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Path: SCPro/DynamicalModels
% 6 DOF spacecraft dynamics with a double integrator position model.
This is a rigid body with an external force and torque input.
The position is in km. The position model is for a double integrator.
This is useful when the duration of the simulations are short
compared to the orbit period.
The force and torque are constant across the integration time step.
Since version 2014.1
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Form:
xDot = RHSRigidBody6DOF( x, t, d )
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Inputs
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x (:,1) State vector [r;v;q;w] (m,m/s,,rad/s)
t (1,1) Time (unused) (s)
d (1,1) Data structure for the simulation
.torque (3,1) External torque (Nm)
.force (3,1) External force in ECI (N)
.inertia (3,3) Vehicle inertia (kg-m^2)
.mass (1,1) Vehicle mass (kg)
.mu (1,1) Gravitational parameter (km^3/s^2)
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Outputs
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xDot (:,1) d[r;v;q;w]/dt
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AerospaceUtils: Coord/QIToBDot Math: Linear/Skew
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