Path: Orbit/OrbitCoord
% Computes planet centered orbital elements.
vC and rC must be inside the patch condition, i.e. when the spacecraft
orbit intersects the sphere of influence. At that point the target
planet or moon is the central body and orbital elements with respect
to that body are computed. If you do the conversion too far inside
the sphere of influence your results will not be correct.
vC, vPC, rC and rPC can be 3x1 or 3xn. In the latter case it finds
the crossing point for the sphere of influence.
If no outputs are specified, it will plot the planet centered orbit.
Velocity, mu and position must be in consistent units. This function
shows the effect of flying by another body but does not directly
help in designing a trajectory.
Type PtchCnc for a demo of a spaceraft approaching the moon in an
Earth-centered elliptical orbit.
Since version 2.
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Form:
el = PtchCnc( vC, vPC, rC, rPC, muC, muP )
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Inputs
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vC (3,1) Velocity of the spacecraft in the central frame
vPC (3,1) Velocity of the planet in the central frame
rC (3,1) Position of the spacecraft in the central frame
rPC (3,1) Position of the planet in the central frame
muC (1,1) Gravitational parameter of the central body
muP (1,1) Gravitational parameter of the planet
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Outputs
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el (:) Elements in the planet frame
el.a, el.e, el.i, el.w, el.L, el.M
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Orbit: OrbitCoord/RPRA2AE Orbit: OrbitMechanics/RVOrbGen Orbit: OrbitMechanics/SphOI SC: BasicOrbit/Period SC: BasicOrbit/RV2El Common: Database/Constant Common: General/DispWithTitle Math: Linear/Mag
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