Path: Orbit/RHSOrbit
% 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 optional rotation matrix function must be of the form
[bECIToEF, omega] = bFun( jD, bFunData )
bECIToEF is 3x3 and omega is 3x1. Omega is the planet angular rate
vector in the ECI frame.
If bFun is not used, the rotation is around the ECI z axis.
The default data structure is for the the Earth on March 22, 2016 at
11:58:19.
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Form:
xDot = RHSOrbitPlanetFixed( x, t, d )
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Inputs
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x (6,1) State [r;v]
d (.) Data structure
.mu (1,1) Gravitational constant
.gFun (2,1) Pointer to the gravity function
.gFunData (1,1) Gravity function data
.omega (1,1) Planet rotation rate
.aECI (1,1) Non-gravitational acceleration in the ECI frame
.theta0 (1,1) Initial planet to ECI angle
.jD0 (1,1) Initial Julian Date
.bFun (1,1) Pointer to the rotation matrix function
.bFunData (1,1) Rotation matrix function data
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Outputs
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xDot (6,1) State derivative [r;v]
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AC: ACData/ACTConstants SC: SCData/sCTConstants Common: CommonData/Constants Common: CommonData/xSplashSmall Common: Database/Constant Common: General/DeleteCell Common: Time/DTSToDTA Common: Time/Date2JD Math: Linear/Mag Math: Linear/Skew
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