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Low-thrust perturbation guidance

Citation

Bauer, Thomas Patrick (1982) Low-thrust perturbation guidance. Dissertation (Ph.D.), California Institute of Technology. http://resolver.caltech.edu/CaltechETD:etd-08122005-133355

Abstract

Low-thrust perturbation guidance, as applied to the minimum time problem of an Earth to Mars rendezvous, has been reexamined and shown to perform orders of magnitude better, as measured by the terminal state error, than previous studies indicated. The orbits of Earth and Mars were assumed to be inclined and elliptical. The only forces considered were the Sun's gravity and that of the constant thrust rocket engine. First order necessary conditions of the calculus of variations were developed for the nominal trajectory. The resulting nonlinear two-point boundary value problem was solved with the Backward Sweep Method. Feedback gain related and trajectory information is stored on a file during the optimization of the nominal trajectory to be retrieved later in the guidance programs by a high order interpolator. Two guidance schemes, Time-To-Go Guidance and Minimum Distance Guidance, were investigated for several initial perturbations in velocity and position. The performance of the two schemes was found to be clearly acceptable although not quite as good as reoptimization. The two schemes are equivalent in performance. Moreover, a simplified version of the schemes, Current Time Guidance, was found to be comparable in performance to the more elaborate guidance schemes. A comparison of the current results with those of previous studies was made showing that terminal state errors can be reduced 100 to 10,000 times more than found earlier. This apparent improvement may possibly be explained by the use of a high fidelity integrator and other enhancements implemented in the software, although algorithm and programming mistakes in the earlier studies are suspected. A similar minimum time problem, that of a two-dimensional Earth to Mars orbit transfer using a solar sail, was also reexamined. The optimized trajectory was found to be very similar to those obtained by most earlier studies. A recent report which prompted the study was found to have an error in a transversality condition causing anomalous results.

Item Type:Thesis (Dissertation (Ph.D.))
Subject Keywords:Earth-Mars trajectories, feedback control, low thrust, spacecraft guidance, trajectory control, transfer orbits, optimal control, orbit pertubation, position errors, terminal guidance, trajectory optimization
Degree Grantor:California Institute of Technology
Division:Engineering and Applied Science
Major Option:Aeronautics
Thesis Availability:Public (worldwide access)
Research Advisor(s):
  • Caughey, Thomas Kirk
Thesis Committee:
  • Caughey, Thomas Kirk (chair)
  • Zukoski, Edward E.
  • Culick, Fred E. C.
  • Stewart, Homer Joseph
  • Wood, Lincoln
Defense Date:25 May 1982
Record Number:CaltechETD:etd-08122005-133355
Persistent URL:http://resolver.caltech.edu/CaltechETD:etd-08122005-133355
Default Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:3101
Collection:CaltechTHESIS
Deposited By: Imported from ETD-db
Deposited On:12 Aug 2005
Last Modified:26 Dec 2012 02:57

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