Path: Orbit/OrbitMechanics
% Perturbing acceleration due to a planet on a spacecraft.
The spacecraft is within the sphere of influence of another body.
The equations become
2
d r mu r
-- + ---- = a
2 3
dt |r|
This function is valid when r << rho. Multiple planets can be input at once.
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Form:
[a, aP] = APlanet( r, mu, rho )
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Inputs
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r (3,1) Vector of the spacecraft from the central body
mu (:) Planet gravitational parameter(s)
rho (3,:) Vector of the perturbing planet(s) from the central body
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Outputs
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a (3,1) Total acceleration
aP (3,:) Accelerations of individual planets
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Reference: Bond, V.R., M.C. Allman, Modern Astrodynamics
Princeton University Press, 1996, pp. 203-204.
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Math: Linear/Mag
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