Open Access

ARTICLE

Method for Collision Avoidance in Spacecraft Rendezvous Problems with Space Objects in a Phasing Orbit

Danhe Chen^1,*, A. A. Baranov², Chuangge Wang¹, M. O. Karatunov³, N. Yu. Makarov³

1 Nanjing University of Science and Technology, Nanjing, 210094, China
2 Keldysh Institute of Applied Mathematics, Russian Academy of Sciences, Moscow, Russia
3 Peoples’ Friendship University of Russia (RUDN University), Moscow, Russia

* Corresponding Author: Danhe Chen. Email:

(This article belongs to the Special Issue: Modeling and Analysis of Autonomous Intelligence)

Computer Modeling in Engineering & Sciences 2021, 127(3), 977-991. https://doi.org/10.32604/cmes.2021.014662

Received 18 October 2020; Accepted 13 January 2021; Issue published 24 May 2021

Abstract

As the number of space objects (SO) increases, collision avoidance problem in the rendezvous tasks or re-constellation of satellites with SO has been paid more attention, and the dangerous area of a possible collision should be derived. In this paper, a maneuvering method is proposed for avoiding collision with a space debris object in the phasing orbit of the initial optimal solution. Accordingly, based on the plane of eccentricity vector components, relevant dangerous area which is bounded by two parallel lines is formulated. The axises of eccentricity vector system pass through the end of eccentricity vector of phasing orbit in the optimal solution, and orientation of axis depends on the latitude argument where a collision will occur. The dangerous area is represented especially with the graphical dialogue, and it allows to find a compromise between the SO avoiding and the fuel consumption reduction. The proposed method to solve the collision avoidance problem provides simplicity to calculate rendezvous maneuvers, and possibility to avoid collisions from several collisions or from “slow” collisions in a phasing orbit, when the protected spacecraft and the object fly dangerously close to each other for a long period.

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Keywords

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