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SUPPORT SITE |
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SUPPORT SITE |
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Path: Orbit/OrbitControl
% Compute two delta-v's to raise the apogee and circularize the orbit. -------------------------------------------------------------------------- Form: [dV1,dV2,tOF,aT] = ApogeeRaisingDeltaV( r, v, rDes, aT ); -------------------------------------------------------------------------- ------ Inputs ------ r (3,1) ECI position (km) v (3,1) ECI velocity (km/s) rDes (1,1) Desired apogee (km) aT (1,1) Transfer orbit semi major axis. Optional. (km) ------- Outputs ------- dV1 (3,1) First delta-v to raise the apogee dV2 (3,1) Second delta-v to circularize at apogee tOF (1,1) Time of flight from current state to final orbit aT (1,1) Semi major axis of transfer orbit --------------------------------------------------------------------------
Common: Graphics/Plot2D Math: Linear/Cross Math: Linear/Mag Math: Linear/Unit SC: BasicOrbit/El2RV SC: BasicOrbit/Nu2M
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