Preliminary Static Aeroelastic Analysis of Reusable Launch Vehicle Stability and Control Derivatives

摘要

Durign the development and design of the X-33 reusable launch vehicle, loads and control analyses had been done using propulsive and aerodynamic loads derived from such sources as computational fluid dynamics and wind-tunnel models of a rigid vehicle. Required control forces and moments were determined using rigid vehicle trajectory analyses, and the detailed control load distributions were determined for achieving the required control forces and moments, again using rigid vehicle analyses.