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 Hiten Moon LUNAR-A SELENE2 SLIM 1985 Sakigake Suisei Comet Halley Moon 1990 1998 Hayabusa Asteroid Itokawa Nozomi Mars IKAROS Kaguya Akatsuki Moon 2003 Venus 2007 BepiColombo 2010 2014 Hayabusa2 Mercury Asteroid Ryugu PROCYON 2
Starting Point 1985 Japan's Asteroid Explorations Past, Present, and Future Hayabusa 2003-2010 Hayabusa2 2014-2020 Phaethon (Geminids) to NEO? S-type C-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 Next: Trojan mission? Many New technologies Hayabusa2 Impactor system Ka-band communicaiton 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 4.6 billion years ago... Molecular cloud Proto solar system disk The science of Itokawa Mineralogy, Topography, Structure, Regolith, Meteoroid In addition to the science of Itokawa... Organic matter, H 2 O Solar system HAYABUSA Itokawa Space weathering, Impact, Cosmic ray, Solar wind Boulder Earth Ryugu 5
Hayabusa 1&2 will solve the "Missing Zone" Molecular cloud core 4.6 billion years ago Protoplanetary disk Condensation melt and evaporation of dust Adhesion/mixture Formation of CAI* Formation of Chondrule *CAI : Calciumaluminium-rich inclusion Formation of planetesimal History of Asteroid Scattered to outside Fall to center Collision and growth of planetesimal Formation environment and composition of parent asteroid Missing Formation of parent asteroid Collisional destruction and reaccumulation metamorphism and differentiation by internal heating Zone Asteroid Meteorite Orbital evolution Rubble pile Present Heating space weathering Near earth asteroid Planetesimal Dust (mineral, H 2 O, Organic mater) Catastrophic disruption Differentiation metal core 6
History of Hayabusa and Hayabusa2 Idea for sample return began in1985 Year Serious troubles in Hayabusa 2000 01 02 03 04 05 06 07 08 09 10 11 12 13 14 15 16 Now MUSES-C launch project Started in 1996 Post MUSES-C Post Hayabusa Hayabusa Hayabusa Mk2 Marco Polo Sample Analysis Earth return Post Haybusa2 Hyabusa2 Initial proposal in 2006 Copy of Hayabusa but modified Target : C-type asteroid 1999 JU3 Launch: 2010 Preparation Project Op. Launch New proposal in 2009 Modified Hayabusa adding new challenges Target : C-type asteroid 1999 JU3 (Ryugu) Launch: 2014 7
Objectives : Hayabusa vs Hayabusa-2 Hayabusa Technological demonstrator Round-trip to asteroid Sample return Engineering Ion engine Autonomous navigation Sample collection Reentry capsule Science : Origin and evolution of the solar system Remote sensing observation Sample analysis Hayabusa2 1. Science Origin and evolution of the solar system Organic matter, H 2 O 2. Engineering Technology : more reliable and robust New challenge : ex) impactor 3. Exploration Extend the area that human can reach Spaceguard, Resources, Research for manned mission, etc. S-type Asteroid C-type Asteroid 8
Mission Scenario of Hayabusa Observations, sampling Launch 9 May 2003 Earth Swingby 19 May 2004 Asteroid Arrival 12 Sept. 2005 Earth Return 13 June 2010 Serious troubles 9
2003.05.09 Engineering of Hayabusa 2004.05.19 2005.09.12 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 Western Side Bottom 12
Summary of Science Results by Remote Sensing l Mass l Shape, size, spin l Density Mass:(3.51 ± 0.105) x 10 10 kg Volume = (1.84 ± 0.092) x 10 7 m 3 Bulk Density:1.9 ± 0.13 g/cm 3 Macro-porosity = 40% l Albedo l Material l Structure l etc. Ordinary chondrite Olivine Pyroxene and Olivine Pyroxene Rubble pile 13
Scientific Results from Sample Initial Analysis LL chondrite LL4 (~600 o C) LL5/6 (~800 o C) planetesimal Catastrophic impact Formation of Itokawa parental body (>20 km) Escape rate (~10 cm/my) Thermal metamorphism (<4.562 Ba) Micrometeoroids Solar wind Galactic cosmic ray Reaccumulation Itokawa formation Rubble pile asteroid Grain motion (150y~3My) Space weathering 100 m 14
