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Inclusion of known integrals in the optimal trajectory problemThe classical problem of determination of the rocket trajectory which minimizes mass expenditure during motion between two points in the field of a single gravitating body is analyzed. The known integrals of the system are incorporated into the adjoint equations resulting in a reduction from a seventh-order adjoint system to a third-order adjoint system. The first case which is treated in that of planar motion under specific end conditions. In this case a regularization of the recently derived equations is achieved. The general three-dimensional case is also reduced from a seventh-order adjoint system to a third-order adjoint system. In this case a regularization has not been found.
Document ID
19740008424
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Burns, R. E. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Date Acquired
September 3, 2013
Publication Date
February 1, 1974
Subject Category
Space Sciences
Report/Patent Number
M-125
NASA-TN-D-7592
Accession Number
74N16537
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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