Double-loop control. In Figure 5, G ud (s) and G id (s) are shown in

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Stall characteristics of different aircrafts.

Bias power calculation and dynamic limiting.

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Simplified EMS simulation model of our RVC with a stirrer angle defined

Satellite transfer orbit after Launch Vehicle Injection Apogee firing

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Solved G(s)=s2+91 A PD controller is implemented using the

Block diagram of the coupled atmospheric-propagator models. The blue