"Simulation and Controller Design for Satellites in Formation Flying"
Vengada Ganeshwaran, S. Lakshmi, J. Shanmugam
Formation flying is a new paradigm in a space mission design aimed at replacing large satellite with multiple small satellites. Some of the proposed benefits of formation flying satellites are reduced mission costs and multi-mission capabilities achieved through the reconfiguration of formation. This paper presents the control law for absolute station keeping of the satellite which had been done by classical orbital element feedback control, in which orbital element feedback gains had been selected by using genetic algorithm for the orbit maintenance of the satellites. The disturbance in leader follower formation in near polar low earth orbit due to eccentricity of master, with initial positions of satellites determined by using the solution of Euler-Hill equation of relative motion. Euler-Hill equations describe the linearised dynamics of satellite (Deputy) with respect to another (Master) which is assumed to move in a circular orbit. Given the initial conditions of master satellite, the initial conditions of the Deputy satellite had been found for leader-Follower, Projected circular and general circular formation of satellites. The variation in orbital elements of satellites in formation flying had been found by using Gaussian Planetary equation which had been used in the control law.
Key-Words:- Formation Flying, Leader-Follower Formation, Euler-hill Equation, Master Orbit Eccentricity, Disturbance In The Formation, Perturbation Effects, Gaussian Planetary Equation, Station Keeping, Orbital Element Control, Genetic Algorithm.
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