Path: Orbit/OrbitManeuver
% Computes the delta-V to insert into a planetary or lunar orbit.
The maneuver is done instantaneously. The default mu is for the
Earth's moon.
Type OrbMnvrInsertion for a lunar insertion demo.
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Form:
deltaV = OrbMnvrInsertion( r, v, rT, vT, rP, i, mu, qCToP )
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Inputs
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r (3,1) Spacecraft position in central body frame
v (3,1) Spacecraft velocity in the central body frame
rT (3,1) Planet position in the central body frame
vT (3,1) Planet velocity in the central body frame
rP (1,1) Perigee altitude (km)
i (1,1) Planet orbit inclination (rad)
mu (1,1) Gravitational parameter (Moon is the default)
qCToP (4,1) Quaternion from central body to planet fixed frame
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Outputs
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deltaV (3,1) Vector velocity change in the central body frame
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Orbit: OrbitCoord/RPRA2AE Orbit: OrbitMechanics/RVOrbGen SC: BasicOrbit/Period SC: BasicOrbit/RV2El SC: BasicOrbit/VOrbit Common: Database/Constant Common: Graphics/Plot3D Common: Quaternion/QForm Math: Linear/Cross Math: Linear/Mag Math: Linear/Unit
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