Path: LunarMissions/DynamicalModels
% Right hand side for orbit and attitude dynamics for a lunar mission simulation.
Includes solar disturbances and the power model. Any number of reaction wheels
can be simulated. Reaction wheels are optional. It also includes states for
the IMU (gyro and accelerometer) bias.
* The gravity model includes the Earth, Sun and the Moon.
The Moon gravity model can have spherical harmonics.
* The solar power model includes eclipses due to the Moon and Earth
but not self-shadowing.
You can select the Moon or Earth as the coordinate center for orbit
propagation. Get the default data structure by typing:
d = RHSLunarMission
Set up the state name output by typing:
RHSLunarMission( x );
You must initialize the JPL ephemerides prior to using this function.
Type:
PlanetPosJPL( 'initialize', [0 3 10] );
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Forms:
d = RHSLunarMission; % data structure
RHSLunarMission( x ); % initialize persistent variables
[xDot, p] = RHSLunarMission( x, t, d )
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Inputs
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x (:,1) State [rECI;vECI;qECIToBody;omega;massFuel;pBattery;
iMUBiasAccel;iMUBiasGyro;omegaRWA]
t (1,1) Time
d (.) Data structure
.jD0 (1,1) Julian date of epoch
.mass (1,1) Spacecraft mass (kg)
.inertia (3,3) Spacecraft inertia (kg-m2)
.power (.) Power data, see SolarCellPower
.opticalModel * Handle, see CubeSatRadiationPressure
.surfData (.) optional; empty to skip optical calcs
.thruster (.)
.rWA (.)
.iMU (.)
.gravity (.)
.forceBody (3,1) Body forces (N)
.torqueBody (3,1) Body torques (Nm)
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Outputs
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xDot (:,1) dx/dt
p (.) Data structure with internally computed variables
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AerospaceUtils: Coord/QIToBDot CubeSat: Modeling/InertiaCubeSat CubeSat: Power/SolarCellPower CubeSat: Simulation/CubeSatRadiationPressure Interplanetary: Ephemeris/PlanetPosJPL LunarMissions: LunarEnvironment/CubeSatLunarEnvironment Common: Quaternion/QForm Common: Quaternion/QTForm Common: Time/Date2JD Math: Linear/Cross Math: Linear/DupVect Math: Linear/Skew
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