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Hayabusa and Hayabusa2 - Challenges for Sample Return from Asteroids

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Hayabusa and Hayabusa2 - Challenges for Sample Return from Asteroids Hayabusa and Hayabusa2 - Challenges for Sample Return from Asteroids - 14th BroadSky Workshop : Opening Up Ways to Deep Space Cleveland, Ohio, USA October 18, 2016 Makoto Yoshikawa (JAXA) Lunar and Planetary Missions of Japan ×LUNAR-A ×SELENE2 SLIM Hiten Moon ×Nozomi 1985 IKAROS Moon Sakigake Kaguya 1990 Mars Akatsuki 1998 Moon Suisei 2003 Hayabusa Venus 2007 BepiColombo 2010 2014 Comet Halley Asteroid Itokawa Hayabusa2 Mercury Asteroid Ryugu PROCYON 2 Japan's Asteroid Explorations Past, Present, and Future Starting Point Hayabusa Hayabusa2 1985 2003-2010 2014-2020 Phaethon （Geminids） to NEO ? C-type S-type D-type to Trojans ? 3 Technology of Sample Return New technology for asteroid sample return mission Hayabusa Ion engine Autonomous navigation Sample collection system Re-entry capsule Hayabusa2 Next: Impactor system Trojan mission? Ka-band communicaiton Many New technologies 4 Science of Sample Return Origin and evolution of the solar system • Planetesimal formation : Accumulation and destruction • Evolution from planetesimals to asteroids • Initial material : Minerals, water, organic matters • Material circulation in the early solar system • Relation between asteroids and meteorites The science of Itokawa In addition to the 4.6 billion years ago... science of Itokawa... Molecular cloud Mineralogy, Topography, Structure, Regolith, Meteoroid Organic matter, H O Proto solar system disk 2 Itokawa Boulder Ryugu HAYABUSA Space weathering, Impact, Cosmic ray, Earth Solar system Solar wind 5 Hayabusa 1&2 will solve the "Missing Zone" History of Asteroid 4.6 billion years ago Present Condensation melt Scattered to outside Formation of and evaporation of Formation of Fall to center Molecular cloud core dust Meteorite Protoplanetary Collisional Collision and growth Adhesion/mixture destruction and re- of planetesimal accumulation Asteroid Formation Heating Formation of CAI* parent asteroid planetesimal environment and metamorphism and space weathering composition of differentiation by Formation of Near earth internal heating asteroid disk parent asteroid Chondrule Orbital evolution Missing Zone *CAI : Calcium- aluminium-rich inclusion Rubble pile Planetesimal metal Dust Catastrophic (mineral, H O, Organic mater) core 2 disruption Differentiation 6 History of Hayabusa and Hayabusa2 Idea for sample Serious troubles return began in1985 in Hayabusa Now Year 2000 01 02 03 04 05 06 07 08 09 10 11 12 13 14 15 16 MUSES-C Hayabusa Sample Analysis ▲ ▲ launch Earth return project Started Hayabusa Mk2 Post Post MUSES-C Post Hayabusa in 1996 Marco Polo Haybusa2 Hyabusa2 Preparation Project Op. ▲ Launch Initial proposal in 2006 New proposal in 2009 Copy of Hayabusa but modified Modified Hayabusa adding new challenges Target : C-type asteroid 1999 JU3 Target : C-type asteroid 1999 JU3 (Ryugu) Launch: 2010 Launch: 2014 7 Objectives : Hayabusa vs Hayabusa-2 Hayabusa Hayabusa2 Technological demonstrator 1. Science Round-trip to asteroid Origin and evolution of the solar system Sample return Organic matter, H2O Engineering 2. Engineering Ion engine Technology : more reliable and robust Autonomous