JAXA activities 2009-2010JAXA activities 2009-2010

October 8, 2010October 8, 2010

Japan Aerospace Exploration AgencyJapan Aerospace Exploration Agency

Soichi NoguchiSoichi Noguchi

Соичи НогучиСоичи Ногучи 　　

JAXA AstronautsJAXA AstronautsNoguchiNoguchi

STS-114STS-114

Exp-22/23Exp-22/23 FurukawaFurukawa

Exp-28/29Exp-28/29

MukaiMukai

STS-65, 95STS-65, 95

YamazakiYamazaki

STS-131STS-131

WakataWakata

STS-72, 92STS-72, 92

Exp-18/19/20Exp-18/19/20

MohriMohri

STS-47, 99STS-47, 99

DoiDoi

STS-87, 123STS-87, 123

HoshideHoshide

STS-124STS-124

YuiYui KanaiKanaiOnishiOnishi

Astronauts: 2 former(MeSci, USOOSA), 6 activeAstronauts: 2 former(MeSci, USOOSA), 6 activeCandidates: 3Candidates: 3Completed Flights: 11 Shuttle , 2 ISS ExpeditionCompleted Flights: 11 Shuttle , 2 ISS Expedition ( (Exp18, Exp18, 22)22)

Astronaut Candidates Astronaut Candidates 20092009

[Dec.21] Soyuz 21S Launch

[Dec.23] Docking

Soyuz 21S Launch Dec.2009

SFA Assembly Jan.2010

[Jan.4-6]

SFA Assembly in JPM

Attached to JEM Airlock Table

ICS Direct Link to Tsukuba Mar.2010

[Feb.24] ICS Comm with SSIPC

[May.5] Space School via ICS[Mar.6] Try Zero-G Event via ICS (voice, MPC video)

SSIPC started ICS Nominal Ops from Feb.1, 2010.

Flight 19A Apr.2010

[Apr.5] STS-131/19A Launch

2 Japanese on ISS!

Soyuz 21S Return June 2010

[May.12] 21S Relocation

ULF4 mission

[Jun.2] Soyuz 21S Return

International Space StationInternational Space Station

““Kibo” Japanese Experiment Kibo” Japanese Experiment Module Module

““Kibo” Japanese Experiment Kibo” Japanese Experiment Module Module

JEM Small Fine Arm (SFA)

Total Length Approx. 2.2m

Weight Approx. 180kg

Spec. 6 DOF (6 joints), SFA TOOL (Grapple Mech, FTS, Wrench)

Max Weight 80kg (with compliance control)300kg (no conpliance)

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JEMRMS Main Arm

JPM

JEF

JEM Airlock

Small Fine Arm

TDRSDRTS

White White SandsSands

U.S.U.S. JapanJapan(TKSC)(TKSC)

JEM Operations JEM Operations Control System Control System (OCS)(OCS)

NASA Link ICS Link

DRTS SNDRTS SN

JAX

A I/F

MSFCMSFC

JSCJSC NA

SA I/F

ICS I/F

SSIPCSSIPC

S-band

Ku-bandKa-band

S-band•Return(192kbps) : ISS Telemetry, Voice•Forward(72kbps) : ISS Command, VoiceKu-band•Return(50Mbps) : Payload Data, Video•Forward(3Mbps) : Crew Data

Ka-band

•RTN(50Mbps) : JEM Telemetry, Voice,

Video, Payload Data

•FWD(3Mbps) : JEM Command, Voice,

Payload Data, Video

Overview on JEM Communications Operation

JEM Telemetry/CommandAudio, Video

Payload Data

Completed “Full Configuration of Kibo” March 2010祝

Launched on H-IIB rocket Launched on H-IIB rocket from Tanegashima, Japan from Tanegashima, Japan

(11.09.09 JST)(11.09.09 JST)

Captured and berthed by Captured and berthed by Exp20 crew with Exp20 crew with

Canadarm2 Canadarm2

(18.09.09 JST)(18.09.09 JST)

H-II Transfer VehicleH-II Transfer Vehicle

Reentry Reentry

Rendezvous Rendezvous

HTVs to be launched annually 2009-2015 (7 HTVs to be launched annually 2009-2015 (7 times)times)

PressurizedLogistics Carrier

Avionics and Propulsion Modules

Exposed Pallet

Cargo Capacity to ISS Total 　 6 tons　　　 Pressurized 4.5 tons　　　 Unpressurized 1.5 tons 　　

Dimensions Total Length 　　　 10 m Max. Diameter 　 4.4 m Total Weight 　　 16.5 tons

Mission Duration Planned duration 100 hr Off-nominal Hold More than 1 week ISS Docked Ops 30 days

H-II Transfer Vehicle (HTV)H-II Transfer Vehicle (HTV)

Unpressurized Logistics Carrier

Status of HTV-R(Return capability) Concept Study

JAXA has just started the concept study of HTV with Return vehicle (HTV-R).

Trade off study of several configurations is on going. The purposes of the HTV-R are as follows.

Establishment of safe and confident return to the Earth technology for Japanese future manned space activities.

