Innovative Approach for Solar Sail Periodic Orbits Identification in Non-Autonomous Circular Restricted Three-Body Systems
Document Type : selected article
Authors
1
School of Aerospace engineering, College of Interdisciplinary Science and Technologies, University of Tehran, North Kargar Street, Tehran, Iran.
2
University of Tehran
3
School of Advanced Technologies - Iran University of Science and Technology
Abstract
Solar sails are currently being widely used for various space applications, including deep space missions. While most of these applications are studied within the framework of the Sun-Earth three-body problem, limited research has been conducted to explore the potential of solar sails in the Earth-Moon three-body problem. The aim of this paper is to identify new periodic orbits for solar sails within the context of the Earth-Moon three-body problem. By incorporating the acceleration caused by solar sail radiation pressure into the Earth-Moon three-body problem, the system becomes non-autonomous, requiring different methods for extracting periodic orbits. In this study, the identification of periodic orbits for solar sails in the circular restricted Earth-Moon three-body problem is formulated as a two-point boundary value problem. Initially, preliminary guesses for periodic orbits of a simple spacecraft, without considering solar sail acceleration, are obtained using a Poincaré map. Then, the precise initial conditions for the periodic orbits of the solar sail are determined through a differential correction algorithm. To validate the proposed approach, the resulting orbits are plotted and their stability is compared with the periodic orbits of a spacecraft without a solar sail.
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Volume 5, Issue 2
March 2026Pages 14-22
- Receive Date 28 June 2024
- Revise Date 23 December 2024
- Accept Date 05 February 2025