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
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
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
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
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
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. 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. 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. 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. Key Events of M1(ETM2)
10
EML-2
LEO
TLO Injection
Powered Fly By
L2 Injection
RVD on L2
Habitat Operation

11. Key Events of M2
11
EML-2
LEO
Release on L2
TLO Injection
Powered Fly By
Re-entry &
Recovery

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