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Conditions of stability of the closed-loop system are derived.
Second, several important properties of the riser system are derived.
The equations of motion of the reduced system are derived.
Expressions for the main parameters of the system are derived.
First, mathematical models of a rotor-bearing system are derived.
The transfer functions of the optimum guidance system are derived and an example missile-control system is synthesized.
The equations of motion of the system are derived using Hamilton's principle.
Analytic expressions for the power output and efficiency of the hybrid system are derived.
Analytical expressions for the Lyapunov coefficients of a planar differential system are derived.
First, the equations of motion of the system are derived in an absolute coordinate system.
The dynamic equations for the system are derived using the extended Hamilton's principle.
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