Operation status for the asteroid
explorer, Hayabusa2
September 27, 2018
JAXA Hayabusa2 ProjectTopics
Regarding Hayabusa2 :l MINERVA-;1 newsflashl MASCOT release operationl Images of Ryugu

Contents
0. Hayabusa2 & mission flow outline
1. Project status & overall schedule
2. MINERVA-;1 newsflash
3. MASCOT release operation
4. Images of Ryugu
5. Other issues
6. Future plans

Overview of Hayabusa2
ObjectiveWe will explore and sample the C-type asteroid Ryugu, which is a more primitive
type than the S-type asteroid Itokawa that Hayabusa explored, and elucidate
interactions between minerals, water, and organic matter in the primitive solarsystem. By doing so, we will learn about the origin and evolution of Earth, theoceans, and life, and maintain and develop the technologies for deep-space return
exploration (as demonstrated with Hayabusa), a field in which Japan leads theworld.

Expected results and effects
BBy exploring a C-type asteroid, which is rich in water and organic materials, wewill clarify interactions between the building blocks of Earth and the evolution ofits oceans and life, thereby developing solar system science.
B Japan will further its worldwide lead in this field by taking on the new challenge ofobtaining samples from a crater produced by an impacting device.
BWe will establish stable technologies for return exploration of solar-system bodies.

Features:
BWorld’s first sample return mission to a C-type asteroid.
BWorld’s first attempt at a rendezvous with an asteroid and performance ofobservation before and after projectile impact from an impactor.
BComparison with results from Hayabusa will allow deeper understanding of thedistribution, origins, and evolution of materials in the solar system.

International positioningH
BJapan is a leader in the field of primitive body exploration, and visiting a type-C
asteroid marks a new accomplishment.
BThis mission builds on the originality and successes of the Hayabusa mission. In
addition to developing planetary science and solar system exploration
technologies in Japan, this mission develops new frontiers in exploration ofprimitive heavenly bodies.
BNASA too is conducting an asteroid sample return mission, OSIRIS-REx (launch:2016; asteroid arrival: 2018; Earth return: 2023). We will exchange samples andotherwise promote scientific exchange, and expect further scientific findings
through comparison and investigation of the results from both missions.

(Illustration: Akihiro Ikeshita)
Hayabusa 2 primary specifications
MassApprox. 609 kg
Launch3 Dec 2014
MissionAsteroid return
Arrival27 June 2018
Earth return2020
Stay at asteroid
Approx. 18 months
Target body
Near-Earth asteroid Ryugu
Primary instruments
Sampling mechanism, re-entry capsule, optical cameras, laser range-finder,
scientific observation equipment (near-infrared, thermal infrared), impactor,
miniature rovers.

Mission FlowLaunch
3 Dec 2014

Arrival at asteroid
June 27, 2018@▲
Earth swing-by
3 Dec 2015

Examine the asteroid by remote sensing
observations. Next, release a small lander androver and also obtain samples from the surface.

Earth returnlate 2020

Depart asteroid
Nov–Dec 2019

Create artificial
craterSample analysis(Illustrations: Akihiro Ikeshita)

After confirming safety, touchdown
within the crater and obtain
subsurface samples

Releaseimpactor

Use an impactor to create
an artificial crater on theasteroid’s surfaceCurrent statusH

1. Current project status& schedule overview

– September 19 – 21 was the MINERVA-II1 deployment operation, withMINERVA-II1 Rover-1A & Rover-1B separating from the spacecraft on
September 21. The two rovers were later confirmed to have landed on thesurface of Ryugu and are moving via hopping.
– September 30 – October 4 is the MASCOT deployment operation, including thepreparatory period.

