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.