Path: SC/Dynamics
% 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.
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Form:
d = RHSRigidBody6DOF
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 Common: Database/Constant Math: Linear/Skew
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