Schedule overview:
2015
312

Event	

/,4,$-01(2$4,0/2016
10 12!

launch	(& 2017

4

37,/*%9

$2 5/052/(940$34(20,'2020
12

Arrival at Ryugu	5/( ((/41229
$24+2(452/34(20,'1208,.,4901(2$4,0/3Earth swing-by	(& $2 $9

2019

6 7

$1120$&+C"D4(3401(2$4,0/3 Southern hemisphere station
operations (CAN/MLG)	
$9  
&4
$9

Ion engine operations ※	

2018

Departure from Ryugu	06L(&Capsule re-entry	$4(  

Optical navigation	 Solar conjunction	$9 5- 06(&06

12$/5/ 

2. MINERVA-;;1 newsflash
History from deployment to presentn 9/21: 13:05JST separation from the Hayabusa2 spacecraftn 9/21: Day 1 (Sol.1D Image data obtained after rover deploymentn 9/21: Day 2 (Sol.1DRover ON confirmation, telemetry pendingn 9/22: Day 3 (Sol.3DRover ON confirmation, telemetry pendingn 9/22: Day 4 (Sol.4Dl Rover-1A confirm hoppingl Rover-1B telemetry received, surface temperature
measurement, hop preparation
BBBBBBBn 9/23: Day 7 (Sol.7DRover-1A, 1B telemetry receivedl Rover-1B confirm hopping
BBBBBBBn 9/27: Day 20 (Sol.20D

2. MINERVA-II1 newsflash
Image taken immediately after separation

Image captured by Rover-1A on September 21 at around 13:08 JST. This is a color image taken immediately
after separation from the spacecraft. Hayabusa2 is at the top and the surface of Ryugu is bottom. The image isblurred because the shot was taken while the rover was rotating. (Image credit: JAXA)



2. MINERVA-II1 newsflash
Image taken immediately after separation

Image captured by Rover-1B on September 21 at around 13:07 JST. This color image was taken
immediately after separation from the spacecraft. The surface of Ryugu is in the lower right. The top
left colored blur in the top left is due to the reflection of sunlight when the image was taken. (Imagecredit: JAXA) we deleted halation.



2. MINERVA-II1 newsflash
Image captured during hopping

Image captured by Rover-1A on September 22 at around 11:44 JST. Color image captured whilemoving (during a hop) on the surface of Ryugu. The left-half of the image is the asteroid surface.
The bright white region is due to sunlight. (Image credit: JAXA).



2. MINERVA-II1 newsflashNewImages taken by Rover-1B
September 23, 2018: confirmation of Rover-1B hop

2018/09/23 09:50

2018/09/23 09:55

2018/09/23 10:00
CImage creditHJAXAD

2. MINERVA-II1 newsflashNew
September 23, 2018: image captured immediately before hop of Rover-1B

CImage creditHJAXAD

2. MINERVA-II1 newsflashNew
September 23, 2018 at 10:10 JST: surface image from Rover-1B after landing

CImage creditHJAXAD

2. MINERVA-II1 newsflash
September 23, 2018 at 09:43 JST: surface image taken from Rover-1ANewCImage creditHJAXAD

2. MINERVA-II1 newsflash
September 23, 2018 at 09:48 JST: surface image taken from Rover-1ANewCImage creditHJAXAD

2. MINERVA-II1 newsflash
September 23, 2018 at 09:48 JST: surface image taken from Rover-1AMINERVA-II1 successfully captured the shadow of its own antenna and pin

Newpinantenna

CImage creditHJAXAD

2. MINERVA-II1 newsflash
Rover-1B successfully shot a movie

15 frames captured on
September 23, 2018from 10:34 – 11:48
JSTNew

CanimationD
CcreditHJAXAD

2. MINERVA-II1 newsflash
September 21, 2018 at 13:02 JST: image from ONC-W1 at 70m altitude

Separation
location ofMINERVA-II1(estimated)

CImage creditHJAXAD

2. MINERVA-II1 newsflash
Search via ONC? 04:21:06

New= 04:12:34(after ~6.5 mins)

(after ~16 mins)

Bright	  spot	  not	  seen	  in	  previous	  and	  next	  image

Spacecra�	  descent	  target	  point> 04:16:18(after ~10 mins)

04:18:26(after ~13 mins)

The bright point is confirmed as the MINERVA-II or the container cover moving
across =<><?, (=, >: ONC-W1, ?: ONC-T).
CImage creditHJAXAEAISTEU. TokyoEKochi UERikkyo UENagoya UEChiba Institute of TechEMeiji U, U. AizuD2. MINERVA-II1 newsflash
ReferenceHLocation of landing site targets

