Path: LunarMissions/LunarLanding
% Cartesian orbital equations in a planet fixed (rotating) frame.
The gravity function returns the gravitational accelerations in the
planet fixed frame. It must be of the form
a = GravFun( r, gFunData )
where a is in the planet fixed frame. d.mu is not used in this case.
The planet rotation is around the ECI z axis.
The default data structure is for the the moon.
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Form:
xDot = RHSPlanet3D( x, ~, d )
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Inputs
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x (7,1) State [r;v;m], where m is fuel mass
t (1,1) Time (not used)
d (.) Data structure
.mu (1,1) Gravitational constant
.gFun (@) Handle to the gravity function
.gFunData (.) Gravity function data structure
.omega (1,1) Planet rotation rate
.uThrust (3,1) Unit thrust vector
.thrust (1,1) Thrust (N)
.uE (1,1) Exhaust velocity (m/s)
.m0 (1,1) Dry mass, total mass is m0 + m
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Outputs
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xDot (7,1) State derivative [r;v;m]
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Common: Database/Constant Math: Linear/Mag Math: Linear/Skew
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