navigation New challenge : ex) impactor Sample collection Reentry capsule 3. Exploration Extend the area that human can reach Science : Spaceguard, Resources, Research for Origin and evolution of the manned mission, etc. solar system Remote sensing observation Sample analysis C-type Asteroid S-type Asteroid 8 Mission Scenario of Hayabusa Observations, sampling Earth Swingby Launch 19 May 2004 9 May 2003 Asteroid Arrival 12 Sept. 2005 Earth Return Serious 13 June 2010 troubles 9 Engineering of Hayabusa 2005.09.12 2003.05.09 2004.05.19 2010.06.13 10 Capsule and Sample Capsule (June 14, 2010) Instrument Module Container Confirmation of Itokawa grain Small grain Inside the container 11 Images of Itokawa Eastern Side Head Bottom Western Side 1212 Summary of Science Results by Remote Sensing l Mass Mass：(3.51 ± 0.105) x 1010 kg� Volume = (1.84 ± 0.092) x 107 m3 Bulk Density：1.9 ± 0.13 g/cm3 l Shape, size, spin Macro-porosity = 40% l Density l Albedo l Ordinary Material chondrite Pyroxene Olivine l Structure Pyroxene and Olivine l etc. Rubble pile 13 Scientific Results from Sample Initial Analysis LL chondrite LL4 (~600oC) LL5/6 (~800oC) Catastrophic planetesimal impact Formation of Thermal Itokawa parental metamorphism body (>20 km) （<4.562 Ba） Escape rate Solar wind (~10 cm/My) Micro- Galactic Re- meteoroids cosmic ray accumulation Itokawa formation Rubble pile asteroid 100 m Grain motion Space (150y~3My） weathering 14 Science Publications 2 June 2006 26 August 2011 -Rubble-pile structure - A Direct Link Between S-Type Asteroids and -Near-infrared spectral results Ordinary Chondrites -Surface morphologies - Oxygen Isotopic Compositions -Local topography - Neutron Activation Analysis -Shape, physical properties - Origin and Evolution of Itokawa Regolith - Irradiation History of Itokawa Regolith Space 15 Mission Scenario of Hayabusa2 Launch Arrival at Ryugu 03 Dec. 2015 03 Dec. 2014 June-July 2018 The spacecraft observes the asteroid, releases the small rovers and the lander, Earth swing-by and executes multiple samplings. Sample analysis 2019 New Experiment Earth Return Nov.-Dec. 2020 Nov.-Dec. 2019 : Departure The impactor collides to the surface of the asteroid. The sample will be obtained from the newly created crater. 16 Hayabusa2 Spacecraft Deployable Camera X-band LGA (DCAM3) X-band HGA Solar Array Panel X-band MGA Ka-band HGA ONC-T LIDAR NIRS3 TI R Science Instruments Star Trackers Ion Engine Near Infrared Spectrometer (NIRS3) RCS thrusters ×12 Reentry Capsule Sampler Horn LIDAR ONC-W2 ONC-T, ONC-W1 Small Lander and Rovers MASCOT MINERVA-II MASCOT Lander Thermal Infrared Imager (TIR) MINERVA-II Rovers II-1A II-1B II-2 Small Carry-on Impactor (SCI) by DLR and CNES II-1 : by JAXA MINERVA-II Team II-2 : by Tohoku Univ. & MINERVA-II Target Markers ×5 consortium Size ： 1m×1.6m×1.25m (body) Mass： 600kg (Wet) 17 Remote Sensing Instruments of Hayabusa2 Optical Navigation Camera (ONC) filter set was changed (ONC-T : 6.35deg2, ONC-W : 65.24deg2) Light Detection and Ranging (LIDAR) adapted to low albedo of C-type (Range : 30m – 25km) Near Infrared Spectrometer (NIRS3) absorption by H2O Wave length : 1.8 – 3.2 µm Thermal Infrared Imager (TIR) Thermal radiation Wave length : 8 – 12 µm 18 Sampling Operation Sequence 19 Artificial Crater Generation Operation separation explosion (a) ①SCI Separation ②Horizontal Escape (b) ③Vertical Escape