Spacecra�	  descent	  target	  pointSpacecra�	  descent	  target	  point

If MINERVA-II1 separated at the spacecraft descent target point,then post separation MINERVA-II1 should be within the area N6.3. MASCOT release operation
MASCOT System Overview

MASCOT (Mobile Asteroid Surface Scout)
J Developed by DLR (German AerospaceCenter) in close cooperation with CNES
(French Space Agency)(©	  JAXA)

J Agile, lightweight & compact landing platform
for in-situ asteroid research
J Lander Module mass: ~9.8 kg
J Lander Module size: 0.275 x 0.290 x 0.195 m
J Carries Four Scientific Payloads: MASCAM,
MicrOmega, MARA, and MASMAG

Flight	  Model(©	  DLR)	  

3. MASCOT release operation	  MASCOT System Overview

Top AntennaRadiator

Scientific instruments aboard MASCOT
DeviceFunc�on

Wide-­‐angle	  camera	  (MASCAM)

Imaging	  at	  mul�ple	  wavelengths

Spectroscopic	  microscope	  (MicrOmega)

Inves�ga�on	  of	  mineral	  composi�on	  and	  characteris�csThermal	  radiometer	  (MARA)

Surface	  temperature	  measurements

Magnetrometer	  (MASMAG)

Magne�c	  ﬁeld	  measurement

MASCOT Bus System
J Power: Primary lithium battery
J Communication: Communication system usingtransceivers same as Minerva-II rovers
J Mobility: Up-righting and hopping mechanism
using motor and excenter mass
J GNC: MASCOT attitude determination using
proximity sensors

MARA

MASCAM
MicrOmega

MASMAG

Battery Pack
Ebox

CCOM Transceivers

Mobility Unit

3. MASCOT release operation	  MASCOT On-Asteroid Operation
Baseline MASCOT Activities after the Separation
CP 	  :	  Contact	  Point	  	  EoM 	  :	  End	  of	  Mission	  SP 	  :	  Se�lement	  Point	  MP 	  :	  Measuring	  Point	  MSC 	  :	  MASCOT	  	  	  

3. MASCOT release operation
Landing site candidates for MASCOTHHSelection from
10 candidates and the order of priority

C©DLR,CNESD

Priority of landing siteHMA-9 > MA-1 > MA-10 > MA-7 > MA-5 > MA-2

3. MASCOT release operation

MASCOT landing site©JAXA, University Tokyo, Kochi University, Rikkyo University, Nagoya University,Chiba Institute of Technology, Meiji University, University of Aizu, AIST, CNES, DLR

3. MASCOT release operation

MASCOT landing site©JAXA, University Tokyo, Kochi University, Rikkyo University, Nagoya University,
Chiba Institute of Technology, Meiji University, University of Aizu, AIST, CNES, DLR

3. MASCOT release operationOutline of MASCOT release operation sequence

Note: Time indicates the scheduled time, but may change due to conditions during the actual operation.



GFRyugu Images

NewImage in the evening direction during BOX-B operations
Images taken in the evening direction of Ryugu. Left is the photograph with the Optical Navigation Camera Telescopic(ONC-T) and on the right is the photograph from the Thermal Infrared Imager (TIR). The photographs were taken on
August 31, 2018 at around 19:00 JST from a position of around -x = 9km.
(Left image creditHJAXA, University of Tokyo, Kochi University, Rikkyo University, Nagoya University, Chiba Institute of Technology, Meiji University, Universityof Aizu, AIST; Right image credit : JAXA, Ashikaga University, Rikkyo University, Chiba Institute of Technology, University of Aizu, Hokkaido University ofEducation, Hokkaido Kitami Hokuto High School, AIST, National Institute for Environmental Studies, University of Tokyo, German Aerospace Center (DLR), Max
Planck Society for the Advancement of Science, Stirling University.)



