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Journal for the History of Astronomy; Journal of Astronomical History and Heritage; Journal of Astrophysics and Astronomy; Journal of the American Association of Variable Star Observers; Journal of Astronomical Instrumentation; Journal of Astronomical Telescopes, Instruments, and Systems; Journal of the British Astronomical Association
Orbital mechanics or astrodynamics is the application of ballistics and celestial mechanics to the practical concerning the motion of rockets, satellites, and other spacecraft. The motion of these objects is usually calculated from Newton's laws of motion and the law of universal gravitation .
The following is a partial list of scientific journals.There are thousands of scientific journals in publication, and many more have been published at various points in the past.
In the three-body problem, Broucke's doctoral research involved pioneering use of computer simulations to classify stable and unstable orbits. [1] He investigated what happens to this classification for earth–moon–satellite systems in the limit as the ratio of earth to moon mass approaches zero; his conjecture about this limiting behavior, "Broucke's principle", was finally proven correct ...
Early results about relative orbital motion were published by George William Hill in 1878. [3] Hill's paper discussed the orbital motion of the moon relative to the Earth.. In 1960, W. H. Clohessy and R. S. Wiltshire published the Clohessy–Wiltshire equations to describe relative orbital motion of a general satellite for the purpose of designing control systems to achieve orbital rendezvous.
Astrodynamics is the term used to describe the application of Newtonian mechanics to human-made objects in space, such as rockets and spacecraft. It is a subfield of celestial mechanics and ballistics .
Ismael Lopez, Colin R. McInnes. (1995) Autonomous rendezvous using artificial potential function guidance. Journal of Guidance, Control, and Dynamics 18:2, 237-241; Russel S. Wenzel, John E. Prussing. (1996) Preliminary study of optimal thrust-limited path-constrained maneuvers. Journal of Guidance, Control, and Dynamics 19:6, 1303-1309
A space vehicle's flight is determined by application of Newton's second law of motion: =, where F is the vector sum of all forces exerted on the vehicle, m is its current mass, and a is the acceleration vector, the instantaneous rate of change of velocity (v), which in turn is the instantaneous rate of change of displacement.