Path: Orbit/OrbitManeuver
% Computes the delta-V for a 2-burn transfer to a circular orbit at rF.
The delta-Vs are at
a. the initial orbit
b. the final orbit
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Form:
[deltaV, tOF, transfer] = OrbMnvrCircularize( rI, vI, gammaI, rF, mu )
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Inputs
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rI (1,1) Initial radius
vI (1,1) Initial velocity
gammaI (1,1) Initial flight path angle (rad)
rF (1,1) Final radius
mu (1,1) Gravitational parameter
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Outputs
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deltaV (1,1) Delta-V data structure.
.total (1,1) Total required delta-V
.a (1,1) Delta-V at point a
.b (1,1) Delta-V at point b
tOF (1,1) Time of flight
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Orbit: OrbitCoord/RV2AE SC: BasicOrbit/E2M SC: BasicOrbit/Nu2E SC: BasicOrbit/Nu2M SC: BasicOrbit/VOrbit Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle Math: Linear/Cross Math: Linear/Dot Math: Linear/DupVect Math: Linear/Mag
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