Optimization for Multitarget, Multispacecraft Impulsive Rendezvous Considering J2 Perturbation

2021 ◽  
pp. 1-12
Author(s):  
Shiyu Chen ◽  
Fanghua Jiang ◽  
Haiyang Li ◽  
Hexi Baoyin
Keyword(s):  
J2 Perturbation

Orbit determination for fuel station in multiple SSO spacecraft refueling considering the J2 perturbation

2020 ◽  
Vol 105 ◽  
pp. 105994
Author(s):  
Xiaoyu Zhu ◽  
Chengxi Zhang ◽  
Ran Sun ◽  
Junli Chen ◽  
Xiangcheng Wan
Keyword(s):  
Orbit Determination ◽  
J2 Perturbation

Teardrop hovering formation for elliptical orbit considering J2 perturbation

2020 ◽  
Vol 106 ◽  
pp. 106098
Author(s):  
Shengzhou Bai ◽  
Chao Han ◽  
Xiucong Sun ◽  
Hongli Zhang ◽  
Yiping Jiang
Keyword(s):  
Elliptical Orbit ◽  
J2 Perturbation

Active Collision Avoidance Control for Fractionated Satellite Clusters in Ellipse Orbit

2012 ◽  
Vol 433-440 ◽  
pp. 4989-4996
Author(s):  
Wei Wei Yang ◽  
Lu Cao ◽  
Yong Zhao ◽  
Xiao Qiang Chen
Keyword(s):  
Collision Avoidance ◽  
Minimum Distance ◽  
Automatic Differentiation ◽  
Collision Probability ◽  
J2 Perturbation ◽  
Collision Avoidance Control ◽  
Relative Dynamics ◽  
Avoidance Control ◽  
Satellite Clusters ◽  
Structure Configuration

The active collision avoidance maneuver of fractionated satellite cluster is studied. Especially, two clusters with different structure configuration in ellipse orbit and the collision description method between them are discussed. Due to the limitation of the collision probability based on the minimum distance, a new method is developed which including the effect of relative velocity on collision. Only J2 perturbation is considered in the relative dynamics and a PD controller based on BP neural network using automatic differentiation method is adopted when a collision is imminent. The simulation results validate that the presented active collision avoidance control law is effective.

Satellite formation keeping via chaotic artificial bee colony

2017 ◽  
Vol 89 (2) ◽  
pp. 246-256 ◽  
Author(s):  
Soyinka Olukunle Kolawole ◽  
Duan Haibin
Keyword(s):  
Artificial Bee Colony Algorithm ◽  
Artificial Bee Colony ◽  
Feedback Controller ◽  
Experimental Results ◽  
Effective Control ◽  
Satellite Formation ◽  
Content Type ◽  
Optimal Feedback ◽  
Bee Colony ◽  
J2 Perturbation

Purpose Keeping satellite position within close tolerances is key for the utilization of satellite formations for space missions. The presence of perturbation forces makes control inevitable if such mission objective is to be realised. Various approaches have been used to obtain feedback controller parameters for satellites in a formation; this paper aims to approach the problem of estimating the optimal feedback parameter for a leader–follower pair of satellites in a small eccentric orbit using nature-based search algorithms. Design/methodology/approach The chaotic artificial bee colony algorithm is a variant of the basic artificial bee colony algorithm. The algorithm mimics the behaviour of bees in their search for food sources. This paper uses the algorithm in optimizing feedback controller parameters for a satellite formation control problem. The problem is formulated to optimize the controller parameters while minimizing a fuel- and state-dependent cost function. The dynamical model of the satellite is based on Gauss variational equations with J2 perturbation. Detailed implementation of the procedure is provided, and experimental results of using the algorithm are also presented to show feasibility of the method. Findings The experimental results indicate the feasibility of this approach, clearly showing the effective control of the transients that arise because of J2 perturbation. Originality/value This paper applied a swarm intelligence approach to the problem of estimating optimal feedback control parameter for a pair of satellites in a formation.

Satellite formation keeping using differential lift and drag under J2 perturbation

2017 ◽  
Vol 89 (1) ◽  
pp. 11-19 ◽  
Author(s):  
Xiaowei Shao ◽  
Mingxuan Song ◽  
Jihe Wang ◽  
Dexin Zhang ◽  
Junli Chen
Keyword(s):  
Control Strategy ◽  
Tracking Error ◽  
Flat Plates ◽  
Satellite Formation ◽  
Content Type ◽  
Small Satellites ◽  
J2 Perturbation ◽  
Simulation Results ◽  
Lift And Drag ◽  
Formation Keeping

Purpose The purpose of this paper is to present a method to achieve small satellite formation keeping operations by using the differential lift and drag to control the drift caused by J2 perturbation in circular or near-circular low earth orbits (LEOs). Design/methodology/approach Each spacecraft is equipped with five large flat plates, which can be controlled to generate differential accelerations. The aerodynamic lift and drag acting on a flat plate is calculated by the kinetic theory. To maintain the formation within tracking error bounds in the presence of J2 perturbation, a nonlinear Lyapunov-based feedback control law is designed. Findings Simulation results demonstrate that the proposed method is efficient for the satellite formation keeping and better accuracy advantage in comparison with classical approaches via the fixed maximum differential aerodynamic acceleration. Research limitations/implications Because the aerodynamic force will reduce drastically as the orbital altitude increases, the formation keeping control strategy for small satellites presented in this paper should be limited to the scenarios when satellites are in LEO. Practical implications The formation keeping control method in this paper can be applied to solve satellite formation keeping problem for small satellites in LEO. Originality/value This paper proposes a Lyapunov control strategy for satellite formation keeping considering both lift and drag forces, and simulation results show better performance with high accuracy under J2 perturbation.

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