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Analytic Gradient Computation for Bounded-Impulse Trajectory Models Using Two-Sided Shooting.

Donald H Ellison1, Bruce A Conway1, Jacob A Englander2

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Journal of Guidance, Control, and Dynamics : a Publication of the American Institute of Aeronautics and Astronautics Devoted to the Technology of Dynamics and Control
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Summary
This summary is machine-generated.

Analytic methods for computing complex partial derivatives in space mission trajectory optimization are presented. These methods improve computational efficiency and accuracy for low-thrust and deep-space maneuvers.

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Area of Science:

  • Astrodynamics
  • Optimization Theory
  • Computational Mathematics

Background:

  • Optimization methods in astrodynamics often require accurate partial derivative information for convergence.
  • Existing methods for computing derivatives can be computationally intensive or less accurate.

Purpose of the Study:

  • To develop analytic methods for computing complex partial derivatives of bounded-impulse trajectory models.
  • To address the match point defect constraint and extend gradient computations for trajectory path constraints.

Main Methods:

  • Analytic differentiation applied to multiple gravity-assist low-thrust trajectory models.
  • Shooting transcription methods for bounded-impulse trajectory optimization.
  • Extension of gradient computations to include trajectory path constraints.

Main Results:

  • Efficient and accurate computation of partial derivatives for complex trajectory models.
  • Demonstrated benefits in a comet sample return mission design problem.
  • Outperformed automatic differentiation and finite differences in computational efficiency.

Conclusions:

  • Analytic gradient computation offers significant advantages for trajectory optimization.
  • The developed methods enhance the efficiency and robustness of space mission design.
  • These techniques are crucial for complex astrodynamical problems.