FlightS4-002 Status of Hayabusa2: Asteroid Sample Return Mission to C-type Asteroid Ryugu Yuichi Tsuda, Makoto Yoshikawa (ISAS/JAXA) Highlights of Hayabusa2 Hayabusa2 is the 2nd Japanese sample return mission to small body. JAXA launched Hayabusa2 in 2014, which will explore the C-type asteroid Ryugu (1999JU3), and will return back to the Earth in 2020. • Round-trip mission – High specific impulse ion engine for continuous-thrust trajectory control. • In-situ science at “Ryugu” – 1.5year proximity operation at “Ryugu” – Four landers, four remote science instruments. • Touch down & sample collection – Two normal touch down, one pin-point touch down (to the artificial crater) are planned. • Artificial crater generation – Kinetic impact on the asteroid surface to create a 2m-class crater. – Sub-surface structure of the asteroid can be acquired. 2 Mission Scenario of Hayabusa2 June-July 2018 : Arrival at Ryugu Launch The spacecraft observes Dec. 3, 2014 ▲ the asteroid, releases the Dec. 3, 2015 small rovers and the Earth swingby lander, and executes multiple samplings. The spacecraft carries Sample analysis an impactor. New Experiment Earth Return Nov.-Dec. 2020 Nov.-Dec. 2019 : Departure The impactor collides to the 2019 surface of the asteroid. Thesamplewillbeobtained from the newly created crater. 3 Hayabusa2 Spacecraft (1/2) Deployable Xband LGA Camera (DCAM3) Xband HGA Kaband HGA Solar Array Panel Xband MGA Star Trackers Near Infrared Spectrometer (NIRS3) Reentry Capsule +Z +X Sampler Horn LIDAR ONC‐W2 +Y Science Payload Size ： 1m×1.6m×1.25m (body) Mass： 609kg (Wet) 4 Hayabusa2 Spacecraft (2/2) Ion Engine RCS thrusters ×12 ONC‐T, ONC‐W1 MASCOT Lander Thermal Infrared Imager (TIR) MINERVA‐II Rovers Small Carry‐on +Z Impactor (SCI) +X Science Payload Target Markers ×5 +Y 5 Robotic Exploration with 12 Deployable “Robots” Reentry Capsule Deployable Camera (DCAM3) MASCOT Lander MINERVA‐II2 Rover MINERVA‐II1 Rovers Target Markers Small Carry‐on Impactor (SCI) Trajectory to Ryugu Hayabusa2 trajectory Ryugu orbit Ryugu arrival Earth orbit (Jun-Jul. 2018) Sun Launch (Dec. 3, 2014) Earth swing-by We are here! (Dec. 3, 2015) (January 28,2016) 7 Events around the Earth Swingby Nov 3, 2015 TCM1 Celestial Pole Nov 10-14, 2015 TIR Earth Moon Obs. LIDAR Optical Link Nov 26, 2015 Nov 26, 2015 Eclipse in TCM2 ONC-T Earth Moon Obs. NIRS3 Earth Moon Obs. (9:58UTC) Dec 1, 2015 TCM3―Cancelled 2015/12/3 ONC-W2 Earth Obs. Eclipse (20min) Dec 3, 2015 Asteroid Relative Visual NAV Test Closest Approach to the Sun Moon Orbit Closest Approach Dec 4-8, 2015 ONC-T Earth Obs. (10:08:07UTC) NIRS3 Earth Obs. To the Sun Dec 11-21, 2015 TIR Earth Obs. LIDAR Optical Link Eclipse out NIRS3 Earth Obs. (10:18UTC) Dec 22, 2015 Return to Cruising Attitude 8 HYB2 Earth Swingby Closest Passage: Altitude 3090km (@10:08:07) over Hawaii, Swingby Deflection angle 83deg Velocity at Perigee 10.3km/s, Interplanetary Velocity 30.3→31.9km/s (+1.6km/s increase） 9 Earth Swing-by Result (Guidance and Navigation) • The targeting accuracy was 300m, which was within 0.3σ of the swing-by target ellipsoid. Targeting ellipsoid • Primary NAV was done by JAXA and to reach Ryugu excellent support including shadow navigation by JPL/DSN. • Good training also for Reentry trajectory guidance. ※1 tick=10km. Contour refers to altitude. ■ Target center ● Final Swingby Target ● Swingby Result （ ● and ● are 300m apart) 10 ONC-T Earth-Moon System, Pseudo Color, Nov.26, 2015 3,000,000km Earth Moon 11 ONC-T, Earth Pseudo Color, Dec.4, 2015 400,000km 12 Operations of Science Instruments ONC-T TIR Australia Pseudo Color image Plants exist region Thermal Image NIRS3 LIDAR Earth Moon 1-way link from the earth to the spacecraft strong (mV) m) μ signal level wave length length ( wave 受信レベル data NO weak LIDAR Signal Level (mV) Level (mV) LIDAR Signal Absorption by water on the earth LIDAR Dec. 19, 2015 Distance 6.70 million km (= 0.045AU) 13 The Earth images at swing-by (animation) The images of the Earth taken by ONC-W2.Thetime(UTC)ofeach image and the distance from the Earth are shown in the photo. The images were taken from 00:00 to 09:15 (UTC) on December 3, 2015. The viewing angle is at about 60 degrees. 14 Observation of Hayabusa2 from Ground-Based Telescope • Observation campaign :Conducted as an outreach activity • The observation was successful in 36 places out of 82. (Japan, US, NZ, AUS) ■●:successful Bisei Spaceguard Center Hoshinoko Yakata Nishiharima Obs. Results of Observation Campaign (by Takeshi Yasuda,JAPOS) 15 Conclusion • Hayabusa2 is flying normally. The Earth swingby on Dec. 3, 2015 was successful. • The propulsive cruise using ion engine will start in the next March. Total of 7000hrs of ion engine operation is scheduled to reach Ryugu. • Detailed proximity science operation schedule is being planned. Largest unknown: Ryugu’s rotation state 2015 2016 2017 2018 2019 2020 12 3 10 12 4 6 7Approach 12Reentry 12 Commis- Return EDVEGA SWBY Transfer Cruise Phase Proximity Phase Events sioning Cruise Launch Earth Swingby Ryugu Arrival Ryugu Departure EDL Operation (Dec.3) (Dec.3) (Jun-Jul.) (Nov-Dec.) (Nov-Dec.) Sothern Hemisphere Stations Operation Solar Conj. (CAN/MLG) OpNAV Oct May Jun Jul Dec Jan IES Powered Cruise Mar Jun Apr Jun Dec May Nov Jun Dec Feb Jul Oct 16 International Collaboration USA NASA Europe DLR CNES Australia SLASO/DIISR DoD/AOSG AQIS/AC 17 Collaboration with OSIRIS-REx Team Hayabusa2 OSIRIS-REx C-type Collaborations B-type Science Education Outreach ... (162173) Ryugu (101955) Bennu 18 Dec.3, 2015, Dec.11, 2015, Right after the Earth swing by success Hayabusa2 Joint Science Team Meeting 19 Thank you for Listening 20.