1. JAXA activities 2009-2010 October 8, 2010 Japan Aerospace Exploration Agency Soichi Noguchi Соичи Ногучи Соичи Ногучи

2. JAXA Astronauts NoguchiSTS-114Exp-22/23 FurukawaExp-28/29 Mukai STS-65, 95 YamazakiSTS-131 Wakata STS-72, 92 Exp-18/19/20 Mohri STS-47, 99 Doi STS-87, 123 HoshideSTS-124 Yui Kanai Onishi Astronauts: 2 former(MeSci, USOOSA), 6 active Candidates: 3 Completed Flights: 11 Shuttle, 2 ISS Expedition (Exp18, 22) Astronaut Candidates 2009

3. [Dec.21] Soyuz 21S Launch [Dec.23] Docking Soyuz 21S Launch Dec.2009

4. SFA Assembly Jan.2010 [Jan.4-6]  SFA Assembly in JPM  Attached to JEM Airlock Table

5. 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.

6. Flight 19A Apr.2010 [Apr.5] STS-131/19A Launch 2 Japanese on ISS!

7. Soyuz 21S Return June 2010 [May.12] 21S Relocation ULF4 mission [Jun.2] Soyuz 21S Return

8. International Space Station “Kibo” Japanese Experiment Module

10. JEM Small Fine Arm (SFA) Total LengthApprox. 2.2m WeightApprox. 180kg Spec.6 DOF (6 joints), SFA TOOL (Grapple Mech, FTS, Wrench) Max Weight80kg (with compliance control) 300kg (no conpliance) 9 JEMRMS Main Arm JPM JEF JEM Airlock Small Fine Arm

11. TDRS DRTS White Sands U.S.Japan(TKSC) JEM Operations Control System (OCS) NASA LinkICS Link DRTS SN JAXA I/F MSFC JSC NASA I/F ICS I/F SSIPC S-band Ku-band Ka-band S-band Return(192kbps) : ISS Telemetry, Voice Forward(72kbps) : ISS Command, Voice Ku-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/Command Audio, Video Payload Data

12. Completed “Full Configuration of Kibo” March 2010 祝

13. Launched on H-IIB rocket from Tanegashima, Japan (11.09.09 JST) Captured and berthed by Exp20 crew with Canadarm2 (18.09.09 JST) H-II Transfer Vehicle Reentry Rendezvous HTVs to be launched annually 2009-2015 (7 times)

14. Pressurized Logistics Carrier Avionics and Propulsion Modules Exposed Pallet Cargo Capacity to ISS Total 6 tons Pressurized4.5 tons Unpressurized1.5 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) Unpressurized Logistics Carrier

15. 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.

16. 15 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)

17. 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 ton Diameter: 4.0 m Height: 3.8m Downmass Capability: 1.6 ton

18. Road map to the Japanese future manned space activities 20112016 - 2018 20XX HTV-R Design, Manufacture, Test HTV-R Operation Development of Manned Vehicle First 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 X Dragon Diameter 3.6mΦ (Cargo in 2011) Manned ESA ARV Diameter 4.4mΦ (Cargo in 2016) Manned (in 2020 ) (Status of NASA, ESA) Implemented Re-entry Experiments ・ OREX ・ HYFLEX ・ USERS ・ Hayabusa Manned [Common] -Demonstra- tion of re- entry and recovery technology - Realization of return capability from the ISS

19. 18 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 vehicle ① Thermal protection (Heat shield) ⇒ To keep low temperature ② Lifting entry ⇒ To keep low G ③ High 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

20. 【 Reference 】 Return Vehicles Country RussiaUSAChinaUSA Return Vehicle SoyuzSpace 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 StatusOngoing （ until 2011 ） Ongoing Completed CountryEuropeUSA Return Vehicle ARV Dragon （ Space X ） Size Φ4.4×H4m 7500kg(Capsule) Φ3.6m×H2.9m Capability Upmass:6t （ incl. propellant 4t ） Downmass:1.5t Upmass:3.3t （ incl. exposure cargo ） Downmass:2.5t ScheduleUnmanned: 2016, Manned: 20252011 19

22. Hayabusa Sample Return 2005.Nov Landing & Sample Retrieval On Itokawa 2010.June Atmospheric Reentry 2010.June Capsule Recovered!

23. Hayabusa Mission Goal

24. Hayabusa “Final Approach”

27. 26 Back-up HTV

28. 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 1 st Flight (HTV-1)

29. 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)  SMILES  HREP Exposed Pallet H-II Transfer Vehicle 1 st Flight (HTV-1)

30. Step to the Japanese manned space transportation system Functions of HTV (Demonstr ated) Functions of return vehicle Functions of manned vehicle HTV Manned vehicle Thermal control Pressure and temperature control of pressurized section Life support Safety abort Thermal protection (Heat shield) Lifting entry High accuracy guidance Power generation, distribution Data handling, Communication Navigation, Guidance, Control Rendezvous docking Operation control (Flight and Docked phase) HTV-R 29 Automatic docking (Heat exchanger)

31. HTV operation

32. Japan’s past experiences on re-entry vehicles VehicleSummaryEntry/ Recovery RYUSEI(OREX ) (Orbital Re-entry Experiment) Dia. 3.4 m, Height 1.5 m Mass 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 31

33. BACKUP Hayabusa

34. 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."

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