Hayabusa and Hayabusa2 - Challenges for Sample Return from Asteroids -

Makoto Yoshikawa (JAXA)

Cleveland, Ohio, USA October 18, 2016

14th BroadSky Workshop : Opening Up Ways to Deep Space

Lunar and Planetary Missions of Japan

Sakigake

Suisei

1985

Hiten

1990

2007

Kaguya

×Nozomi

2003

2010

1998

IKAROS

Akatsuki

Hayabusa

Hayabusa2

×LUNAR-A

2014

Comet Halley

Moon

Moon

Moon

Mars

Venus

Asteroid Itokawa Asteroid Ryugu

PROCYON

SLIM ×SELENE2

BepiColombo

Mercury

2

Starting Point 1985

Japan's Asteroid Explorations Past, Present, and Future

Hayabusa 2003-2010

Hayabusa2 2014-2020

to Trojans ? S-type

C-type D-type

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Phaethon （（Geminids））

to NEO ?

Technology of Sample Return New technology for asteroid sample return mission

 Ion engine  Autonomous navigation  Sample collection system  Re-entry capsule

Hayabusa

 Impactor system  Ka-band communicaiton

Hayabusa2

 Many New technologies

Next: Trojan mission?

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Science of Sample Return Origin and evolution of the solar system

Ryugu Itokawa

In addition to the science of Itokawa...

Organic matter, 　　 　　　　　　H2O

Solar system

Proto solar system disk

HAYABUSA

Earth

The science of Itokawa

Mineralogy, Topography, Structure, Regolith, Meteoroid

Space weathering, Impact, Cosmic ray, Solar wind

Boulder

Molecular cloud 4.6 billion years ago...

•  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

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Hayabusa 1&2 will solve the "Missing Zone"

Formation of CAI*

Formation of Chondrule

Present Condensation melt and evaporation of dust

Orbital evolution

Molecular cloud core

Adhesion/mixture

Near earth asteroid

Protoplanetary disk

metamorphism and differentiation by internal heating

Formation of planetesim

al

Meteorite

Collision and growth of planetesimal

Scattered to outside Fall to center

Asteroid

Collisional destruction and re-accumulation

Heating space weathering

Formation of parent asteroid

Missing Zone

Formation environment and composition of parent asteroid

4.6 billion years ago

*CAI : Calcium-aluminium-rich inclusion

Dust (mineral, H2O, Organic mater)

Planetesimal Catastrophic disruption

Rubble pile

Differentiation

History of Asteroid

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metal core

Idea for sample return began in1985

History of Hayabusa and Hayabusa2

Year

▲ Launch

　　　　　　 Hayabusa ▲

launch

Now

Project

Serious troubles in Hayabusa

Post Haybusa2

MUSES-C Sample Analysis

project Started in 1996 Post MUSES-C Post Hayabusa

Preparation

Hayabusa Mk2 Marco Polo

Initial proposal in 2006 Copy of Hayabusa but modified Target : C-type asteroid 1999 JU3 Launch: 2010

New proposal in 2009 Modified Hayabusa adding new challenges Target : C-type asteroid 1999 JU3 (Ryugu) Launch: 2014

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▲ Earth return

Op. Hyabusa2

2000 01 02 03 04 05 06 07 08 09 10 11 12 13 14 15 16

Objectives : Hayabusa vs Hayabusa-2

1. Science   Origin and evolution of the solar system   Organic matter, H2O

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.

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

Hayabusa Hayabusa2

C-type Asteroid

S-type Asteroid

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Mission Scenario of Hayabusa

Launch 9 May 2003

Earth Swingby 19 May 2004 Asteroid Arrival

12 Sept. 2005

Observations, sampling

Earth Return 13 June 2010

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Serious troubles

Engineering of Hayabusa 2003.05.09

2005.09.12

2010.06.13

2004.05.19

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Instrument Module Container

Capsule and Sample

Capsule (June 14, 2010)

Inside the container Small grain Confirmation of Itokawa grain

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Images of Itokawa

Eastern Side

Western Side

Head

Bottom

1122 12

Summary of Science Results by Remote Sensing

l Mass

l Shape, size, spin

l Density

l Albedo

l Material

l Structure

l etc.

