JAXA activities 2009-2010

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

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

3. Soyuz21SLaunch Dec.2009 [Dec.21] Soyuz 21SLaunch [Dec.23] Docking

4. SFAAssemblyJan.2010 • [Jan.4-6] • SFAAssemblyinJPM • AttachedtoJEMAirlockTable

5. ICSDirect Link to Tsukuba Mar.2010 SSIPCstartedICSNominalOpsfromFeb.1,2010. [Feb.24] ICSCommwithSSIPC [May.5]SpaceSchoolviaICS [Mar.6]TryZero-GEventviaICS(voice,MPCvideo)

6. Flight19A Apr.2010 2JapaneseonISS! [Apr.5] STS-131/19ALaunch

7. Soyuz21SReturn June 2010 ULF4mission [May.12] 21SRelocation [Jun.2]Soyuz 21SReturn

8. International Space Station “Kibo” Japanese Experiment Module

9. “Kibo” Japanese Experiment Module

10. JEM Small Fine Arm (SFA) JEMRMS Main Arm Small Fine Arm JPM JEM Airlock JEF

11. TDRS S-band Ka-band DRTS Ku-band NASA Link ICS Link • 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 U.S. Japan (TKSC) White Sands DRTS SN SSIPC JSC JEM Telemetry/CommandAudio, Video JAXA I/F NASA I/F JEM Operations Control System (OCS) ICS I/F MSFC Payload Data Overview on JEM Communications Operation

12. 祝 Completed “FullConfigurationofKibo”March 2010

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

14. H-II Transfer Vehicle (HTV) Cargo Capacity to ISS Total 6 tons Pressurized4.5 tons Unpressurized1.5 tons Dimensions Total Length10 m Max. Diameter4.4 m Total Weight16.5 tons Mission Duration Planned duration100 hr Off-nominal Hold More than 1 week ISS Docked Ops30 days Pressurized Logistics Carrier Exposed Pallet Unpressurized Logistics Carrier Avionics and Propulsion Modules

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. HTV-ROperations Concept ISS HRV (HTV Return Vehicle) De-orbit by HTV HRV Separation • -Docking • Resupply to ISS • Return Cargo into HRV • Disposal Waste into HTV Rendezvous Flight Approach Lifting Entry H-IIB Launch Vehicle Parachute Activation HTV Burn Out Recovery operation HTV Mission Control Room (Option No.1 Configuration) HTV-R 15

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 20XX 2011 2016 - 2018 HTV-R Design, Manufacture, Test HTV-R Operation Development of Manned Vehicle First Flight HTV-R Manned Space Vehicle • [Common] • Demonstra-tion of re-entry and recovery technology • Realization of return capability from the ISS Option 1 【Manned Technology】 ・Abort ・Life support ・Man / Machine Interface (CMD and Monitor Panel, Chair, etc.) HTV Manned Diameter 2.6mΦ Implemented Re-entry Experiments ・OREX ・HYFLEX ・USERS ・Hayabusa Option 2 Diameter 4mΦ (Status of NASA, ESA) Manned Manned (in 2020 ) US, Space X Dragon Diameter 3.6mΦ (Cargo in 2011) ESAARV Diameter 4.4mΦ (Cargo in 2016)

19. Contribution to the ISS Return Demand and the Demonstration of the Return to the Earth Technology Major mission requirements for return vehicle Utilization return demand from ISS Temperature control (Room temp. , Freeze) Low acceleration (Less than 4G) Recovery time from installation to handover to user within 4days Life science (70%) Living thing, Plant, Protein, Cell/Medical sample Required technology for return vehicle Material experiment (30%) ①Thermal protection (Heat shield) 　　⇒　To keep low temperature ②Lifting entry 　　⇒　To keep low G ③High accuracy guidance 　　⇒　Quick recovery Step for the manned vehicle of Japan 18

20. 【Reference】Return Vehicles

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. Back-up HTV

28. H-II Transfer Vehicle 1st Flight (HTV-1) • 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

29. H-II Transfer Vehicle 1st Flight (HTV-1) • Unpressurized Cargo (3.6 tons) • (0.9 tons) • SMILES • HREP Exposed Pallet SMILES(Superconducting Submilimeter-Wave Limb-Emission Sounder) HREP(Hyper-spectral Imager for Coastal Ocean / Remote Atmosphere and Ionosphere Detection System)

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

31. HTV operation

32. Japan’s past experiences on re-entry vehicles 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. 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.