Path: SC/Dynamics
% Two body spacecraft model right-hand-side. This calls the two body dynamics model, TBModel. It is usually called by a numerical integration routine. See also TBModel. -------------------------------------------------------------------------- Form: xDot = FTB( x, t, r0, r1, lam1, iner0, iner1, m0, m1, torque, force, iAxis ) -------------------------------------------------------------------------- ------ Inputs ------ x (14,1) The state vector [q0;q0to1;w0;w1;....] t (1,1) The time vector r0 (3,1) The vector from the origin to the body 0 cm in the body 0 frame r1 (3,1) The vector from the origin to the hinge in the body 0 frame lam1 (3,1) The vector from the hinge to the body 1 cm in the body 1 frame iner0 (3,3) The body 0 inertia in the body 0 frame iner1 (3,3) The body 1 inertia in the body 1 frame m0 The body 0 mass m1 The body 1 mass torque (6,1) [totalExternalTorque(3); hingeTorque(3)] force (6,1) [body0ExternalForce(3); body1ExternalForce(3)] at their cms iAxis (1,:) The axes of the second body that are not constrained. ------- Outputs ------- xDot (14,1) The derivative of the state vector --------------------------------------------------------------------------
AerospaceUtils: Coord/QIToBDot SC: Dynamics/TBModel Common: Control/C2DZOH Common: Quaternion/Q2Mat Math: Linear/Cross Math: Linear/SkewSymm
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