Mathematical models of the orbital motion of spacecraft with electric propulsion are considered. The equations of spacecraft motion are given. An auxiliary longitude used as a new independent variable in a number of problems is introduced. Boundary conditions for typical problems of low-thrust trajectory optimization, description of methods of calculation of main perturbing accelerations and peculiarities of applied methods of numerical integration of spacecraft equations of motion are given. Typical optimization problems of spacecraft trajectories with electric propulsion are described, which are reduced to boundary value problems for systems of ordinary differential equations using the maximum principle. The continuation method for solving these boundary value problems is described. Formulations of the problems of optimization of spacecraft trajectories with engines of limited power and limited thrust are given. The design model of spacecraft for the problem of joint optimization of trajectory and main design parameters is considered.
Mathematical Models of a Spacecraft with an Electric Propulsion for Trajectory Optimization Problems
Studies in Systems, Decision and Control
Through Optimization of Aerospace Vehicle Trajectories by the Pontryagin Maximum Principle ; Chapter : 7 ; 309-348
2025-05-29
40 pages
Article/Chapter (Book)
Electronic Resource
English
Pontryagin maximum principle , Boundary value problem , Continuation method , Complex step differentiation , Low-thrust trajectory optimization , Limited power problem , Limited thrust problem Engineering , Aerospace Technology and Astronautics , Optimization , Control and Systems Theory , Computational Intelligence , Mechanical Engineering
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