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SUPPORT SITE |
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SUPPORT SITE |
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Path: Orbit/OrbitMechanics
% Compute the required orbital elements for a flyby
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Form:
b = FlybyHyperbola( r, v, rP, mu )
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Inputs
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r (1,1) Distance
v (1,1) Velocity
rP (1,:) Perigee
mu (1,1) Mu
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Outputs
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b (1,1) Datastructure
.a (1,1) semimajor axis
.e (1,1) eccentricity
.rP (1,1) perigee
.vP (1,1) perigee velocity
.t (1,1) Time to r
.h (1,1) Hyperbolic anomaly at r
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Common: Graphics/Plot2D Common: Graphics/TimeLabl SC: BasicOrbit/RV2A SC: BasicOrbit/VOrbit
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