Galaxy Forum China 2013 - Proposal for Human Mission to Earth-Moon L2

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Galaxy Forum China 2013 - Proposal for Human Mission to Earth-Moon L2

  1. 1. 1 Proposal platform investigation technology for exploration is provided near the ISS(LEO) Japan Manned Space Systems Corp. Tatsuhiro NOZUE Galaxy Forum China 2013 – Beijing Sunday 22 September 2013 (1:30- 5:00pm) @ China National Convention Center
  2. 2. 2 Mission Items Name Purpose Mission Profile ETM1 Test for mission below LEO → ISS → HEO (through Van Allen radiation belt) → Re-entry to Earth M1(ETM2) Transportation to EML-2 LEO → EML-2 M2 Go and Return from EML-2 LEO→ EML-2→Re-entry to Earth M3 Transportation to LLO LEO→LLO M4 Go and Return from LLO LEO→ LLO→ Re-entry to Earth M5 Transportation to Lunar surface LEO→ LLO → Lunar surface M6 Go and Return from Lunar surface LEO→ LLO→ Lunar surface →Re-entry to Earth Supposed Mission Purpose : To confirm the key technology for following Mission as possible Based on ISS(LEO) Mission M1 is also Exploration Test Module for cost reduction ,so named M1(ETM2). ETM1 : Exploration Test Model 1 LEO : Low Earth Orbit HEO : Highly Elliptical Orbit LLO : Low Lunar Orbit EML-2 : Earth-Moon Lagrange Point 2 From Next pages shows Mission Profile of M1(ETM2) to M6
  3. 3. 3 Trajectory Profile (M1(ETM2):LEO→EML-2) L2 Powered Fly By Injection to L2 CP S HTV-H( Habitat) CPS : Cryogenic Propulsion System TLO : Translunar Orbit TLO Injection ΔV=3089m/s ΔV=251m/s ΔV=140m/s Deep Space Habitat Purpose of HTV-H: To become a Habitat Module which supplies cargo and pressurized space for crew of DSH
  4. 4. 4 Trajectory Profile (M2:LEO→EML-2→Re-entry to Erath) L2 Powered Fly By Powered Fly By CP S Injection to L2 Re-entry & Recovery CRV(Crew Rescue Vehicle) TLO Injection ΔV=3089m/s ΔV=251m/s ΔV=140m/s ΔV=251m/s ΔV=140m/s Departure from L2 Deep Space Habitat Purpose of CRV: CRV will be a redundant return system.
  5. 5. 5 System Conditions:Constitution of HTV-H Electric Module Pressurized Module D O C K I N G P O R T Electric Power System/SAP ECLSS, Crew Support Communication, Data Handling Thermal Control RCS,GNC CARGO Propellant tank MON-3/MMH HTV(base) Prop. Module Electric Module Non- Pressurized Module Pressurize d Module Prop. Module (upgrade ) HTV-H
  6. 6. 6 System Conditions:Constitution of CRV Re-entry Capsule D O C K P O R T ECLSS, Crew Support CARGO Electric Module Propellant tank MON-3/MMH HTV(base) Prop. Module Electric Module Non- Pressurized Module Pressurized Module Prop. Module (upgrade ) CRV RCS,GNC Electric Power System/SAP Communication , Data Handling Thermal Control
  7. 7. System Conditions (module of HTV-H,CRV Mass) Subsystem Weighty(ton) Note Prop. Module 1.4 RCS for RVD RVD propellant 2.4 Electric Module 3.3 buttery included 7 Sub-system (Based on HTV) Payload Sub system Weight(ton) Note Pressurized Module 3.0 Based on HTV ECLSS 1.5 Re-entry Capsule 3.0(manned) Cargo The rest Required Cargo Weight> 0Note : Rocket is selected to satisfy “Cargo Weight>0” Supposed Rocket type Payload to LEO Rocket A 25ton H-X (Japan future) equivalent Rocket B 50ton Falcon Heavy equivalent Rocket C 70ton SLS equivalent
  8. 8. System Conditions (Propulsion System) 8 Table.4 Propulsion System for Orbit Maneuver CPS HTV upgrade oxidizer/fuel LOX/LH2 MON-3/MMH Isp 450sec 350sec note structure efficiency η str=mp/(mp+ms) =0.85 HTV Prop. Module + large thrust eng. +large propellant tank maneuver Case1:TLO injection Case2 : non-use Case1: All maneuver except TLO injection Case2: All maneuver CPS : Cryogenic Propulsion System TLO : Translunar Orbit MON-3/MMH : Mixed Oxides of Nitrogen / Mono Methyl Hydrazine. CPS is used to inject to TLO only, after short time from launch to avoid the problem of evaporation
  9. 9. Result of Feasibility Study 9 Propulsion Sub-system weight (ton) Payload Weight (ton) No. Mission Profile Rocket LEO (ton) CPS CPS Propell ant HTV up grade HTV upgrade Propellan t Prop. Module RVD Propell ant Electric Module Pressur ized Module ECLS S Re-entry Capsule Cargo ETM1 LEO→ISS →HEO A 25.0 - - 1.6 10.5 1.4 2.4 3.3 0.0 1.5 3.0 1.3 M1 (ETM2) LEO→ISS →EML-2 B 50.0 4.4 25.2 0.9 2.2 1.4 2.4 3.3 3.0 1.5 0.0 5.6 B 50.0 - - 4.3 31.9 1.4 2.4 3.3 3.0 1.5 0.0 2.2 M2 LEO→ EML-2→Re- entry to Earth B 50.0 4.4 25.2 1.8 4.2 1.4 2.4 3.3 0.0 1.5 3.0 2.8 C 70.0 - - 6.1 47.4 1.4 2.4 3.3 0.0 1.5 3.0 5.0 M3 LEO→LLO B 50.0 4.4 25.2 2.0 4.6 1.4 2.4 3.3 3.0 1.5 0.0 2.2 C 70.0 - - 6.1 47.4 1.4 2.4 3.3 3.0 1.5 0.0 4.3 M4 LEO→ LLO→ Re- entry to Earth C 70.0 6.2 35.3 4.9 11.4 1.4 2.4 3.3 0.0 1.5 3.0 0.7 M5 LEO→ LLO → Lunar surface C 70.0 6.2 35.3 6.5 15.2 0.0 0.0 3.3 3.0 0.0 0.0 0.6 M6 LEO→ LLO→ Lunar surface →Re-entry to Earth C 70.0 6.2 35.3 6.5 15.2 1.5 3.6 1.0 0.0 0.0 0.5 0.3 Rocket type to satisfy cargo > 0 M1(ETM2),M2,M3,M4:manned mission Mission to EML-2 is profitable Next we discuss the M1(ETM2) and M2 and ETM1
  10. 10. Key Events of M1(ETM2) 10 EML-2 LEO TLO Injection Powered Fly By L2 Injection RVD on L2 Habitat Operation
  11. 11. Key Events of M2 11 EML-2 LEO Release on L2 TLO Injection Powered Fly By Re-entry & Recovery
  12. 12. Test or Experiment plan of ETM1 12 15,000km LEO L2 RVD exp.2 (option) ISS docking ISS releas e Re-entry & Recovery L2 RVD exp.1 ISS based exp. ・ECLSS(air , water) Control ・ Astronaut Health Control On-orbit exp. ・Environment Monitoring in Pressurized Module ・Radiation Environment Monitoring ・Power & Thermal control ・Operational Technology Re-entry exp. Re-entry & Recovery from HEO Maneuver exp. HEO Injection ΔV=1863m/s Propulsion Subsystem Test HEO HEO : Highly Elliptical Orbit

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