An investigation has been conducted to determine preliminary wing designs for a single-stage-to-orbit (SSTO) vehicle. This vehicle has the following mission profile: vertical takeoff, boost-to-orbit, hypersonic reentry, and horizontal landing. For this vehicle, the wing is sized to meet Space Shuttle reentry aerodynamic requirements for hypersonic trim and horizontal landing, since reentry trajectories for the Shuttle and the SSTO vehicle are similar. A hypersonic and subsonic aerodynamic computer program was developed and combined with an existing optimization algorithm to automatically size and shape a wing which satisfies both reentry and landing requirements while also maintaining a minimum mass design. With this procedure, the influence of hypersonic and subsonic aerodynamic requirements, control surface size, and center-of-gravity positions on the initial wing design were investigated.
Optimum wing sizing of a single-stage-to-orbit vehicle
Aerospace Sciences Meeting ; 1982 ; Orlando, FL
1982-01-01
Conference paper
No indication
English
Optimum wing sizing of a single-stage-to-orbit vehicle
AIAA | 1982
|Optimum wing sizing of a single-stage-to-orbit vehicle
NTRS | 1983
|Optimum wing sizing of a single-stage-to-orbit vehicle
AIAA | 1983
|