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Fuel-optimal trajectories of aeroassisted orbital transfer with plane changeThe problem of minimization of fuel consumption during the atmospheric portion of an aeroassisted, orbital transfer with plane change is addressed. The complete mission has required three characteristic velocities, a deorbit impulse at high earth orbit (HEO), a boost impulse at the atmospheric exit, and a reorbit impulse at low earth orbit (LEO). A performance index has been formulated as the sum of these three impulses. Application of optimal control principles has led to a nonlinear, two-point, boundary value problem which was solved by using a multiple shooting algorithm. The strategy for the atmospheric portion of the minimum-fuel transfer is to start initially with the maximum positive lift in order to recover from the downward plunge, and then to fly with a gradually decreasing lift such that the vehicle skips out of the atmosphere with a flight path angle near zero degrees.
Document ID
19890016653
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Naidu, Desineni Subbaramaiah (Old Dominion Univ. Norfolk, VA, United States)
Hibey, Joseph L. (Old Dominion Univ. Norfolk, VA, United States)
Date Acquired
September 6, 2013
Publication Date
June 30, 1989
Subject Category
Astrodynamics
Report/Patent Number
NASA-CR-185334
NAS 1.26:185334
Accession Number
89N26024
Funding Number(s)
CONTRACT_GRANT: NAG1-736
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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