The Infona portal uses cookies, i.e. strings of text saved by a browser on the user's device. The portal can access those files and use them to remember the user's data, such as their chosen settings (screen view, interface language, etc.), or their login data. By using the Infona portal the user accepts automatic saving and using this information for portal operation purposes. More information on the subject can be found in the Privacy Policy and Terms of Service. By closing this window the user confirms that they have read the information on cookie usage, and they accept the privacy policy and the way cookies are used by the portal. You can change the cookie settings in your browser.
Due to the problem of serious nonlinear, strong coupling, uncertain parameters existed in the process of hypersonic vehicle's flight, this paper designs a fuzzy boundary layer adaptive sliding mode controller based on tangent reaching law. Firstly, the longitudinal model is linearized exactly, and then by introducing a parameters adjusted by online fuzzy logic system as sliding boundary layer, quasi-sliding...
As the process of traditional dynamics modeling for rigid-flexible couple system is complex, this paper introduces the theory of characteristic modeling to simplify the modeling process. Unlike other reduced-order models, characteristic model compresses the high-order information into the characteristic parameters. Therefore, it will not lose model information. In addition, in order to improve the...
An integrated control law is presented considering a nonlinear model of generic hypersonic vehicle as a plant. Based on dynamic inverse theory, the nonlinear model is transformed into an equivalent affine system. Then a dynamic inverse controller could be designed according to the equivalent system. What's more, two fuzzy logic regulars are used to adapt control parameters on line, and the fuzzy rules...
In this paper, a pitch angle controller is designed based on L1 adaptive control theory to guarantee steady generator power output while reducing the mechanical loads at above rated wind speed. Firstly, a non-affine model of the pitch regulated variable-speed wind turbine is built to formulate complicated aerodynamics. The L1 adaptive pitch angle controller is then introduced to assure uniformly bounded...
The design of a robust adaptive backstepping flight control law for a unmanned aerial vehicle (UAV) is discussed. The lumped uncertainties of the nonlinear UAV model are concerned in this paper. RBF neural networks are used inside the backstepping control law to approximate the lumped uncertainties. Command filters are used to implement the virtual control law and avoid “explosion of complexity”....
The dynamics of flexible air-breathing hypersonic vehicles (FAHVs) are nonlinear non-minimum, so the internal dynamics of FAHVs is unstable. The traditional dynamic inversion method is unsuitable for the control of FAHVs. Stable inversion method proposes an efficient way for the control of nonlinear nonminimum system, so a stable inversion based sliding mode control (SMC) method is proposed for the...
This paper investigates the attitude control problem of on-orbit servicing spacecraft which changes moment of inertia after the rendezvous and docking task. Considering in the small-angle circumstance and manipulating attitude dynamics model with linearization method, the attitude controller based on pole assignment is obtained. Finally, a numerical example is provided to illustrate the effectiveness...
Set the date range to filter the displayed results. You can set a starting date, ending date or both. You can enter the dates manually or choose them from the calendar.