Dual Lander Mission (original) (raw)

Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z

Dual Lander Mission

Part of American Mars Expeditions

Combo Lander
Credit: NASA

American manned Mars expedition. Study 1999. After some discussion within NASA, in the Combo Lander mission was found to be too lean.

Status: Study 1999.

It was again reformulated as a Design Reference-Mission type with two landers, six crew sent on two different opportunities, and ISRU production on the surface, and split cargo/crew landers to provide more redundancy. Even with the mass-saving advanced technology assumptions of the Combo Lander study, this drove the total mass required in Low Earth Orbit back to 600 metric tons, and the number of heavy lift launch vehicle launches to 12.

Dual Lander Mission Summary:

Summary: Follow-on of combo lander study - back to 2 landers; no formal report, presentation charts only
Propulsion: Solar electric/Lox/LH2
Braking at Mars: aerodynamic
Mission Type: conjunction
Split or All-Up: split
ISRU: ISRU
Launch Year: 2011
Crew: 12
Mars Surface payload-metric tons: 35
Outbound time-days: 200
Mars Stay Time-days: 600
Return Time-days: 210
Total Mission Time-days: 1010
Total Payload Required in Low Earth Orbit-metric tons: 600
Total Propellant Required-metric tons: 110
Propellant Fraction: 0.18
Mass per crew-metric tons: 100
Launch Vehicle Payload to LEO-metric tons: 75
Number of Launches Required to Assemble Payload in Low Earth Orbit: 12
Launch Vehicle: Magnum

Family: Mars Expeditions. Country: USA. Agency: NASA. Bibliography: 1989.

Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z