Path: Orbit/OrbitManeuver
% Delta-V to change apogee. Computes the delta-v needed to go from a transfer orbit to a final orbit with a plane change. Assumes that the node line coincides with the line of apsides. If there are no arguments a figure is created. -------------------------------------------------------------------------- Form: [dV, theta] = ApogeeDV( eT, iT, a2, e2, i2, mu ) ApogeeDV( eT, iT, a2, e2, i2 ); % create plot -------------------------------------------------------------------------- ------ Inputs ------ eT eccentricity of the transfer orbit iT inclination of the transfer orbit (rad) a2 semi-major axis of the final orbit e2 eccentricity of the final orbit i2 inclination of the final orbit (rad) mu gravitational parameter (default Earth, km^3/sec^2) ------- Outputs ------- dV total delta v theta angle of burn with respect to the final velocity vector -------------------------------------------------------------------------- References: Kaplan, M., Modern Spacecraft Dynamics and Control, John Wiley & Sons, p. 91. --------------------------------------------------------------------------
Orbit: OrbitCoord/A2Apogee Common: Graphics/AxesCart Common: Graphics/Map
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