A real-time guidance algorithm for aerospace plane optimal ascent to low earth orbitProblems of onboard trajectory optimization and synthesis of suitable guidance laws for ascent to low Earth orbit of an air-breathing, single-stage-to-orbit vehicle are addressed. A multimode propulsion system is assumed which incorporates turbojet, ramjet, Scramjet, and rocket engines. An algorithm for generating fuel-optimal climb profiles is presented. This algorithm results from the application of the minimum principle to a low-order dynamic model that includes angle-of-attack effects and the normal component of thrust. Maximum dynamic pressure and maximum aerodynamic heating rate constraints are considered. Switching conditions are derived which, under appropriate assumptions, govern optimal transition from one propulsion mode to another. A nonlinear transformation technique is employed to derived a feedback controller for tracking the computed trajectory. Numerical results illustrate the nature of the resulting fuel-optimal climb paths.
Document ID
19890066714
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Calise, A. J. (Georgia Inst. of Tech. Atlanta, GA, United States)
Flandro, G. A. (Georgia Institute of Technology Atlanta, United States)
Corban, J. E. (Georgia Inst. of Tech. Atlanta, GA, United States)