Tytuł artykułu
Autorzy
Wybrane pełne teksty z tego czasopisma
Identyfikatory
Warianty tytułu
Języki publikacji
Abstrakty
We investigate in this article the optimized orbit transfer of a space vehicle, revolving initially around the primary, in a similar orbit to that of the Earth around the Sun, in an elliptic trajectory, to another similar elliptic orbit of an adequate outer planet. We assume the elements of the initial orbit to be that of the Earth, and the elements of the final orbit to be that of an outer adequate planet, Mars for instance. We assume the elements of the two impulse Hohmann generalized configuration (the case of elliptic, non coplanar orbits) to be a1, e1, a2, e2, aT, eT. From the very beginning, we should assign θ = α 1 + α 2, the total plane change required. α 1 is the plane change at the first instantaneous impulse at peri-apse, which will be minimized, and α 2 the plane change at the second instantaneous thrust at apo-apse.
Czasopismo
Rocznik
Tom
Strony
183--191
Opis fizyczny
Bibliogr. 7 poz.
Twórcy
autor
autor
- Astronomy and Space Science Dept., Faculty of Sciences, Cairo University, Egypt
Bibliografia
- [1] Prussing, J.E. and Conway, B.A.: Orbital Mechanics, Oxford University Press, 1993.
- [2] Ehricke, K.A.: Space Flight, vol. 2: Dynamics, Van Nostrand, 1962.
- [3] Lawden, D.F.: Optimal Transfers Between Coplanar Elliptical Orbits, J. Guidance, vol. 15, No.3: Engineering notes, 1991.
- [4] Kamel, O.M. and Soliman, A.S.: On transfer between elliptical coplanar coaxial orbits, Bulletin of the Faculty of Sciences, Cairo University, vol. 67, 1999.
- [5] Chiang, A.C.: Elements of Dynamic Optimization, McGraw-Hill, 1992.
- [6] Chobotov, V.A.: Orbital Mechanics, 2nd ed. AIAA, Education Series, 1996.
- [7] Eagle, C.D.: [Internet: Windows 95/98/NT application (Hohmann - exe)], 2003.
Typ dokumentu
Bibliografia
Identyfikator YADDA
bwmeta1.element.baztech-article-LOD9-0027-0040