This paper examines two concepts for a reusable military launch system (RMLS). Both are rocket powered vertical takeoff-horizontal landing configurations. One is a conventional wing-body configuration like the Space Shuttle, and the other is a lifting body configuration. The lifting body design lands in an inverted attitude, which significantly reduces the maintenance requirements for the vehicle's thermal protection system. The longitudinal stability and control characteristics are examined, and footprint calculations are made for re-entry.
Longitudinal Control and Footprint Analysis for a Reusable Military Launch Vehicle
2003
12 pages
Report
No indication
English
Footprint calculation for a reusable launch vehicle based on dynamics programming
Tema Archive | 2009
|Online Contents | 1994