Impact Observation ④DCAM3 Separation Detonation & Impact (c) 1999JU3 1999 JU3 ⑤Detonation & Impact (a) high speed debris ⑥Return to HP (b) high speed ejecta (c) low speed ejecta 20 Trajectory Design for the way to Ryugu Hayabusa2 trajectory Ryugu orbit Ryugu arrival Earth orbit Sun (June-July 2018) Launch (Dec. 3, 2014) Earth swing-by (Dec. 3, 2015) 21 Launch and Initial Operations 2014/12/3 04:22:04 Launch 06:09:25 Separation 06:14:53 SAP deployment 06:16:31 Sun acquisition maneuver 09:06:51 Single spin established 1st, 2nd, 3rd tracking passes PAF interface Three axis attitude stabilization established Sampler horn deployed Fully deployed SMP Ion engine gimbal launch lock released Moon photo taken by ONC-W2, benefit Moon taken at 300,000km distance. for scientific calibration purpose 22 Commissioning Phase Date Event 2014 Dec. 3-6 LEOP DSN GDS/CAN/MAD Dec. 7-8 XMGA pointing calibration, X-band COMM characterization/testing Dec. 9 EPS/BAT testing Dec. 10 NIRS3 health check Dec. 11 TIR/DCAM3/ONC health check Dec. 12-15 AOCS characterization/testing Dec. 16 MINRVA-II/MASCOT health check Dec. 17 CPSL/SCI health check Dec. 18 XHGA pointing calibration, IES turn-on preparation Dec. 19-22 IES baking DSN MAD Dec. 23-26 IES testing (ITR-A/B/C/D, single-thruster-at-once operation) DSN MAD 2015 Dec. 27-Jan. 4 Precision OD, DDOR testing DSN GDS/CAN/MAD Jan. 5-10 Ka-band COMM characterization/testing, KaHGA pointing calibration DSN GDS/CAN/MAD Jan. 11 IES turn-on preparation Jan. 12-15 IES testing (<A+C>,<C+D>,<A+D>,<A+C>, dual thrusters operation) Jan. 16 IES testing (<A+C+D>, triple thrusters operation) Jan. 19-20 IES 24hr continuous operation demonstration (<A+D>) DSN MAD Jan. 23 LIDAR/LRF/FLA health check Jan. 24-Mar. 2 IES-AOCS coordinated operation testing SRP dynamics characterization / “Solar Sail Mode” demonstration Mar. 2 Commissioning phase completed 23 Communication System of Hayabusa2 Ｘ-band Low Gain Antenna (X-LGA-A) Ka-band High Gain Antenna (Ka-HGA) X-band High Gain Antenna (X-HGA) X-band Middle Gain Antenna (X-MGA) X-band : Uplink : CMD, RNG (7.2GHz) Downlink : TLM, RNG (8.4GHz) Ka-band: Downlink : TLM, RNG (32GHz) X-band Low Gain Antenna (X-LGA-C) Bit rate : 8bps〜32Kbps X-band Low Gain Antenna (X-LGA-B) 24 Regular Operation Phase to Earth Swing-by 2015 Mar. 3 Regular Operation Phase started Mar. 3-21 First IES Operation in EDVEGA Phase : 409 hours Mar. 27 – May 7 Attitude control in the solar sail mode (One RW operation) May 12-13 Three IES operation for 24hours June 2-6 Second IES Operation in EDVEGA Phase : 102 hours June 9- The solar sail mode operation Sep. 1,2 TCM by IES - mid Sep. Precise OD Oct.-Dec. Precise TCM by RCS Dec. 3 Earth swingby Dec. 2015-Apr. 2016 Post-Swingby southern hemisphere operation 25 Earth Swing-by Approach to the Earth 2015/11/3 Orbit near the earth TCM1 North pole 2015/11/10-13 TIR Obs. 2015/11/26 2015/11/26 Eclipse starts TCM2 ONC-T, TIR, NIRS3 Obs. (18:58JST) 2015/12/1 TCM3―cancel 2015/12/3 2015/12/3 ONC-W2 Obs Eclipse the closest point (20min) Sun direction Closest Orbit of Moon 2015/12/4 (19:08:07JST) TIR and ONC-T Obs. Sun direction Eclipse ends (19:18JST) 2015/12/22 End of Swingby Operation 2015/12/19 （Time is in JST） LIDAR Experiment 26 The Earth images at swing-by (animation) The images of the Earth taken by ONC- W2.
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