Hayabusa and Hayabusa2 - Challenges for Sample Return from Asteroids

Home , Akatsuki (spacecraft), Sakigake, Suisei (spacecraft)

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 parent asteroid and evaporation of Formation of planetesimal Fall to center Molecular cloud core dust Meteorite Protoplanetary disk Collisional Collision and growth Adhesion/mixture destruction and re- of planetesimal accumulation Asteroid Formation Heating Formation of CAI* environment and metamorphism and space weathering composition of differentiation by Formation of Near earth

internal heating asteroid

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

(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 (,,,, dual thrusters operation) Jan. 16 IES testing (, triple thrusters operation) Jan. 19-20 IES 24hr continuous operation demonstration () 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

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. 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 Operations of Science Instruments ONC-T TIR Australia

Color image Plants exist reasion Thermal Image

NIRS3 LIDAR 1-way link from the earth to the spacecraft Earth Moon strong (mV) ルベルレベ信レ signal level wave length ( µm ) 受信

data NO weak LIDAR Signal Level (mV) Absorption by water on the earth LIDAR

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

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 :

Uplink stops for a Station A while Station B

Uplink Transfer：

Uplink Uplink continues continues Station A Station A Station B Station B

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： QSO Delta Differential One-way Range

32 Target Asteroid : 1999 JU3 = Ryugu Orbit 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 Light curve Shape 1.8

Model Tp=7.625 hr assumed 1.7

1.6

1.5

1.4 Differential Magnitude

1.3 Rela�ve reﬂec�on rate Diﬀeren�al Magnitude µ 1.2 Wave length ( m) 0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1 Rotational phase (Data by Viras 2008, Sugita+ Rota�onal phase 2012, Abe+ 2008) (by Kim, Choi, Moon et al. (by T. Müller) A&A 550, L11, 2013)

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 MASCOT SCI MINERVA-II (1A, 1B, 2) DCAM3 Sampler Ground based facilities

34 International Cooperation Structure of Hayabusa2

USA

NASA

Europe DLR CNES

OSIRIS-REx Australia SLASO/DIISR DoD/AOSG

(101955) Bennu AQIS/AC

35 Solar Power Sail System for Trojan Mission 50m from Osamu MORI Trojan asteroid (~5.2 AU)

Ion engines

Earth

(1AU) Sun

Mainbelt (~ 3AU) Jupiter (~5.2 AU) R 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. R 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. R The lander delivers samples to solar power sail-craft for sample return mission (optional). 1) Launch 2) Earth swing-by 5) Departure from Trojan asteroid 3) Jupiter swing-by 6) Jupiter swing-by optional 4) Arrival at Trojan asteroid 7) Return to Earth

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!