Optimal Generalized Coplanar Bi-Elliptic Transfer Orbit Part I

• Autorzy: Kamel O. M. , Soliman A. S.
• Języki publikacji: EN

Abstrakty

EN

We have four feasible simple Bi-elliptic configurations for the transfer problem, for a central gravitational field. We restrict our selves to the first one in this part. We apply three impulses at the points A, C, B. x, z are our independent variables and are equal to the ratio between values of the velocities after and before the application of the impulses at points A, B respectively. Similarly y is defined as the corresponding parameter for the point C. We utilize the optimum condition of ordinary calculus for algebraic functions, to evaluate minimum values of x, z, y. We adopt the Earth - Mars bi-elliptic coplanar transfer system as an example, for the first configuration, to evaluate the numerical minimum values of x, z, y. In part II, we shall consider the other three configurations and expand to domain of application of the numerical results.

Słowa kluczowe

EN

optimization; rocket dynamics; orbital mechanics; bi-elliptic transfer

PL

optymalizacja; astrodynamika

• Wydawca: Wydawnictwo Politechniki Łódzkiej
• Czasopismo: Mechanics and Mechanical Engineering
• Rocznik: 2009
• Tom: Vol. 13, nr 1
• Strony: 73--78
• Opis fizyczny: Bibliogr. 5 poz.

Twórcy

autor

Kamel O. M.

autor

Soliman A. S.

• Astronomy and Space Science Department, Faculty of Sciences, Cairo University, Giza, Egypt

Bibliografia

• [1] Prussing, J. and Conway, B.: Orbital Mechanics, Oxford University Press, (1993).
• [2] Ting, L.: ARS J., PP. 1013-1018, (1960).
• [3] Billik, B.H. and Roth, H.L.: Astronautica Ada, Vol. 13, PP. 23-36, (1966).
• [4] Marec, J.P.: Space-Vehicle Trajectories : Optimization, Reprinted from Systems &Control Encyclopedia, Theory, Technology, Applications, Pergamon Press, (1988).
• [5] Murray, CD. and Dermott, S.F.: Solar System Dynamics, Cambridge University Press, (1999).