Pyroxene Olivine

Pyroxene and Olivine

Mass：：(3.51 ± 0.105) x 1010 kg�� Volume = (1.84 ± 0.092) x 107 m3 Bulk Density：：1.9 ± 0.13 g/cm3

Macro-porosity = 40%

Ordinary chondrite

Rubble pile

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Formation of Itokawa parental

body (>20 km)

Thermal metamorphism （（<4.562 Ba））

Catastrophic impact

Itokawa formation Rubble pile asteroid

planetesimal

Solar wind

Space weathering

Galactic cosmic ray

Micro-meteoroids

Escape rate (~10 cm/My)

Grain motion (150y~3My））

Scientific Results from Sample Initial Analysis

100 m

LL chondrite LL5/6 (~800oC) LL4 (~600oC)

Re- accumulation

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Science Publications 2 June 2006 26 August 2011

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- 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

-Rubble-pile structure -Near-infrared spectral results -Surface morphologies -Local topography -Shape, physical properties

The impactor collides to the surface of the asteroid.

The sample will be obtained from the newly created crater.

Launch

The spacecraft observes the asteroid, releases the small rovers and the lander, and executes multiple samplings.

Earth Return

Sample analysis

Mission Scenario of Hayabusa2

03 Dec. 2014 June-July 2018

2019

Nov.-Dec. 2020

New Experiment

Nov.-Dec. 2019 : Departure

Arrival at Ryugu 03 Dec. 2015

Earth swing-by

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X-band MGA

X-band HGA

Ka-band HGA

Star Trackers

Reentry Capsule

Sampler Horn

Solar Array Panel

Near Infrared Spectrometer (NIRS3)

LIDAR

X-band LGA Deployable Camera (DCAM3)

ONC-W2

Hayabusa2 Spacecraft

Size ：： 1m×1.6m×1.25m (body) Mass：： 600kg (Wet)

Ion Engine

Small Carry-on Impactor (SCI)

MASCOT Lander

MINERVA-II Rovers

Target Markers ×5

RCS thrusters ×12

Thermal Infrared Imager (TIR)

ONC-T, ONC-W1

ONC-T LIDAR NIRS3 TIR

Science Instruments

II-1A II-1B

by DLR and CNES

MASCOT

II-2

II-2 : by Tohoku Univ. & MINERVA-II consortium

II-1 : by JAXA MINERVA-II Team

MINERVA-II

Small Lander and Rovers

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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

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Sampling Operation Sequence

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1999JU3

Artificial Crater Generation Operation

①SCI Separation

②Horizontal Escape ③Vertical Escape

④DCAM3 Separation

⑤Detonation & Impact

⑥Return to HP

Impact Observation

Detonation & Impact

1999 JU3

explosion

separation

(a) high speed debris (b) high speed ejecta (c) low speed ejecta

(a)

(b)

(c)

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Trajectory Design for the way to Ryugu

Sun

Launch (Dec. 3, 2014)

Earth swing-by (Dec. 3, 2015)

Ryugu arrival (June-July 2018)

Ryugu orbit

Hayabusa2 trajectory

Earth orbit

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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  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

PAF interface

Fully deployed SMP

Moon taken at 300,000km distance.