Science Publications 2 June 2006 26 August 2011 -Rubble-pile structure -Near-infrared spectral results -Surface morphologies -Local topography -Shape, physical properties - A Direct Link Between S-Type Asteroids and Ordinary Chondrites - Oxygen Isotopic Compositions - Neutron Activation Analysis - Origin and Evolution of Itokawa Regolith - Irradiation History of Itokawa Regolith Space 15
Launch Mission Scenario of Hayabusa2 Arrival at Ryugu 03 Dec. 2015 03 Dec. 2014 June-July 2018 Earth swing-by The spacecraft observes the asteroid, releases the small rovers and the lander, and executes multiple samplings. 2019 New Experiment Sample analysis 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 (DCAM3) Solar Array Panel X-band HGA X-band LGA X-band MGA Ka-band HGA ONC-T LIDAR NIRS3 TI R Science Instruments Star Trackers Near Infrared Spectrometer (NIRS3) Reentry Capsule Ion Engine RCS thrusters 12 Sampler Horn LIDAR ONC-W2 ONC-T, ONC-W1 Small Lander and Rovers MASCOT by DLR and CNES MINERVA-II II-1A II-1B II-2 II-1 : by JAXA MINERVA-II Team II-2 : by Tohoku Univ. & MINERVA-II consortium MASCOT Lander MINERVA-II Rovers Small Carry-on Impactor (SCI) Target Markers 5 Size : 1m 1.6m 1.25m (body) Mass: 600kg (Wet) Thermal Infrared Imager (TIR) 17
Remote Sensing Instruments of Hayabusa2 Optical Navigation Camera (ONC) filter set was changed (ONC-T : 6.35deg 2, ONC-W : 65.24deg 2 ) Light Detection and Ranging (LIDAR) adapted to low albedo of C-type (Range : 30m 25km) Near Infrared Spectrometer (NIRS3) absorption by H 2 O 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 (b) 2Horizontal Escape 3Vertical Escape Impact Observation Detonation & Impact 4DCAM3 Separation 1999 JU3 (c) 1999JU3 5Detonation & Impact (a) high speed debris (b) high speed ejecta (c) low speed ejecta 6Return to HP 20
Trajectory Design for the way to Ryugu Hayabusa2 trajectory Ryugu orbit Ryugu arrival (June-July 2018) Sun Launch (Dec. 3, 2014) Earth orbit 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 Fully deployed SMP PAF interface Moon taken at 300,000km distance. 1 st, 2 nd, 3 rd tracking passes Three axis attitude stabilization established Sampler horn deployed Ion engine gimbal launch lock released Moon photo taken by ONC-W2, benefit for scientific calibration purpose 22
Date 2014 Dec. 3-6 LEOP Dec. 7-8 Dec. 9 Dec. 10 Dec. 11 Dec. 12-15 Dec. 16 Dec. 17 Dec. 18 Dec. 19-22 Dec. 23-26 Commissioning Phase Event XMGA pointing calibration, X-band COMM characterization/testing EPS/BAT testing NIRS3 health check TIR/DCAM3/ONC health check AOCS characterization/testing MINRVA-II/MASCOT health check CPSL/SCI health check XHGA pointing calibration, IES turn-on preparation IES baking 2015 Dec. 27-Jan. 4 Precision OD, DDOR testing Jan. 5-10 Jan. 11 Jan. 12-15 Jan. 16 Jan. 19-20 Jan. 23 Jan. 24-Mar. 2 IES testing (ITR-A/B/C/D, single-thruster-at-once operation) Ka-band COMM characterization/testing, KaHGA pointing calibration IES turn-on preparation IES testing (<A+C>,<C+D>,<A+D>,<A+C>, dual thrusters operation) IES testing (<A+C+D>, triple thrusters operation) IES 24hr continuous operation demonstration (<A+D>) LIDAR/LRF/FLA health check IES-AOCS coordinated operation testing SRP dynamics characterization / Solar Sail Mode demonstration DSN GDS/CAN/MAD DSN MAD DSN MAD DSN GDS/CAN/MAD DSN GDS/CAN/MAD DSN MAD Mar. 2 Commissioning phase completed 23
Communication System of Hayabusa2 Ka-band High Gain Antenna (Ka-HGA) X-band Low Gain Antenna (X-LGA-A) 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) Bit rate : 8bps 32Kbps X-band Low Gain Antenna (X-LGA-B) X-band Low Gain Antenna (X-LGA-C) 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
Approach to the Earth 2015/11/26 TCM2 2015/12/1 TCM3 cancel 2015/12/3 the closest point 2015/11/3 TCM1 Earth Swing-by 2015/11/10-13 TIR Obs. 2015/11/26 ONC-T, TIR, NIRS3 Obs. 2015/12/3 ONC-W2 Obs Eclipse (20min) Orbit near the earth North pole Eclipse starts (18:58JST) Orbit of Moon 2015/12/19 LIDAR Experiment Sun direction 2015/12/4 TIR and ONC-T Obs. 2015/12/22 End of Swingby Operation Closest (19:08:07JST) Eclipse ends (19:18JST) Sun direction (Time is in JST) 26
