In this paper, we present a review of nonlinear semi‐analytic methods for spacecraft trajectory design, control, and navigation. We first discuss previous and recent development of higher‐order relative dynamics theory for a general dynamical system and stress the importance of incorporating the system nonlinearity in the model. For a given reference trajectory, the localized nonlinear dynamics is represented by the higher order state transition tensors, which are computed numerically by integrating the higher order Taylor series terms. We then analytically propagate the a priori Gaussian probability density function via solutions of the Fokker‐Planck equations and compute the associated moments, such as the mean and covariance matrix. Using this analytic realization of the system dynamics and statistics, we derive analytic methods which allows one to propagate, control, and estimate the spacecraft trajectory while incorporating the system nonlinearity. As examples, three‐body problems are considered and the results are compared with first‐order (linear) methods.
Nonlinear Semi‐Analytic Methods for Spacecraft Trajectory Design, Control, and Navigation
NEW TRENDS IN ASTRODYNAMICS AND APPLICATIONS III ; 2006 ; Princeton, New Jersey (USA)
AIP Conference Proceedings ; 886 , 1 ; 78-89
07.02.2007
12 pages
Aufsatz (Konferenz)
Elektronische Ressource
Englisch
Nonlinear Semi-Analytic Method for Spacecraft Navigation
AIAA | 2006
|Nonlinear Semi-Analytic Method for Spacecraft Navigation AIAA Paper 2006-6399
British Library Conference Proceedings | 2006
|Nonlinear Semi-Analytic Methods for Trajectory Estimation
Online Contents | 2007
|Nonlinear Predictive Control for Spacecraft Trajectory Guidance, Navigation and Control
British Library Conference Proceedings | 1998
|