Alternate DRM Proposalfor Moon Next Scenario

Nov. 15, 2011

1

Naoki SatoJAXA Space Exploration Center (JSPEC)

Nov. 15, 2011

Background

� Current transportation architecture for GER (not only for Moon Next Scenario) is based on:� US SLS and MPCV

� Russian Next Generation Space Launch Vehicle and SpacecraftVehicle and Spacecraft

� Large CPS and/or SEP

� Small or Medium elements should be considered in order to have:� More flexibilities and robustness of program

� More possibilities to involve commercial industries and/or International Partners

2

One possibility for Collaborated Mission Scenario

MOONMOON

Small CPS 2Small CPS 3

Small CPS 2Dock All Elements(crew transfer)

Utilize small

size CPS

3

EARTHEARTH

Small CPS 1, 2

SLS

Small CPS 1

Small CPS 1, 2, 3

Lunar Lander

SLS

Small CPS 1

MPCV

One possibility for Collaborated Mission Scenario

MOONMOON

Small CPS 2Small CPS 3

Small CPS 2Dock All Elements(crew transfer)

This idea could

utilize IP or

Commercial

Launchers

4

EARTHEARTH

Small CPS 1, 2

Small CPS 1

Small CPS 1, 2, 3

Lunar Lander

Small CPS 1

Crew Vehicle

Backup IP or commercial Launchers

・・・・・・・・・・・・ ・・・・・・・・・・・・

Small CPS Characteristics (notional)

� Length and Diameter will be around 10m x 4m

� Total weight will be 26 t

� Thrust will be around 60 klb

� Includes avionics, propulsion, and attitude

control for automated RVD, and power system

� Can be easily tailored to 2nd Stage for Other

Φ4m

10m

� Can be easily tailored to 2nd Stage for Other

Launcher

5

≒≒≒≒SmallCPS

2nd Stage for Other Launcher

Alternate Design Reference Mission Using SEP

5 d Transit

CPS 1

MOONMOON

100 km Low

Lunar Orbit

5 d Transit

CPS 2

Dock All Elements

(crew transfer)

~170 d

Transit

SEP

5 d Transit

CPS 2

Dock All Elements

(crew transfer)

6

LEO 407 km

x 407 km

EARTHEARTH

SLS

CPS 1

Lunar

Lander

SLS

Transit

SEP

Lunar

Lander

CPS 2

SLS

MPCV

with Crew

CPS 2

MPCV

with Crew

SEP

SEP Transportation and Concept

GTO(300××××36000km)

GTOInsertion LLO

(100km)

SEP

Lunar

Lander

7

LandingInsertion

(100km)

SEP Concept (Notional)Thrust: 10Ndelta V: 3500m/sPropellant: 8tPower: 200kWTotal Weight: 15t(*)P/L(Lunar Lander)=35t