A first order orbital mechanics analysis was conducted to examine the possibility of utilizing the Space Shuttle Orbiter to perform payload delivery missions to lunar orbit. In the analysis, the earth orbit of departure was constrained to be that of Space Station Freedom. Furthermore, no enhancements of the Orbiter's thermal protection system were assumed. Therefore, earth orbit insertion maneuvers were constrained to be all propulsive. Only minimal constraints were placed on the lunar orbits and no consideration was given to possible landing sites for lunar surface payloads. The various phases and maneuvers of the mission are discussed for both a conventional (Apollo type) and an unconventional mission profile. The velocity impulses needed, and the propellant masses required are presented for all of the mission maneuvers. Maximum payload capabilities were determined for both of the mission profiles examined. In addition, other issues relating to the feasibility of such lunar shuttle missions are discussed. The results of the analysis indicate that the Shuttle Orbiter would be a poor vehicle for payload delivery missions to lunar orbit.
Feasibility Analysis of Cislunar Flight Using the Shuttle Orbiter
1991
24 pages
Report
Keine Angabe
Englisch
Manned Spacecraft , Unmanned Spacecraft , Cislunar space , Feasibility analysis , Landing sites , Lunar orbits , Orbit insertion , Orbital mechanics , Payload delivery (Sts) , Space shuttle orbiters , Earth orbits , Lunar surface , Payloads , Space shuttle missions , Space stations , Thermal protection
Space shuttle orbiter test flight series
NTRS | 1977
|Flight problem evaluation for Space Shuttle Orbiter
NTRS | 1987
|Shuttle Orbiter thermal control post-flight evaluation
AIAA | 1982
|Aerodynamic flight testing of the Space Shuttle Orbiter
NTRS | 1985
|