MIMO conditional integrator control for unmanned airlaunch

Abstract : A nonlinear MIMO controller based on the conditional integrator technique is designed for the robust stabilization of a new satellite launching strategy called (unmanned) airlaunch. This control technique concerns an integrator performing similar to a sliding mode controller when the system is outside a boundary layer defined by the controller, and performing as a linear controler that provides the integral term when the system enters into the boundary layer. Satellite airlaunch strategy consists in using a two-stage launching system. The first stage is composed of an airplane (manned or unmanned) that carries a rocket launcher, which constitute the subsequent stages. The control objective is to stabilize the aircraft in the launch phase. It is developed separately for the two nonlinear (one MIMO and one SISO) motion modes of the model, the longitudinal mode and lateral mode, and is then applied to the full model of the aircraft. The considered system is highly nonlinear, mostly as a consequence of a possible large angle of attack, sideslip, and roll angle. Finally, the present work illustrates through simulations, the good performance of the proposed control algorithm.
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Submitted on : Tuesday, November 12, 2013 - 4:52:18 PM
Last modification on : Monday, October 28, 2019 - 10:50:21 AM

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Cuong Nguyen Van, Gilney Damm. MIMO conditional integrator control for unmanned airlaunch. International Journal of Robust and Nonlinear Control, Wiley, 2015, 25 (3), pp.394--417. ⟨10.1002/rnc.3092⟩. ⟨hal-00903666⟩

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