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Finite burn maneuver modeling for a generalized spacecraft trajectory design and optimization system
1Department of Aerospace Engineering and Engineering Mechanics, The University of Texas at Austin, Austin, TX 78712, USA. cesar.ocampo@mail.utexas.edu
Annals of the New York Academy of Sciences
|June 29, 2004
Summary
This study presents a unified framework for designing and optimizing spacecraft trajectories with finite engine burns. It addresses complex maneuvers in various force fields using optimal control theory and numerical methods.
Area of Science:
- Aerospace Engineering
- Astrodynamics
- Computational Mathematics
Background:
- Spacecraft trajectory design often involves complex maneuvers with finite thrust.
- Existing systems may struggle with generalized frameworks for diverse mission requirements.
- Optimization of finite burn maneuvers is crucial for mission efficiency and success.
Purpose of the Study:
- To present a generalized trajectory design and optimization system.
- To model, design, and optimize finite burn maneuvers for complex spacecraft trajectories.
- To provide a unified framework for arbitrary force fields and multiple propulsion systems.
Main Methods:
- Application of optimal control theory for maneuver optimization.
- Development of numerical methods including nonlinear equation systems and parameter optimization.
- Implementation within the Copernicus prototype system.
Main Results:
- A generalized system capable of handling complex spacecraft trajectories is developed.
- Methods for optimizing finite thrust maneuvers in arbitrary, time-dependent force fields are established.
- The framework facilitates the use of multiple propulsion systems and spacecraft.
Conclusions:
- The developed system and methods enable efficient design and optimization of finite thrust trajectories.
- The unified framework enhances the flexibility and capability of trajectory design tools.
- Copernicus serves as a prototype for advanced trajectory design and optimization.