Path: SCPro/DynamicalModels
% Spacecraft attitude and orbit dynamics with a disturbance function.
This is a rigid body with single axis CMGs.
It has an external force and torque input.
The torque are constant across the integration time step.
The function fDist (which should be a pointer) is of the form
torque = MyFun( x, t, d )
d can contain additional parameters for the model
You can add additional fields to d. torque in Nm in the body frame.
This function allows you to add torques within the integration loop.
This is required for torques that are functions of time or the
state vector.
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Form:
[xDot,inr,hECI] = RHSCMG( x, t, d )
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Inputs
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x (:,1) State vector [q;phi;w;omegaG;omegaW]
t (1,1) Time (s)
d (1,1) Data structure for the simulation
.torque (3,1) External torque (Nm)
.force (3,1) External force (N)
.inr0 (3,3) Core inertia (kg-m^2)
.inrG {3}(3,3) Gimbal inertia (kg-m^2)
.inrW {3}(3,3) Wheelinertia (kg-m^2)
.torqueG (1,:) Gimbal torque (Nm)
.torqueW (1,:) Wheel torque (Nm)
.fDist (1,:) Disturbance function pointer
.x0 (15,1) Default data structure with 3 CMGs
.states {15} Corresponding state names
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Outputs
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xDot (:,1) d[q;phi;w;omegaG;omegaW]/dt
inr (:,:) The generalized inertia matrix
hECI (3,:) The ECI momentum
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AerospaceUtils: Coord/QIToBDot Common: Control/C2DZOH Common: Quaternion/QTForm Math: Linear/Cross Math: Linear/SkewSymm
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