Realization of return capability of utilization specimen and on-orbit replaceable units from the ISS.

The HTV-R first flight time frame is now under study, sometime between JFY2016 and JFY2018.

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HTV-R Operations Concept

ISS

Rendezvous Flight

H-IIB Launch Vehicle

HTV-R

-Docking-Resupply to ISS-Return Cargo into HRV-Disposal Waste into HTV

Approach

De-orbit by HTV HRV

Separation

HRV (HTV Return Vehicle)

Lifting Entry

Parachute Activation

Recovery operation

HTV Burn Out

HTV Mission Control Room

(Option No.1 Configuration)

Candidates of HTV-R configuration

Option 1:Return Capsule Mass: 2 ton Diameter: 2.6 m Height: 1.5m Downmass Capability: 0.3

ton

Option 2:Return Capsule Mass: 5.7

tonDiameter: 4.0 mHeight: 3.8mDownmass Capability: 1.6

ton

Road map to the Japanese future manned space activities

2011 2016 - 2018 20XX

HTV-R Design, Manufacture, Test HTV-R OperationDevelopment of Manned VehicleFirst Flight

HTV

HTV-R

Diameter 2.6mΦ

Diameter 4mΦ

Option 1

Option 2

Manned Space Vehicle

【 Manned Technology 】・ Abort・ Life support・ Man / Machine Interface (CMD and Monitor Panel, Chair, etc.)

US, Space XDragon

Diameter 3.6mΦ(Cargo in 2011)

Manned

ESA ARVDiameter 4.4mΦ(Cargo in 2016)

Manned (in 2020 )

(Status of NASA, ESA)

ImplementedRe-entry Experiments・ OREX・ HYFLEX・ USERS・ Hayabusa

Manned

[Common]

-Demonstra-tion of re-entry and recovery technology

- Realization of return capability from the ISS

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Utilization return demand from ISS

Life science (70%)

Living thing, Plant, Protein,

Cell/Medical sample

Material experiment

(30%)

Major mission requirements for return vehicle

① Temperature control (Room temp. , Freeze)

② Low acceleration (Less than 4G)③ Recovery time from installation to

handover to user within 4days

Required technology for return vehicle①Thermal protection (Heat shield)　　⇒　 To keep low temperature②Lifting entry　　⇒　 To keep low G③High accuracy guidance　　⇒　 Quick recovery 　

Step for the manned vehicle of Japan

Contribution to the ISS Return Demand and the Demonstration of the Return to the Earth

Technology

【 Reference 】 Return VehiclesCountry Russia USA China USA

Return Vehicle

Soyuz Space Shuttle Shénzhōu Apollo

Size

Φ2.2m×H2.1m

2900kg(Capsule)

3 Crews

－Φ2.5m×H2.5m

3240kg(Capsule)

3 Crews

Φ3.9m×H3.2m

5560kg(Capsule)

3 Crews

Program Status OngoingOngoing

（ until 2011 ）Ongoing Completed

Country Europe USA

Return Vehicle

ARV Dragon （ Space X ）

SizeΦ4.4×H4m

7500kg(Capsule)

Φ3.6m×H2.9m

CapabilityUpmass:6t （ incl. propellant 4t ）

Downmass:1.5tUpmass:3.3t （ incl. exposure cargo ）

Downmass:2.5t

Schedule Unmanned: 2016, Manned: 2025 2011 20

Hayabusa Sample ReturnHayabusa Sample Return

2005.NovLanding & Sample RetrievalOn Itokawa

2010.JuneAtmospheric Reentry

2010.JuneCapsule Recovered!

Hayabusa Mission GoalHayabusa Mission Goal

Hayabusa “Final Approach”Hayabusa “Final Approach”

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Back-up HTV

• Pressurized Cargo (3.6 tons)– 8 Cargo Transfer Bags (CTB) in 8 racks (HRR)– Additional cargo on rack front– Cargo

• 33% food

• 20% experiment prvisions

• 18% JEM parts, Small Fine Arm

• 10% crew provisions– Cargo ownership

• 73% NASA

• 23% JAXA

• 4% ESA

CTB (Cargo Transfer Bag)

HRR (HTV Resupply Rack)Pressurized Logistics Carrier

H-II Transfer Vehicle 1H-II Transfer Vehicle 1stst Flight Flight ((HTV-1) HTV-1)

HREP(Hyper-spectral Imager for Coastal Ocean / Remote Atmosphere and Ionosphere Detection System)

SMILES(Superconducting Submilimeter-Wave Limb-Emission Sounder)

Unpressurized Cargo (3.6 tons)(0.9 tons)SMILESHREP

Exposed Pallet

H-II Transfer Vehicle 1H-II Transfer Vehicle 1stst Flight Flight ((HTV-1) HTV-1)

Step to the Japanese manned space transportation system

Functions of HTV (Demonstrated)

Functions of return vehicle

Functions of manned vehicle

HTV Manned vehicle

Thermal control

Pressure and temperature control of pressurized section

Life supportSafety abort

Thermal protection (Heat shield)Lifting entryHigh accuracy guidance

Power generation, distributionData handling, Communication

Navigation, Guidance, ControlRendezvous docking

Operation control (Flight and Docked phase)

