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Optimal control of aeroassisted plane change maneuver using feedback expansionsA guidance law for an aeroassisted plane change maneuver is developed by an asymptotic expansion technique using a small parameter which essentially represents the ratio of the inertial forces to the atmospheric forces. This guidance law minimizes the energy loss while meeting terminal constraints on the altitude, flight path angle, and heading angle. By neglecting the inertial forces, the resulting optimization problem is integrable and can be determined in closed form. This zeroth-order solution is the first term in an asymptotic series solution of the Hamilton-Jacobi-Bellman equation. The remaining terms are determined from the solution of a first-order, linear partial differential equation whose solution requires only quadrature integration. Our initial results in using this guidance scheme are encouraging.
Document ID
19860062943
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Mishne, D.
(Texas Univ. Austin, TX, United States)
Speyer, J. L.
(Texas, University Austin, United States)
Date Acquired
August 12, 2013
Publication Date
January 1, 1986
Subject Category
Astrodynamics
Report/Patent Number
AIAA PAPER 86-2136
Accession Number
86A47681
Funding Number(s)
CONTRACT_GRANT: JPL-956414
Distribution Limits
Public
Copyright
Other

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