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• W2608532373 abstract "This chapter is devoted to a tether-assisted reentry capsule return mission. The mathematical model of the space tethered system is given. Simplified equations are obtained for the case of the deployed tether. Analytic solutions for satellite motion around its center of mass under the influence of the gravitational moment and tether tension force are given for the cases of slow change of tension force and tether deflection from the local vertical, of small oscillations of the satellite axis around the tether line, of the satellite oscillations near local vertical. Evaluation of microaccelerations on board the satellite is carried out using these solutions. A particular case of the satellite oscillations with a vertical elastic tether in a circular orbit is considered. The bifurcation diagram is constructed, and the hetero- and homoclinic separatrix trajectories are determined. Melnikov's method is used to study the satellite chaotic behavior near separatrices under the action of the periodic tether tension force. It is shown that elastic tether oscillations can result in appearance of chaotic modes of spacecraft motion. The condition of chaos existence, which allows to determine the measure of damping sufficient for prevention of chaotic modes, is obtained. The influence of mass, geometric, and elastic characteristics on the form of phase portrait and on the value of periodic disturbance, caused by oscillations of the elastic vertical tether, is studied. Influence of the orbit eccentricity on the space tether system motion is considered in this chapter. The control law that allows to increase the deflection angle of the tether from the local vertical is offered. The control law is based on a principle of a swing. An approximate analytic solution for the deflection angle from the local vertical is obtained for the control law, and stability of the tether vertical position under the proposed control is investigated. The problem of a payload delivery from an elliptical orbit taking into account atmospheric stage of reentry is considered. The tether deployment should provide the transition of the payload into a trajectory with the permissible loads. The conditions of the payload separation from the tether, which provide minimization of dynamic or thermal loads during the atmospheric motion or minimization of a perigee radius of the payload orbit, are studied." @default.
• W2608532373 created "2017-05-05" @default.
• W2608532373 creator A5002760882 @default.
• W2608532373 date "2017-01-01" @default.
• W2608532373 modified "2023-09-25" @default.
• W2608532373 title "Deployment, Dynamics, and Control of a Tether-Assisted Return Mission of a Reentry Capsule" @default.
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• W2608532373 doi "https://doi.org/10.1016/b978-0-12-811094-2.00004-2" @default.
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