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• W2318193294 abstract "The vast potential of tethered satellite system IS now well recognized. One of the very useful application is the momentum transfer. Raising a payload by deploying it upward from a orbiter on a long tether and then releasing it represent a rather important possible one involving significant fuel econornv. In this paper ,the dynamic model of a two-body tethered satellite system is first set up,two control laws of deployment are selected. Then the caluculation formulas of the six orbital elements of two subsatellites after release are given. The calculation examples are presented. Nomenclature a . e . SZ, i , w, O=semimajor axis ,eccentricity ,right ascension, incliation angle, perigee argument, true anomaly of the orginal orbit a , . e, . Q , 1, , q , 0, (i = 1 , 2 ) =six orbital elements as above of the ith subsatellite IJ =Earth1 s gravitational constant *,=mean orbital rate, 1 =Instantaneous tether length I,, , =fully deployed tether length nl, ( I = 1 , 2 ) =mass of the ith subsatellite nn, =mass of the deployed tether rn=total mass of the system 1 rn~ =equivalent mass of the system, (ml+-mt) (m2 2 1 1 +-mt)/m-Tm. 2 R=magnitude of the position vector of the system center of mass T, U=Kinetic and potential energies, respectively a,Y=pitch and roll angles ,respectively I . Introduction A tethered satellite system is such one that two subsatellite are connected by a long,flexible cable. The constitution of the system is not very complex, but it has many applicable prospects. Most applications can be placed into four broad categories, such as momentum transfer ,special positioning of a probe in space, electrodynamics, gravity generation and so on. One of the most useful and possible applications is the momentum transfer. Rasing a payload by deploying it upward from an orbiter on a long tether and then releasing it represents a rather important possible application of varying the orbit involving significant fuel economy. So this applicable aspect has attracted many scholar' s attentions. Bekey''' and Bekey and P e n z ~ ' ~ ' find that a tethered payload deployed upward and released will rise to a higher orbit with its perigee at the release point and its apogee on the oppostie side of the Earth. Colomo et al'3' have showed that tethered system enable significant impulse savings for transfer missions from circular orbit. Their two-dimensional simulation assumes a massless tether and neglects tether dynamics, integrating only the equations of motion of the Ikrtor ,Astronautics School , Professor ,Astronautics School .Senior Member A H A t Assistant professor.Astronautics School i t I k t o r . Astronautics School Copyright 01 994 by the American lnst~tute of Aeronautics and Astronautics ,Inc. ," @default.
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• W2318193294 date "1994-08-01" @default.
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• W2318193294 title "The calculation of the orbital elements of a tethered satellite system after release" @default.
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• W2318193294 doi "https://doi.org/10.2514/6.1994-3746" @default.
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