Path: SC/Dynamics
% Right-hand-side of spacecraft dynamical equations with a second spacecraft. This is a rigid body with an external force and torque input. The position is in km. The gravity model is for a point mass. The prime spacecraft has attitude dynamics, the target has only point mass dynamics (position and velocity.) The force and torque are constant across the integration time step. -------------------------------------------------------------------------- Form: d = RHSRigidBodyWithTarget; xDot = RHSRigidBodyWithTarget( x, t, d ) -------------------------------------------------------------------------- ------- Inputs ------- x (:,1) State vector [r;v;q;w;rT;vT] (km,km/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 (N) .inertia (3,3) Vehicle inertia (kg-m^2) .mass (1,1) Vehicle mass (kg) .mu (1,1) Gravitational parameter (km^3/s^2) ------- Outputs ------- xDot (:,1) d[r;v;q;w;rT;vT]/dt --------------------------------------------------------------------------
AerospaceUtils: Coord/QIToBDot Common: Database/Constant Common: Quaternion/QTForm Math: Linear/Mag Math: Linear/Skew
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