The NASA Multimission Modular Spacecraft (MMS) consists of standard functional modules (power, attitude control and command and data handling) assembled on a central structure, capable of supporting a variety of experiments/payloads in a wide range of orbits, and is being designed for launch on expendable launch vehicles or the Shuttle. Depending on specific mission requirements, additional modules may be added, including a Propulsion Module (PM) for orbit and/or attitude control. The Delta-launched MMS for the Goddard Space Flight Center (GSFC) Landsat-D mission requires such a module, designated PM-I, that utilizes 0.2 and 5 lbf catalytic hydrazine thrusters. The PM-I (and its growth versions) are truly modular, being separable as a unit from the MMS in orbit, if necessary. The paper presents redundancy trade-offs for valve, thruster and electronic configurations as well as design and implementation alternatives involving the removable Rocket Engine Modules (REM's), the control electronics, thermal elements and mechanical interfaces. Components, command control, telemetry, integration, test and GSE are described. (Kursetz)
MMS propulsion module design
Konstruktion eines Antriebssystems fuer ein Mehrzweckraumfahrzeug
AIAA-Papers ; 1-9
1978
9 Seiten, 17 Bilder, 5 Tabellen
Aufsatz (Konferenz)
Englisch
AIAA | 1978
|SLUB | 1984
SLUB | 1984