HTV-R

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Automatic docking

(Heat exchanger)

HTV operationHTV operation

Japan’s past experiences on re-entry vehicles

Vehicle Summary Entry/

Recovery

RYUSEI(OREX )(Orbital Re-entry Experiment)Dia. 3.4 m, Height 1.5 mMass 865kg

[Purpose] To contribute to HOPE development by accumulating experience in designing and producing a re-entry vehicle and acquiring re-entry data which is difficult to acquire in ground experiments[Result] The vehicle was launched and inserted into orbit by H-II launch vehicle in Feb. 1994. It re-entered the atmosphere after one revolution. The vehicle collected experimental data during re-entry, transmitted after re-entry, and splashed down in the Central Pacific Ocean.

Ballistic Entry

/

Not Recovered

HYFLEX(Hypersonic Flight Experiment)W 1.4m, L 4.4m, H 1.0m

Mass 1048kg

[Purpose] Accumulation of designing, constructing and operating technology of a vehicle flying at hypersonic speed like a plane and acquisition of various data which are difficult to obtain by ground tests

[Result] The vehicle was launched by J-I launch vehicle in Feb. 1996. It collected several useful data in flight and splashed down in the ocean, but it was unsuccessfully recovered.

Lifting Entry

/

Not Recovered

USERS(Unmanned Space Experiment Recovery System)Capsule Dia. 1.5m

　　　　　　 Height 1.9m

　　　　　　 Mass 884kg

[Purpose] To establish the unmanned space experiment system with self return capability

[Result] The vehicle was launched by H-IIA launch vehicle on Sep. 2002. After approximately 8.5 months of on-orbit operations, Reentry Module (REM) was separated from Service Module (SEM), de-orbited and splashed down on May 2003 at open sea east of Ogasawara Islands with the results of processed materials.

Ballistic Entry

/

Recovered

HAYABUSA(MUSES-C)(Mu Space Engineering Satellite-C)Capsule Dia. 0.4m

　　　　　　 Height 0.2m

　　　　　　 Mass 17kg

[Purpose] Sample return from an asteroid named Itokawa by traveling through space using an ion engine and arriving at the asteroid autonomously to acquire a material sample

[Result] The vehicle was launched by M-V rocket on May 2003, and returned to the Earth on June 2010, dropped its onboard capsule in Australia.

Ballistic Entry

/

Recovered

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BACKUP Hayabusa

Outline of HAYABUSA Asteroids are thought to be celestial bodies that preserve information from the time of the Solar System's formation. If we collect a sample from an asteroid and bring it back to Earth to carry out precise research on it, we can gain some

precious clues to understand the origin and evolution of the Solar System. Bringing back a sample from a celestial body in the Solar System is called "Sample Return." "HAYABUSA" is a probe to verify the practicality of acquired technology developed to archive future full-scale "sample return missions.""HAYABUSA' was launched aboard the M-V Launch Vehicle on May 9,2003. It was accelerated by a swing-by of the Earth in May 2004 and reached its target Asteroid Itokawa on September 12,2005, after traveling about 2 billion kilometers. in September and October that year, "HAYABUSA" completed the most remote-sensing and measurement of the geometry of Itokawa and made two landings in November to collect a sample from Itakawa. Through scientific observations performed during "HAYABUSA's" stay on Itokawa various knowledge was obtained including on its gravity and surface condition. The achievements of "HAYABUSA" were featured in the scientific magazine, "Science."

Overview Asteroid Explorer Information about HAYABUSAMay 9, 2003 Launched by the M-V-5 Rocket from Kagoshima Space Center. May 27, 2003 Ion Engine operation started. May 19, 2004 Orbit transfer using the Electric Propelled Delta-V Earth Gravity Assist July 29, 2005 Performed the Star Tracker imaging of Itokawa. September 12, 2005 Arrived at Itokawa. (about 20km away) September 30, 2005 Arrived at the Home Position (about 7km away). November 12, 2005 Released the probing robot ”Minerva”. November 20, 2005 Performed the first touch down and release of the target marker with 880,000 autographs inside. November 26, 2005 Performed the second touchdown. December 8, 2005 Lost communication with the earth due to operation rupture by fuel leakage. January 26, 2006 Resumed communication and operation. January 18, 2007 Sample-catcher was actually transferred into the recovery capsule, and latched and sealed. February, 2007 The ion engines ignited and operated again. April 25, 2007 The homeward journey with an ion engine drive was started. October 18, 2007 Finished first phase orbit maneuver toward Earth. End of May, 2008 Reached the farthest deep space from the Earth. February 4, 2009 Firing ion engine and starting second phase orbit maneuver to return to Earth. November 4, 2009 Ion engine anomaly. November 19, 2009 Resumed cruise by combining two partially working ion engines. March 27, 2010 Finished second phase orbit maneuver toward Earth. April to June, 2010 Trajectory Correction Maneuvers (TCMs) June 13, 2010 Back to the Earth , capsule recovered.