The Orbital of Satellite Transfer with Inclination Change Using a New Techniques

Abstract

The process of satellite transition without perturbations effect were studded in this work. The initial elliptical orbit (e= 0.01, a= 6745.45 km, i= 0°) was transfer to geostationary orbit through the transfer elliptical orbit with inclination variation between the initial and final orbit Δi= 0°,1,2 to 180°. A program was designed to calculate the velocity needed to transition (ΔVhohman), the velocity needed to rotation the plane of orbit (ΔVi), ΔVtotal, mass of fuel needed and time of transition we assume that the time of rotation equal one period. Hohmann transfers method between coaxial elliptical orbits to Satellite transmission was used. It is the process of transition the satellite from an elliptical initial orbit to a circular final orbit through an elliptical transition orbit some assumption were used in our techniques of transition orbit. The results indicated that the best method for the transfer process that is transfer the satellite from the perigee of the initial elliptical orbit and then perform the orbit rotation process of the final upper orbit. The inclination angle can be reach is 60 degree where at this Δi low velocity or low energy needed and the rotation can happen during one period. The amount of fuel needed to transition of the satellite can be achieved.