Artificial satellites have to perform maneuvers throughout their operational life, first to reach their nominal orbit, then to stay precisely on it for several years, and finally to evacuate it at their end of life. With high‐thrust engines, the maneuvers can be modeled as velocity impulses, which change one or several orbital parameters. Only the simplest problems, such as Hohmann transfer, have analytical solutions. In many practical situations, the arrival time is constrained. Lambert's problem must then be solved, for which a series of numerical solution methods are available.
Impulsive Transfer
Space Trajectories ; 147-185
24.12.2024
38 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
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Tema Archiv | 1976
|Optimum impulsive orbital transfer between coplanar orbits
Engineering Index Backfile | 1962
|A computer survey of impulsive ellipse-ellipse transfer
AIAA | 1971
|