A hybrid approach to near-optimal launch vehicle guidanceThis paper evaluates a proposed hybrid analytical/numerical approach to launch-vehicle guidance for ascent to orbit injection. The feedback-guidance approach is based on a piecewise nearly analytic zero-order solution evaluated using a collocation method. The zero-order solution is then improved through a regular perturbation analysis, wherein the neglected dynamics are corrected in the first-order term. For real-time implementation, the guidance approach requires solving a set of small dimension nonlinear algebraic equations and performing quadrature. Assessment of performance and reliability are carried out through closed-loop simulation for a vertically launched 2-stage heavy-lift capacity vehicle to a low earth orbit. The solutions are compared with optimal solutions generated from a multiple shooting code. In the example the guidance approach delivers over 99.9 percent of optimal performance and terminal constraint accuracy.
Document ID
19920072529
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Leung, Martin S. K. (NASA Langley Research Center Hampton, VA, United States)
Calise, Anthony J. (Georgia Institute of Technology Atlanta, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1992
Subject Category
Launch Vehicles And Space Vehicles
Report/Patent Number
AIAA PAPER 92-4304
Meeting Information
Meeting: AIAA Guidance, Navigation and Control Conference