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In this paper, an aircraft speed hold flight control problem is addressed only in one loop via sliding mode control with parameter uncertainties in flight speed and altitude without any reconfiguration of control parameters. Complete nonlinear longitudinal flight dynamics model is built for a conventional aircraft for speed hold problem. Control commands are assumed to be elevator angle deflection and trust input of jet-engine/propeller. Actuator limits are calculated to determine violation limits. A design example is given to illustrate effectiveness of proposed control system with compared simulations for three different flight conditions.