Use of a lifting upper stage to achieve large offsets during ascent to orbit.

摘要: Aerodynamic maneuvers performed by a lifting spacecraft boosted to near orbital velocity were studied as means of reducing tbe requirements for the offset maneuver necessary when desired final orbit plane does not pass through launch site. When aerodynamic are during gliding flight, gradient technique used with digital trajectory simulation showed optimum bank angle be zero at beginning glide and increase gradually until is attained. This inverse decreasing program obtained investigators maximum re-entry cross-range problem. Analytic calculations based on great minor circle flight approximated (but programs). Effective determined analytically constant-speed cruise found competitive results. Compared conventional impulsive outside atmosphere, substantial decreases in requirement either mode realized lift-to-drag ratio 1.3 or greater. Scramjet propulsion cruising type was considered providing modest propellant fraction requirements.