Path: Orbit/OrbitManeuver
% Compute the delta V required to change perigee
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Form:
b = ChangePerigee( d )
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Inputs
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d (:) Input data structure
.a (1,1) Semi-major axis
.e (1,1) Eccentricity of initial orbit
.rP (1,:) New Perigee
.mu (1,1) Mu
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Outputs
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b (:) Output data structure
.dV (1,:) Datastructure
.e (1,:) New eccentricity
.a (1,:) New semi-major axis
.vA (1,:) Apogee velocity
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Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle
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