An 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.
Minimum fuel trajectory for the aerospace-plane
AAS/AIAA Astrodynamics Conference 1989 ; 1989 ; Stowe, VT, United States
1990-01-01
Conference paper
No indication
English
Trajectory optimization for the national aerospace plane
NTRS | 1993
|Trajectory Optimization for the National Aerospace Plane
NTIS | 1993
|Trajectory Optimization for the National Aerospace Plane
NTIS | 1993
|Trajectory optimization for the National aerospace plane
NTRS | 1993
|Trajectory optimization for the National Aerospace Plane
NTRS | 1993
|