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Optimal control of spacecraft motion in the vicinity of Eros 433 asteroid
- Authors: Shornikov A.Y.1
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Affiliations:
- Samara National Research University
- Issue: Vol 18, No 4 (2019)
- Pages: 146-156
- Section: AIRCRAFT AND SPACE ROCKET ENGINEERING
- URL: https://journals.ssau.ru/vestnik/article/view/7622
- DOI: https://doi.org/10.18287/2541-7533-2019-18-4-146-156
- ID: 7622
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Abstract
The article describes an algorithm for optimizing controlled motion of a spacecraft equipped with low-thrust electric propulsion engines maneuvering in the vicinity of an object with an irregular gravitational field (asteroid Eros 433). A mathematical model of the object’s gravitational potential and a model of spacecraft motion are presented. The Pontryagin maximum principle is used to get the time-optimal control program. The formulated boundary value problem is solved numerically by the modified Newton method. The described algorithm can be used to solve similar problems of low-thrust flight dynamics in the vicinity of objects with irregular gravitational fields.
About the authors
A. Yu. Shornikov
Samara National Research University
Author for correspondence.
Email: andreishornikov@gmail.com
Postgraduate Student, Department of Space Engineering
Russian FederationReferences
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