Morphing aircraft transition section tensor product interpolation modeling and control method

Abstract

The invention discloses a morphing aircraft transition section tensor product interpolation modeling and control method. The morphing aircraft transition section tensor product interpolation modeling and control method comprises the following steps of, firstly, establishing a morphing aircraft transition section non-linear kinetic model, and establishing a morphing aircraft kinetic equation; secondly, through a linear parameter varying comprehensive modeling method integrating small-increment linearization and accurate linearization, establishing a morphing aircraft transition section linear parameter varying model, namely, an LPV model; thirdly, on the basis of the LPV model, establishing a tensor product interpolation model; fourthly, based on the tensor product interpolation model, designing a morphing aircraft transition section flight control method which is small in computational amount. On the basis of the new morphing aircraft transition section linear parameter varying modeling method, the tensor product interpolation model is established; on the basis of the tensor product interpolation model, the flight control method is designed and optimization of tensor product interpolation coefficients is performed, so that optimized control effects can be obtained.

Description

technical field [0001] The invention belongs to the field of flight control, and specifically refers to a tensor product interpolation modeling and control method for a transition section of a variant aircraft. Background technique [0002] The morphing aircraft can autonomously change its shape during flight, where the changed shape includes wing camber, span length, chord length, wing area, wing twist, chord length, etc., to improve its aerodynamics through the variation in flight Features to meet the needs of different flight environments and missions. [0003] The aerodynamic and dynamic characteristics of the morphing aircraft will undergo drastic changes during the transition process of morphing. The aircraft exhibits fast time-varying and highly nonlinear characteristics. Therefore, in this case, the traditional flight control method based on the small disturbance linearization model cannot be applied. The linear variable parameter modeling and control method is a ...

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Problems solved by technology

However, the usual linear variable parameter method has the disadvantages of relying too much o

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