This paper is a first look at the problems of building a lunar lander to support a small lunar surface base. A series of trade studies was performed to define the lander. The initial trades concerned choosing number of stages, payload mass, parking orbit altitude, and propellant type. Other important trades and issues included plane change capability, propellant loading and maintenance location, and reusability considerations. Given a rough baseline, the systems were then reviewed. A conceptual design was then produced. The process was carried through only one iteration. Many more iterations are needed. A transportation system using reusable, aerobraked orbital transfer vehicles (OTV's) is assumed. These OTV's are assumed to be based and maintained at a low Earth orbit (LEO) space station, optimized for transportation functions. Single- and two-stage OTV stacks are considered. The OTV's make the translunar injection (TLI), lunar orbit insertion (LOI), and trans-Earth injection (TEI) burns, as well as midcourse and perigee raise maneuvers.
Lunar Lander Conceptual Design
1992
13 pages
Report
No indication
English
Manned Spacecraft , Extraterrestrial Exploration , Lunar landing modules , Space transportation , Spacecraft design , Spacecraft propulsion , Hydrogen oxygen engines , Maintenance , Orbit insertion , Orbit transfer vehicles , Parking orbits , Payload mass ratio , Propellants , Spacecraft control , Translunar injection
Lunar lander conceptual design
NTRS | 1992
|Lunar Lander Conceptual Design
NTIS | 1989
|Lunar lander conceptual design
NTRS | 1989
|