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Robust perturbation guidance for the advanced launch systemReal-time optimal trajectory generation for constructing guidance laws seems feasible. However, these deterministic guidance schemes may be sensitive to system and environmental uncertainties. To overcome this deficiency, it is suggested that the accessory problem about an optimal path, which generates a quadratic cost criterion in the perturbed states and control away from the optimal trajectory, be used as the cost criterion. A modified quadratic cost is minimized with respect to the perturbed control but maximized with respect to additive uncertainties in the linearized dynamics and in the linearized measurements. In this way, a robust neighboring optimum scheme is constructed. A perturbed guidance scheme is stated. To illustrate the theory, the second stage of a launch vehicle is considered. An optimal path is generated, and about this path a robust neighboring optimum guidance law is constructed and tested.
Document ID
19890066716
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Speyer, Jason L.
(Texas Univ. Austin, TX, United States)
Jarmark, Bernt S. A.
(Texas, University Austin, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1989
Subject Category
Launch Vehicles And Space Vehicles
Meeting Information
Meeting: 1989 American Control Conference
Location: Pittsburgh, PA
Country: United States
Start Date: June 21, 1989
End Date: June 23, 1989
Accession Number
89A54087
Funding Number(s)
CONTRACT_GRANT: NAG1-944
Distribution Limits
Public
Copyright
Other

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