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Commissioning Phase Date Event

2014 Dec. 3-6 LEOP

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

Dec. 23-26 IES testing (ITR-A/B/C/D, single-thruster-at-once operation)

2015 Dec. 27-Jan. 4 Precision OD, DDOR testing

Jan. 5-10 Ka-band COMM characterization/testing, KaHGA pointing calibration

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>)

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

DSN GDS/CAN/MAD

DSN MAD

DSN MAD

DSN GDS/CAN/MAD

DSN GDS/CAN/MAD

DSN MAD

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Communication System of Hayabusa2

X-band Middle Gain Antenna (X-MGA)

X-band High Gain Antenna (X-HGA)

Ka-band High Gain Antenna (Ka-HGA)

Ｘ-band Low Gain Antenna (X-LGA-A)

X-band Low Gain Antenna (X-LGA-C)

X-band Low Gain Antenna (X-LGA-B)

X-band :  Uplink : CMD, RNG (7.2GHz)  Downlink : TLM, RNG (8.4GHz)

Ka-band:  Downlink : TLM, RNG (32GHz)

Bit rate : 8bps〜32Kbps

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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

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 Approach to the Earth

Earth Swing-by

Sun direction

2015/11/3 TCM1

2015/11/26 TCM2

2015/12/1 TCM3―cancel

Orbit of Moon

2015/11/10-13 TIR Obs.

2015/11/26 ONC-T, TIR, NIRS3 Obs.

2015/12/3 ONC-W2 Obs 2015/12/3

the closest point

2015/12/4 TIR and ONC-T Obs.

2015/12/22 End of Swingby Operation

Eclipse (20min)

Closest (19:08:07JST)

Sun direction

North pole

Eclipse starts (18:58JST)

Eclipse ends (19:18JST)

Orbit near the earth

（Time is in JST）

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2015/12/19 LIDAR Experiment

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.

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Operations of Science Instruments ONC-T TIR

NIRS3

Plants exist reasion Color image Thermal Image

Australia

LID

AR

受受信信

レレベベ

ルル (m

V)

Dec. 19, 2015　Distance 6.70 million km　(= 0.045AU)

Absorption by water on the earth

1-way link from the earth to the spacecraft Earth Moon strong

weak

wav

e le

ngth

(µm

)

sign

al le

vel

data NO LI

DA

R S

igna

l Lev

el (m

V)

LIDAR

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Optical Link Experiment by LIDAR

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.

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Dec. 19, 2015

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

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 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.

Station A Station B

Station A Station A Station B Station B

Conventional :

Uplink Transfer：：

Uplink stops for a while

Uplink continues

Uplink continues

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 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

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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

(by Kim, Choi, Moon et al. A&A 550, L11, 2013)

(Data by Viras 2008, Sugita+ 2012, Abe+ 2008)

Orbit

Shape Light curve Spectrum

Wave  length  (µm)

Rela�ve  reflec�on

 rate  

Tp=7.625 hr assumedModel

1.2

1.3

1.4

1.5

1.6

1.7

1.8

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

Diff

eren

tial M

agni

tude

Rotational phaseRota�onal  phase

Diffe

ren�

al  M

agnitude

(by T. Müller)

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+3 +2 +1 0 -1 -2 -3 -4 -5 -6 -7 -8 -9 log10 L [m]

Return sample analyses

On-site remote sensing

Observations on the surface

Science for Wide Scale Range

ONC (T, W1, W2) LIDAR NIRS3 TIR MASCOT

MINERVA-II (1A, 1B, 2)

Ground based facilities

SCI DCAM3 Sampler

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Europe

USA

Australia

NASA  

DLR CNES

SLASO/DIISR DoD/AOSG AQIS/AC

International Cooperation Structure of Hayabusa2

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(101955) Bennu

OSIRIS-REx

Solar Power Sail System for Trojan Mission

  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).

Sun

Mainbelt  (~  3AU)  

Earth (1AU)

Trojan asteroid (~5.2 AU)

Jupiter  (~5.2  AU)  

5) Departure from Trojan asteroid 6) Jupiter swing-by 7) Return to Earth

optional

<Event> 1) Launch 2) Earth swing-by 3) Jupiter swing-by 4) Arrival at Trojan asteroid

Ion  engines  

50m   from Osamu MORI

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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!

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