This chapter presents the specific functions involved in launching satellites to orbits to be performed. It describes some characteristics of launch vehicles. A launch vehicle, which may have various associated auxiliary propulsion systems, is used to inject the satellite into an intermediate orbit called the transfer orbit. The procedure using a transfer orbit is based on the so‐called Hohmann transfer, which enables the satellite to move from a low‐altitude circular orbit to a higher‐altitude circular orbit with a minimum expenditure of energy. The chapter explains how to calculate orbit velocity and discusses inclination correction and circularisation. The velocity increments required for changes of orbit, when not provided by the launcher, are provided by either the apogee or perigee motor, depending on the situation. Solid propulsion has been for many years a conventional technology for satellite apogee motors and the motors of transfer stages that are attached to them.
Satellite Installation and Launch Vehicles
Satellite Communications Systems ; 659-719
14.04.2020
61 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
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