GFRyugu Images

New

Image in the evening direction during BOX-B operations
Images taken in the evening direction of Ryugu. Left is the photograph with the Optical Navigation Camera Telescopic(ONC-T) and on the right is the photograph from the Thermal Infrared Imager (TIR). The photographs were taken onAugust 31, 2018 at around 23:00 JST from a position of around -x = 9km.
(Left image creditHJAXA, University of Tokyo, Kochi University, Rikkyo University, Nagoya University, Chiba Institute of Technology, Meiji University, Universityof Aizu, AIST; Right image credit: JAXA, Ashikaga University, Rikkyo University, Chiba Institute of Technology, University of Aizu, Hokkaido University ofEducation, Hokkaido Kitami Hokuto High School, AIST, National Institute for Environmental Studies, University of Tokyo, German Aerospace Center (DLR), Max
Planck Society for the Advancement of Science, Stirling University.)



GFRyugu Images

New

Images acquired during Touchdown 1 Rehearsal 1

Image of the touchdown candidate sites taken from about 3km above the surface using the Optical Navigation Camera –Telescopic (ONC-T). The image was captured on September 12, 2018 at around 06:00 JST. In the right-hand image, theapproximate areas of the touchdown candidate sites are marked out.
C©JAXAD

(Image credit: JAXA, University of Tokyo, Kochi University, Rikkyo University, Nagoya University, Chiba Institute of Technology, Meiji University, Aizu University,AIST). GFRyugu Images
Image captured by ONC-W1 during the MINERVA-II1 separation operation
New

NoteHThis is thefirst image takenby ONC-W2.
Image of Ryugu captured with the ONC-W2 at an altitude of about 67m. Image was taken on
September 21, 2018 at around 13:00 JST. This photograph of the horizon of Ryugu was taken
diagonally downwards from where the W2 is installed on the spacecraft.

(Image credit: JAXA, U. Tokyo, Kochi U, Rikkyo U, Nagoya U, Chiba Institute of Tech, Meiji U, U. Aizu, AIST)



GFRyugu Images
Image captured with ONC-T during the MINERVA-II1 separation operation

New

Image of Ryugu captured by the ONC-T at an altitude of about 64m. Image was taken on
September 21, 2018 at around 13:04 JST.This is the highest resolution photograph obtainedof the surface of Ryugu. Bottom left is a large boulder.
CImage credit: JAXA, U. Tokyo, Kochi U, Rikkyo U, Nagoya U, Chiba Institute of Tech, Meiji U, U. Aizu, AIST.DNoteHHHighest resolution photographobtained by Hayabusa

High resolution image of the surface of asteroid Itokawa photographed by Hayabusa. "D" is taken froman altitude of 63m. It is thought that the so-called "Muses Sea" (official name "MUSES-C Regio") iscovered with a "gravel" of granules with diameters from a few mm to few cm. (From Yano et al,Science Vol 312 2, June 2006)



5. Other issues■ On the “Imagining Ryugu” contest
BHayabusa2 Project nodes (organizations and institutes thatgathered entries) must now each nominate works.
BFinal judgement will be at the end of the year.

6. Future Plans■Operation schedule
J September 30 – October 4 HMASCOT release operation (including
preparatory period)@MASCOT separation scheduled for October 3 at around 11:00 JST.
J Mid-OctoberHTouchdown 1 Rehearsal 2
J Late OctoberHTouchdown 1■Press briefings and media events
J October 3 CWednesdayD@9:30L18:30 Open press centerKSagamihara
15:00L16:00 Press briefing@@@ 17:00L18:00 MASCOT press conference transmission
J October 11CThursdayD@15:30L16:30 Press conf.KOchanomizu
Note: Time is in JST.
ReferenceMINERVA-II1
MINERVA-II is the successor of MINERVA installed on the Hayabusa spacecraft.	  
MINERVA-II1 (Rover-1A, Rover-1B)

Producedat JAXAC©JAXADI Collaborating manufacturers, universities andrelated organizationsJ
Aichi University of Technology, University of Aizu,Addnics corp.EAntenna Giken Co., Ltd., ELNA ,CesiaTechnoEThe University of Tokyo, Tokyo
Denki UniversityA Digital Spice Corp., Nittoh Inc.EMaxon Japan, DLR, ZARMl Weight (including deployment)
MIMERVA-II1 :2.5kgl MINERVA-II1
Twin roversMINERVA-II1
MIcro Nano Experimental Robot Vehicle for Asteroid,
the Second Generation

J New hopping mobility
J Adaptation with AI
J Small, light-weight,
J Low power consumption
J Autonomous behavior

C©JAXADJ Scientific observation（stereo sensing, thermometer)MINERVA-II11(&,),&$4,0/30)06(2  

bodysizeweightactuators
sensorscom.

