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Limited variance control in statistical low thrust guidance analysisDifficulties arise in guiding a solar electric propulsion spacecraft due to nongravitational accelerations caused by random fluctuations in the magnitude and direction of the thrust vector. These difficulties may be handled by using a low thrust guidance law based on the linear-quadratic-Gaussian problem of stochastic control theory with a minimum terminal miss performance criterion. Explicit constraints are imposed on the variances of the control parameters, and an algorithm based on the Hilbert space extension of a parameter optimization method is presented for calculation of gains in the guidance law. The terminal navigation of a 1980 flyby mission to the comet Encke is used as an example.
Document ID
19760028316
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Jacobson, R. A.
(California Institute of Technology, Jet Propulsion Laboratory, Mission Analysis Div., Pasadena Calif., United States)
Date Acquired
August 8, 2013
Publication Date
July 1, 1975
Subject Category
Space Communications, Spacecraft Communications, Command And Tracking
Report/Patent Number
AAS PAPER 75-066
Meeting Information
Meeting: Astrodynamics Specialist Conference
Location: Nassau
Country: Bahamas
Start Date: July 28, 1975
End Date: July 30, 1975
Sponsors: American Astronautical Society and American Institute of Aeronautics and Astronautics
Accession Number
76A11282
Funding Number(s)
CONTRACT_GRANT: NAS7-100
Distribution Limits
Public
Copyright
Other

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