The change in the hyperbolic orbital elements due to application of a small impulse

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

Abstrakty

EN

The differential variations in the hyperbolic orbital classical element s due to a small impulse in the direction of the velocity vector are computed. We applied the method of Gauss for secular perturbations using the Lagrangian form of planetary equations.

Słowa kluczowe

PL

dynamika rakiety; równanie Lagrange'a; ruch orbitalny

EN

rocket dynamics; Gauss method for secular perturbations; Lagrange planetary equations; orbital motion

• Czasopismo: Mechanics and Mechanical Engineering
• Rocznik: 2004
• Tom: Vol. 7, nr 2
• Strony: 107-119
• Opis fizyczny: Bibliogr. 7 poz.

Twórcy

autor

Kamel, O. M.

autor

Soliman, A. S.

autor

Ammar, M. K.

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

Bibliografia

• [1] Brouwer, D and Clemence, GM: (1965), Methods of Celestial Mechanics, Academic Press.
• [2] Boccaletti, D and Pucacco, G: (1999), Theory of Orbits, Springer, Part 2 Perturbative and Geometrical Methods, Ch. 6.
• [3] Edelbaum, TN: (1967), How Many Impulses?, Astronautics & Aeronautics, AIAA.
• [4] Herrick, S: (1971), Astrodynamics, 1, Van Nostrand.
• [5] Murray, CD and Dermott, SF: (1999), Solar System Dynamics, Cambridge University Press.
• [6] Roy, AE: (1982), Orbital Motion, Adam Hilger.
• [7] Smart, WM: (1960), Celestial Mechanics, Longmans.