Path: LunarMissions/LunarRHS
% Right-Hand-Side function for solar system object trajectories with moon
This model explicitly includes the moon. You must initialize the JPL
ephemerides before running this function.
PlanetPosJPL( 'initialize', planets );
Planets contains the JPL ephemeris ids from 1 to 11. The force model must
be of the form f = ForceModel( r, v, d ) where d can be any data
structure. f is the force vector in N in the ECI frame.
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Form:
d = RHSTrajectory; % Get the default data structure
RHSTrajectory( x ); % initialize persistent variables
[xDot, p] = RHSTrajectory( x, t, d ); % Call during simulation
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Inputs
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x (6*n,1) State [r;v] for n bodies
t (1,1) Time since start date
d (.) Date
.jD0 (1,1) Julian date at start
.mu (1,1) Sun gravitational parameter
.planets (1,:) Planet IDs.
.object (:) Data structures for object
.mass (1,1) Mass
.forceModel (.) Force model structure
.gravity (.) Gravity model structure
.cM (3,1) Center of mass
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Outputs
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xDot (6*n,:) State derivative d[r;v]/dt
p {} Auxiliary outputs
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See also: PlanetPosJPL, ForceSimple, GravityHelio, NoForce
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Interplanetary: Ephemeris/PlanetPosJPL LunarMissions: LunarRHS/ForceSimple LunarMissions: LunarRHS/GravityHelio LunarMissions: LunarRHS/NoForce Common: Database/Constant Common: Time/JD2000
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