Flight S4-002 Status of Hayabusa2: Asteroid Sample Return Mission to C-type Asteroid Ryugu. Yuichi Tsuda, Makoto Yoshikawa (ISAS/JAXA)

Transcription

1 Flight S4-002 Status of Hayabusa2: Asteroid Sample Return Mission to C-type Asteroid Ryugu Yuichi Tsuda, Makoto Yoshikawa (ISAS/JAXA)

2 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 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

3 Launch Dec. 3, 2014 Mission Scenario of Hayabusa2 Dec. 3, 2015 Earth swingby June-July 2018 : Arrival at Ryugu The spacecraft observes the asteroid, releases the small rovers and the lander, and executes multiple samplings. The spacecraft carries an impactor. New Experiment Sample analysis Earth Return Nov.-Dec Nov.-Dec : Departure 2019 The impactor collides to the surface of the asteroid. The sample will be obtained from the newly created crater. 3

4 Hayabusa2 Spacecraft (1/2) Deployable Camera (DCAM3) Solar Array Panel Xband HGA Xband LGA Xband MGA Kaband HGA Star Trackers Near Infrared Spectrometer (NIRS3) Reentry Capsule Sampler Horn Science Payload LIDAR +Z +X ONC W2 +Y Size : 1m 1.6m 1.25m (body) Mass: 609kg (Wet) 4

5 Hayabusa2 Spacecraft (2/2) Ion Engine RCS thrusters 12 ONC T, ONC W1 MASCOT Lander MINERVA II Rovers Thermal Infrared Imager (TIR) Small Carry on Impactor (SCI) +Z +X Science Payload Target Markers 5 +Y 5

6 Robotic Exploration with 12 Deployable Robots Reentry Capsule Deployable Camera (DCAM3) MASCOT Lander MINERVA II1 Rovers MINERVA II2 Rover Small Carry on Impactor (SCI) Target Markers

7 Trajectory to Ryugu Hayabusa2 trajectory Ryugu orbit Ryugu arrival (Jun-Jul. 2018) Sun Launch (Dec. 3, 2014) Earth orbit Earth swing-by (Dec. 3, 2015) We are here! (January 28,2016) 7

8 8 Events around the Earth Swingby Nov 26, 2015 TCM2 Dec 1, 2015 TCM3 Cancelled Dec 3, 2015 Closest Approach Nov 3, 2015 TCM1 Nov 10-14, 2015 TIR Earth Moon Obs. LIDAR Optical Link Nov 26, 2015 ONC-T Earth Moon Obs. NIRS3 Earth Moon Obs. 2015/12/3 ONC-W2 Earth Obs. Asteroid Relative Visual NAV Test Celestial Pole Eclipse in (9:58UTC) Eclipse (20min) Moon Orbit Dec 11-21, 2015 LIDAR Optical Link NIRS3 Earth Obs. Dec 4-8, 2015 ONC-T Earth Obs. NIRS3 Earth Obs. TIR Earth Obs. to the Sun Dec 22, 2015 Return to Cruising Attitude Closest Approach (10:08:07UTC) Eclipse out (10:18UTC) To the Sun

9 9 HYB2 Earth Swingby Closest Passage: Altitude 3090km over Hawaii, Swingby Deflection angle 83deg Velocity at Perigee 10.3km/s, Interplanetary Velocity km/s (+1.6km/s increase)

10 10 Earth Swing-by Result (Guidance and Navigation) The targeting accuracy was 300m, which was within 0.3σ of the swing-by target ellipsoid. Primary NAV was done by JAXA and excellent support including shadow navigation by JPL/DSN. Good training also for Reentry trajectory guidance. Targeting ellipsoid to reach Ryugu 1 tick=10km. Contour refers to altitude. Target center Final Swingby Target Swingby Result ( and are 300m apart)

11 11 ONC-T Earth-Moon System, Pseudo Color, Nov.26, ,000,000km Earth Moon

12 12 ONC-T, Earth Pseudo Color, Dec.4, ,000km

13 Operations of Science Instruments ONC-T TIR Australia Pseudo Color image Plants exist region Thermal Image NIRS3 wave length (μm) data NO Earth Moon Absorption by water on the earth strong weak signal level LIDAR LIDAR 受信レベル Signal Level (mv) 1-way link from the earth to the spacecraft Dec. 19, 2015 Distance 6.70 million km (= 0.045AU) 13

14 The Earth images at swing-by (animation) The images of the Earth taken by ONC-W2. The time (UTC) of each 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, The viewing angle is at about 60 degrees. 14

15 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

16 16 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 Events Commissioning EDVEGA SWBY Transfer Cruise Phase Approach Proximity Phase Return Cruise Reentry Launch (Dec.3) Earth Swingby (Dec.3) Ryugu Arrival (Jun-Jul.) Ryugu Departure (Nov-Dec.) EDL Operation (Nov-Dec.) Sothern Hemisphere Stations Operation (CAN/MLG) Oct May OpNAV Solar Conj. Jun Jul Dec Jan IES Powered Cruise Mar Jun Apr Jun Dec May Nov Jun Dec Feb Jul Oct

17 International Collaboration USA NASA Europe DLR CNES Australia SLASO/DIISR DoD/AOSG AQIS/AC 17

18 Collaboration with OSIRIS-REx Team Hayabusa2 OSIRIS-REx C-type Collaborations Science Education Outreach... B-type (162173) Ryugu (101955) Bennu 18

19 19 Dec.3, 2015, Right after the Earth swing by success Dec.11, 2015, Hayabusa2 Joint Science Team Meeting

20 Thank you for Listening 20