.3, 2015 Jun.27, 2018 MASCOT Deployment Oct.3, 2018 Ryugu Departure Nov.13.2019 Kinetic Impact Earth Return Second Dec.6, 2020 Apr.5, 2019 Target Markers Orbiting Touchdown Sep.16, 2019 Jul,11, 2019 First Touchdown Feb.22, 2019 MINERVA-II-2 Orbiting MD [D VIp srvlxp #534<# Oct.2, 2019 Hayabusa2 Spacecraft Overview Deployable Xband Xband Camera (DCAM3) HGA LGA Xband Solar Array MGA Kaba nd Ion Engine HGA Panel RCS thrusters ×12 ONC‐T, ONC‐W1 Star Trackers Near Infrared DLR MASCOT Spectrometer (NIRS3) Lander Thermal Infrared +Z Imager (TIR) Reentry Capsule +X MINERVA‐II Small Carry‐on +Z LIDAR ONC‐W2 +Y Rovers Impactor (SCI) +X Sampler Horn Target +Y Markers ×5 Launch Mass: 609kg Ion Engine: Total ΔV=3.2km/s, Thrust=5-28mN (variable), Specific Impulse=2800- 3000sec. (4 thrusters, mounted on two-axis gimbal) Chemical RCS: Bi-prop. 20N thrusters ×12 (6 DOF maneuverability) Solar Array Paddle: 2.6kW @ 1 a.u. TT&C: X-band Uplink, X/Ka-band Downlink, 8-32Kbps, X/Ka RARR&DDOR capability 4 International Collaboration in Hayabusa2 200+ Japanese researchers, 100+ international researchers USA 1. NASA • Tracking and navigation support by JPL • Asteroid observation • Sample exchange with OSIRIS‐REx mission Europe Australia 1. DLR (Germany) 1. Australian Space Agency •Provision of MASCOT Lander (ASA) •Tracking support thr ESA • Landing authorization •Drop tower experiment 2. Department of Defense 2. CNES (France) ） •Provision of instruments (DOD aboard MASCOT • Provision of Landing site 5 Arrival at Ryugu on June 27, 2018 • Top shape with a very circular equatorial bulge • Spectrum type: Cb • Diamter: ～900 m • Mass: ～450 million ton • Obliquity: ～8° • Rotation period：P = 7.63 hours • Reflectance factor （v-band）：0.02 • Terrain: Very bumpy (C)JAXA, U of Tokyo, et.al. Accomplishments of Hayabusa2 (1/2) CAM‐H image at the 1st touchdown 1. Mobile activity of exploration robots on small body 2. Multiple robots deployment on small body MASCOT taken by ONC‐W2 Touchdown Accuracy：59.8 cm MINERVA‐II‐1A TM image MASCOT images Landing accuracy of C01‐Cb the 2nd touchdown MINERVA‐II‐1A image (3.5 m Diameter Target Landing Area) 3. 60cm‐accuracy landing and sampling on extra‐terrestrial celestial body image credit: JAXA 7 Accomplishments of Hayabusa2 (2/2) 4. Artificial crater forming and detailed 5. Multiple landing on extra‐terrestrial celestial body observation of impact process 6. Access to subsurface material Impact ejecta Accumulation of Impact ejecta observed by around artificial crater DCAM3 Deployed SCI taken by ONC‐W1 30m Artificial Crater TD2 Target Site 20m Artificial Crater impact Center Touchdown point of TD2 Target Marker 14.5m Artificial crater and TD2 point in one view Artificial crater generated by SCI (above) and its digital elevation map (right) 7. Smallest‐object constellation around extra‐ image credit: JAXA terrestrial celestial body 8 Reentry Terminal Guidance Phase • 5 TCMs in the last 2 months before Earth return. • The SRC was separated 12 hrs before reentry. • The spacecraft diverted from the reentry trajectory 11 hrs before reentry. Ion engine TCM （Sep.15-16,37M km from Earth) 2.0m/s Small trajectory adjustment Capsule reentry（Dec.6） TCM‐0 （Oct.22, Using RCS, same for later TCMs） Escape Maneuver 0.15m/s Small trajectory adjustment (Nov.12) (Dec.5, R-11hr) TCM‐1 0.007m/s Targeting to Woomera 12m/s TCM‐2 (Nov.26) 1.2m/s Final adjustment TCM‐3 (Dec.1) 0.05m/s Capsule TCM‐4 separation (Dec.5, R-12hr) TCM‐5 9 Hayabusa2 has returned! Coober Pedy, Australia, Dec.6, 2020, 2:28:48‐2:29:11JST (Altitude 80～50km) 10 Sample Return Capsule recovery Dec.6 (JST) 02:28 SRC reentry 02:32 SRC beacon signal detected 02:54 SRC landed (loss of beacon signal) 04:47 SRC found 08:03 SRC arrived at Quick Look Facility 57hr! 11:13 Fore‐heat shield found (requirement 12:31 Aft‐heat shield found 100hr) Dec.7 22:30 SRC shipped to Japan Dec.8 11:27 SRC carried into curation facility 11 Ryugu samples found in the sample container! Sample yield : 5.4g (requirement: 0.1g) Hayabusa2 Extended Mission ✓ Multi‐swingby + solar electric propulsion ✓ Pursuing for Planetary Defense technologies and sciences ✓ High speed flyby of asteroid 2001 CC21 ✓ Rendezvous to fast rotator asteroid 1998 KY26 1998 KY26 Rendezvous Earth swingby Earth swingby (2031) 2001 CC21 Flyby (2028) (2026) (2027) Significance of Hayabusa2 Science Space Exploration Engineering Planetary Defense Planetary Resource Hayabusa2 is pushing forward the boundaries of small body surface activity ACCESS / ROVING / SAMPLING / IMPACTING Launch Mass: About 4,000 kg Mission Duration: About 5 Years Launcher: H3 Launch Vehicle Target Launch Year: JFY2024 The sample return mission from the Martian moon, Phobos 15 Thank you for your attention.
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