The De-orbiting Characteristic Of Satellites In Elliptical Orbit Using The Electrodynamic Tether System+

1957, the Soviet Union la unched the first artificia l earth satellite, in the next50 yea rs of space explora tion, it has also prod uced lots of abandoned satellitesand space debris, which are now posed a ma jor threat to the aircra ft in orbit. Forthe abandoned satellites and space debris, de-orbiting is a good way to reducethese , using cond uctive cable in the ground motion genera ted ma gnetic fieldLorentz force method of waste in orbit satellites from orbit is a promising method.This paper talks about the de-orbiting time cha racteristics of the satellites inelliptica l orbit with sma ll eccentricity using the electrod yna mic tether system indepthstudy, as follows :(1)Firstly, establish ing the ma gnetic field model, and giving the calcula tionabout the electrod yna mic force of the satellite in elliptica l orbit, which under theaction of the ma gnetic field model and processing the electrod yna mic tether asthe lumped mass system. Second ly, calcula ting the angle between theelectrod yna mic tether and the direction of the loca l vertica l,the angle betweenthe velocity direction of the satellite and the direction of the loca l level. Fina lly,accord ing to the establishment of the perturbation equations , a simula tion aboutthe satellite whose orbit is 800km above the ground of the earth was made forusing the electrod yna mic tether system for de-orbiting.(2)Further more,calcula ting the electrod yna mic force of the satellite inelliptica l orbit when the tether was modeled as a rigid body with distributed massthroughout the length, and making a simula tion about the de-orbiting of thesatellite, and comparing it with the result of the supra text. Besides, cha nging thepara meters of the orbit, ma inly were the initia l orbita l altitude , the initia l orbita leccentricity, the initia l orbit inclina tion angle , cha nges for these para meters were simulated, and ana lyzing the impact on the de-orbiting time .(3)Accord ing to the perturbation equations , giv ing an estima ted formula ofcalcula tion about the de-orbiting time of the satellite, and comparing it with thesimula tion result. Putting the emphasis on the influence of the perturbations ofthe atmosphere drag and the Earth's eccentricity on the de-orbiting time andmaking a simula tion on these. Fina lly, making a simula tion when the para metersof the electrod yna mic tether cha nged (the length, the cross-sectiona l area ), andana lyz ing the impact on the de-orbiting time.