Cylinder (hexadecagonal pole)
Diameter: )180[mm]
Height: 70[mm]1A:1151[g], 1B:1129[g]DC motor
4 cameras(1A), 3 cameras(1B)
photodiodes, accelerometer
thermometers, gyro
32k[bps](max)Selection of landing site candidates forMINERVA-;;
Conditions for MINERVA-II landing site selectionHp Landing site does not overlap with spacecraft touchdown candidates.
p Landing site does not overlap with MASCOT landing site candidates.
p The altitude of the spacecraft after separation must not be lower than 30m.
p Ensure communication with ground station.
n Ensure communication with Hayabusa2 spacecraft.
n Not high temperature region, and fewer parts in shadow
BDue to the equatorial ridge, separation near the equator results in widely spaced landing
points to the north and south.
BSeparating in the southern hemisphere may result
Landing
north
location
in a spacecraft altitude below 30m.
south

BSeparate in northern hemisphere,
more than 100m north of the equator.

Separation
position

C©JAXAD When separating near the equator, thelanding position spread north and south.Selection of landing site candidates forMINERVA-;;
Landing site candidates for MINERVA-II: northern hemisphere

Possible overlap
with mid-latitude
touchdown

No communication
with ground station
Longitude 0°
C©JAXAD

BTouchdownBconfirm no overlap with
MASCOT's landing site.
BAlso consider observability etc. using theONC-T camera.

Candidate locationsH
N6 > N1 > N7 

MINERVA-II1
MINERVA-;1 schematic showing the deployment operation sequence Additional free fall for
preventing plumecontamination
Ascent ΔV

Altitude

MINERVA-II Separation
GCP-NAV
Home position:

20 km

Wait for attitude control
convergence

constant descent velocity@@40 → 10 cm/s@@(deceleration at 5km)

MINERVA-II landing
Attitude scan>A�er	  350sec	  of	  =	  “Lateral	  dV2	  (A�er	  Separa�on)”	  Point B:
1st Contact on
Surface

60 m
Separation
altitudeHH
55m

free fall=at	  LIDAR	  Alt.	  60m	  “Lateral	  dV1	  (Before	  Separa�on)	  ”	  “GCP-­‐NAV	  end”	  	  HP Keeping

ONC-W2

Point A:MINERVA-IISeparation

ONC-T

Point C:
Final settlement
Point

ONC-W1year of2018

9/20, 14:08

9/21, 13:04

13:06 13:07

Time(JSTDD

9/22, 15:00

BOX-B Operation

C©JAXAD#01(2$4,0/,.$*(3Image of the south polePublished
Cbut south pole is
now at the image topD

Image of Ryugu towards the asteroid’s south pole. Photograph taken with the Optical Navigation
Camera Telescopic (ONC-T) on August 24, 2018 at around 17:00 JST. The image was captured froma position of around +y = 9 km. The distance to Ryugu was about 22 km. (Image credit: JAXA, University of Tokyo, Kochi University, Rikkyo University, Nagoya University,Chiba Institute of Technology, Meiji University, University of Aizu, AIST)



Touchdown 1 Rehearsal 1
TD1-R1 operation overview (Time is JST)
September 11, 2018@@15:27@@Start descent from home position (altitude 20km), descent speed 0.4m/s@@20:20@@Altitude approximately 10km
September 12@@02:05@@Descent slowed to 0.1m/s@@10:40@@Altitude approximately 1.5km@@12:57@@Descent cancelled at an altitude of about 600m:Abegan rising at 0.5m/s@@16:30@@Acceleration for return to home position
September 13@@15:00@@Return to home position: An automatic change was planned from the LIDAR long-distance mode to the shortdistance mode. However, it was impossible to reach the required light intensity
needed for the switch as the reflected light for distance measurement was too weak.
The altitude measurement therefore became impossible and the spacecraftC©JAXAD
autonomously ceased descent and began to rise.