Minimum fuel trajectory for the aerospace-planeAn overall trajectory for a single-stage-to-orbit vehicle with an initial weight of 234 tons is calculated, and four different propulsion models including turbojet, ramjet, scramjet, and rocket are considered. First, the atmospheric flight in the thicker atmosphere is discussed with emphasis on trajectory optimization, optimization problem, aerodynamic problem, propulsion model, and initial conditions. The performance of turbojet and ramjet-scramjet engines is analyzed; and then the flight to orbit is assessed from the optimization point of view. It is shown that roll modulation saves little during the trajectory, and the combined application of airbreathing propulsion and aerodynamic lift is suggested.
Document ID
19900059730
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Breakwell, John V. (Stanford University CA, United States)
Golan, Oded (Stanford Univ. CA, United States)
Sauvageot, Anne (Stanford Univ. CA, United States)