This document describes the detailed design requirements and design criteria to support Structures/TPS Technology development for SSTO winged vehicle configurations that use vertical take-off and horizontal landing and delivers 25,000 lb payloads to a 220 nm circular orbit at an inclination of 51.6 degrees or 40,000 lb payloads to a 150 nm circular orbit at a 28.5 degree inclination.
Requirements Report for SSTO Vertical Take-off and Horizontal Landing Vehicle
1994
156 pages
Report
Keine Angabe
Englisch
Unmanned Spacecraft , Space Launch Vehicles & Support Equipment , Structural Mechanics , Design analysis , Launch vehicle configurations , Single stage to orbit vehicles , Spacecraft design , Structural design , Thermal protection , Circular orbits , Payloads , Requirements , Spacecraft launching , Weight analysis
An Assessment of Take-Off and Landing Modes for Reusable SSTO Launchers
British Library Conference Proceedings | 1994
|Online Contents | 1995
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