Evaluation of an optimal guidance algorithm for aero-assisted orbit transferA detailed evaluation is performed of a guidance algorithm for aeroassisted orbit transfer that was developed earlier based on the method of matched asymptotic expansions. It is shown that, by exploiting the structure of the matched asymptotic expansion solution procedure, the original problem which requires the solution of a set of 20 implicit algebraic equations can be reduced to a problem of six implicit equations in six unknowns. The main contribution here is that it was possible to obtain a solution that is near optimal, requires a minimum of computation, and thus can be implemented in real time and on-board the vehicle. Guidance law implementation entails treating the current state as a new initial state and repetitively solving the matched asymptotic expansion problem to obtain the feedback controls.
Document ID
19920072591
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Melamed, N. (NASA Langley Research Center Hampton, VA, United States)
Calise, A. J. (Georgia Institute of Technology Atlanta, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1992
Subject Category
Astrodynamics
Report/Patent Number
AIAA PAPER 92-4454
Meeting Information
Meeting: AIAA Guidance, Navigation and Control Conference