Date of Award:
5-2014
Document Type:
Dissertation
Degree Name:
Doctor of Philosophy (PhD)
Department:
Mechanical and Aerospace Engineering
Committee Chair(s)
David K. Geller
Committee
David K. Geller
Committee
Jacob H. Gunther
Committee
Warren F. Phillips
Committee
Charles M. Swenson
Committee
Stephen A. Whitmore
Abstract
Traditional spacecraft guidance techniques have the objective of deterministically minimizing fuel consumption. These traditional approaches to guidance are developed independently of the navigation system, and without regard to stochastic effects. This work presents and demonstrates a new approach to guidance design. This new approach seeks to maximize the probability of mission success by minimizing the variance of trajectory dispersions subject to a fuel consumption constraint. The fuel consumption constraint is imposed by formulating the dynamics in terms of a steering command, and placing a constraint on the final time. Stochastic quadratic synthesis is then used to solve for the nominal control along with the estimator and feedback gains. This new approach to guidance is demonstrated by solving a simple Zermelo boat problem. This example shows that a significant reduction in terminal dispersions is possible with small increases to fuel budgeted for the maneuver.
Checksum
8cd03d984f1d6b351abe630f62d398b3
Recommended Citation
Robinson, Shane B., "Spacecraft Guidance Techniques for Maximizing Mission Success" (2014). All Graduate Theses and Dissertations, Spring 1920 to Summer 2023. 2175.
https://digitalcommons.usu.edu/etd/2175
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