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Hayabusa2 Asteroid Sample Return Mission H. Kuninaka JSPEC/JAXA 10Th SBAG

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Hayabusa2 Asteroid Sample Return Mission H. Kuninaka JSPEC/JAXA 10Th SBAG Hayabusa2 Asteroid Sample Return Mission H. Kuninaka JSPEC/JAXA 10th SBAG Target Asteroid : 1999 JU3 Orbit Itokawa Rotation period: 0.3178day (~7.6 h) ����)�(331, 20), (73, -62) Kawakami Model Mueller Model Axis ratio = 1.3 : 1.1 : 1.0 Mars Size : 0.87 ± 0.03 km Earth Albedo : 0.070 ± 0.006 H=18.82 ± 0.021, G=0.110 ± 0.007 Type : Cg (by Mueller 2 Shape model by Kawakami et. al) Hayabusa vs Hayabusa2 (1) Hayabusa Hayabusa2 Size � 1m�1.6m�1.1� Size � 1m�1.6m�1.25��body� �body� Mass� 600kg�Wet� Mass� 510kg�Wet� � � � � � Communication : X-band + Ka-band � Ion engine : modified � Small lander : MASCOT(Mobile Asteroid Surface Scout� from DLR � AOCS : 4 reaction wheels Nominal Payloads for Science Payloads Specifications Multiband Imager Wavelength: 0.4 – 1.0 µm, FOV: 5.7 deg x 5.7 deg, Pixel Number: 1024 (ONC-T) x 1024 px filter (ul, b, v, w, x, p, Wide) (Heritage of Hayabusa) Near IR Spectrometer Wavelength: 1.8 – 3.2 µm, FOV: 0.1 deg x 0.1 deg (NIRS3) (Heritage of Hayabusa, but 3µm range is new) Thermal IR Imager Wavelength: 8 – 12 µm, FOV: 12 deg x 16 deg, Pixel Number: 320 x 240 (TIR) px (Heritage of Akatsuki) Laser Altimeter (LIDAR) Measurement Range: 30 m – 25 km (Heritage of Hayabusa) Sampler Minor modifications from Hayabusa-1 (Heritage of Hayabusa) Small Carry-on Impactor Small system released form the spacecraft to form an artificial crater on (SCI) the surface (New) Separation Camera Small, detached camera to watch operation of Small Carry-on Impactor (DCAM) (Heritage of Ikaros) Small Rover Similar to MINERVA of Hayabusa-1 (MINERVA II-1, II-2) (possible payload: Cameras, thermometers) (Heritage of Hayabusa) Small Rover Supplied from DLR & CNES (MASCOT) MicrOmega, MAG, CAM, MARA 4 Hayabusa2 Mission Schedule year 2014 2015 2016 2017 2018 2019 2020 month � � 12 06 12 06 08 12 12 Spacecraft IES operation Launch windows Earth Swing-by Departure Earth Arrival at Science from 1999 return 1999JU3 observation JU3 , Sampling IES operation Impactor 5 Mission Outline of Hayabusa-2 Launch June 2018 : Arrival at 1999 JU3 Global observation of the asteroid, Dec 2014 deployment of small rover/lander, Mothership carries multiple samplings an impactor. Sample analysis New Experiment Earth Return Dec. 2020 Dec. 2019 : Departure 2019 The impactor collides to the surface of the asteroid. Further exploration 6 Potential International Cooperation JAPAN USA * To NASA To JAXA •US scientists participation •Deep Space Network support •Asteroid sample provision •Radiometric navigation support •Accommodation of appointed •Cooperation with OSIRIS-REx personnel on mission ops. Europe *NASA/JAXA LOA on potential collaboration Australia between the Hayabusa-2 and OSIRIS-REx missions, Nov. 9, 2012 Summary Hayabusa2 in under development. SOE of Hayabusa2 Launch at end of 2014 Proximity Operation from June 2018 to Dec. 2019 Earth Return on Dec. 2020 Hayabusa and Hayabusa2 will contribute to Human NEA Mission Optical Navigation in approch to asteroid from heliocentric space Landmark Navigation in proximity operation around asteroid Autolanding in zero gravity field Redundancy against malfunctions in long flight Information and Knowledge on C and S-type asteroids 9 Back-up Ion Thruster Assembly (ITA) Thruster 4 units including 1 stand-by 3 units simultaneous operation System thrust 5 - 30 mN System Power 250 – 1,200 W Specific Imp. 2,600 – 3,000 sec Ion Prod. Cost < 250 eV Lifetime > 18,000 hours Gimbal +/-5 deg Xe loading < 73 kg Dry weight < 70 kg Impactor � high speed debris � high speed ejecta � low speed ejecta separation explosion � Separation mechanism � Impactor � 1999 JU3 � ��� 12 Impactor experiment half size case explosion trajectory 13 impact! .
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