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We investigate the problem of fly past of a space vehicle traveling in a generalized elliptic Hohmann transfer system between the elliptic orbits of the Earth and Jupiter around the Sun. We consider the four feasible elliptic Hohmann configurations. We begin our treatment by a more precise expression for the hyperbolic excess velocity, because we deal with the elliptic not the circular Hohmann case. We assign the semi-major axes and the eccentricity of the hyperbolic trajectory that lies within the sphere of influence of the Jovian planet. Whence we have a more accurate determination of the elements of the hyperbolic trajectory before the vehicle's departure out of Jupiter's influence sphere to follow its trip to a further outer planet of the local solar system.
Czasopismo
Rocznik
Tom
Strony
25--38
Opis fizyczny
Bibliogr. 5 poz.
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autor
autor
autor
- Astronomy and Space Science Dept., Faculty of Sciences, Cairo University, Egypt
Bibliografia
- [1] Roy, A.E.: Orbital Motion, Adam Hilger, Bristol, U.K., 1982.
- [2] Ehricke, K.A.: Space Flight, vol. 2, Dynamics, New Jersey: Van Nostrand, 1962.
- [3] Hohman, W.: Die Ereichbarkeit der Himmelskorper. The attainability of Heavenly Bodies, NASA, Technical Translations F-44, 1960.
- [4] Kamel, O.M. and Soliman, A.S.: Bull. FAC, SCI., Cairo University, 67, pp. 61-71, 1999.
- [5] Chrone, J. and Daugherty, K. : Dynamics and Control Functional Division Report, Nov. 18, 2004.
Typ dokumentu
Bibliografia
Identyfikator YADDA
bwmeta1.element.baztech-article-LOD9-0027-0028