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, 2015. The viewing angle is at about 60 degrees. 27
ONC-T Operations of Science Instruments TIR Australia Color image Plants exist reasion Thermal Image NIRS3 wave length (µm) data NO Earth Moon Absorption by water on the earth strong weak signal level LIDAR 受信レベル Signal Level (mv) LIDAR 1-way link from the earth to the spacecraft Dec. 19, 2015 Distance 6.70 million km (= 0.045AU) 28
Optical Link Experiment by LIDAR Dec. 19, 2015 Mt. Stromlo station at SERC (Space Environment Research Centre Australia) in Australia transmitted laser light towards Hayabusa2. Hayabusa2 successfully received the beam using the onboard LIDAR at the distance of 6,700,000 km from Earth. 29
Operations and Experiments after Earth Swing-by 2016 Jan. - April Southern hemisphere operation March 22 May 21 1st long-term IES operation after Earth Swing-by : 798 h May 24 June 9 Mars Observation (by ONC-T, NIRS3, TIR) June 22, 23 Experiment of uplink transfer June 29 July 8 Experiments of Ka-band communication : Dec. May 2017? 2nd long-term IES operation Nov. 2017 - June 2018? 3rd long-term IES operation 30
Experiment of Uplink Transfer The experiment of uplink transfer was done by using DSN stations on June 22, 23, 2016 and it was successful. This is the first experiment for Japanese spacecraft. Conventional : Station A Uplink stops for a while Station B Uplink Transfer: Uplink continues Uplink continues Station A Station A Station B Station B 31
Experiments of Ka band June 26 July 3, 2016 : Ka-band communication test by using Goldstone Station (NASA DSN) was successful in the distance of about 50 million km. July 1, 2, 2016 : DDOR experiment by using Ka-band was successful. (Stations : NASA-Goldstone, ESA-Malargüe) July 5 8, 2016 : Ka-band compatibility test by using Malargüe Station (ESA) was successful. DDOR: Delta Differential One-way Range QSO 32
Rela ve reflec on rate Target Asteroid : 1999 JU3 = Ryugu Asteroid (162173) 1999 JU3 Discovered in May 1999 by LINEAR Team Shape : almost spherical Size : 900 m Rotation period: 7.6 h Pole orientation (320, -40 ) :current estimate Albedo : 0.05 Type : Cg Spectrum Wave length (µm) (Data by Viras 2008, Sugita+ 2012, Abe+ 2008) Differen al Magnitude Differential Magnitude 1.8 1.7 1.6 1.5 1.4 1.3 Light curve Model Tp=7.625 hr assumed 1.2 0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1 Rotational phase Rota onal phase (by Kim, Choi, Moon et al. A&A 550, L11, 2013) Orbit Shape (by T. Müller) 33
Science for Wide Scale Range log10 L [m] +3 +2 +1 0-1 -2-3 -4-5 -6-7 -8-9 On-site remote sensing Observations on the surface Return sample analyses ONC (T, W1, W2) LIDAR NIRS3 TIR SCI DCAM3 Sampler MASCOT MINERVA-II (1A, 1B, 2) Ground based facilities 34
International Cooperation Structure of Hayabusa2 USA NASA Europe DLR CNES OSIRIS-REx (101955) Bennu Australia SLASO/DIISR DoD/AOSG AQIS/AC 35
Solar Power Sail System for Trojan Mission 50m Ion engines from Osamu MORI Trojan asteroid (~5.2 AU) Earth (1AU) Sun Mainbelt (~ 3AU) Jupiter (~5.2 AU) The spacecraft is supposed to be launched in early 2020s and make a world s first trip to Trojan asteroid using Earth and Jupiter gravity assist. After arriving at Trojan asteroid, the lander is separated from solar power sail-craft to collect surface and underground samples and perform in-situ analysis. The lander delivers samples to solar power sail-craft for sample return mission (optional). <Event> 1) Launch 2) Earth swing-by 3) Jupiter swing-by 4) Arrival at Trojan asteroid 5) Departure from Trojan asteroid 6) Jupiter swing-by 7) Return to Earth optional 36
Summary Hayabusa and Hayabusa2 are challenging missions not only for science but also for space technologies. Hayabusa2, which was launched on Dec. 3, 2014, are now on the way to the target asteroid Ryugu, and the operations are ongoing smoothly. Asteroids are important in various aspects, and we would like to extend our missions to other objects. Science Spaceguared Resource Manned mission Engineering Culture Asteroids are important! 37