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Fuel optimal maneuvers for spacecraft with fixed thrustersSeveral mathematical models, including a minimum integral square criterion problem, were used for the qualitative investigation of fuel optimal maneuvers for spacecraft with fixed thrusters. The solutions consist of intervals of "full thrust" and "coast" indicating that thrusters do not need to be designed as "throttleable" for fuel optimal performance. For the primary model considered, singular solutions occur only if the optimal solution is "pure translation". "Time optimal" singular solutions can be found which consist of intervals of "coast" and "full thrust". The shape of the optimal fuel consumption curve as a function of flight time was found to depend on whether or not the initial state is in the region admitting singular solutions. Comparisons of fuel optimal maneuvers in deep space with those relative to a point in circular orbit indicate that qualitative differences in the solutions can occur. Computation of fuel consumption for certain "pure translation" cases indicates that considerable savings in fuel can result from the fuel optimal maneuvers.
Document ID
19820009172
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Carter, T. C.
(Eastern Connecticut State Coll. Willimantic, CT, United States)
Date Acquired
August 10, 2013
Publication Date
January 1, 1982
Publication Information
Publication: Alabama Univ. in Huntsville The 1981 NASA(ASEE Summer Fac. Fellowship Program
Subject Category
Spacecraft Design, Testing And Performance
Accession Number
82N17046
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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