Wing stall flutter closed-loop control method for continuous variable camber trailing edge

Abstract

The invention discloses a three-dimensional wing stall flutter closed-loop control method based on a continuously variable camber trailing edge and a process thereof. The method comprises the following steps: firstly, calculating the open-loop influence of the continuous change of the trailing edge camber on the characteristics of wing stall flutter by means of an efficient and high-precision CFD / CSD method; then establishing and training a nonlinear unsteady reduced-order model which considers wing vibration and three-dimensional spanwise trailing edge motion at the same time by adopting a recurrent neural network; the reduced-order model is adopted to quickly calculate the aerodynamic force of any motion of the flexible trailing edge changing in the three-dimensional spanwise direction and is used for designing the motion form of the flexible trailing edge, and the stall flutter motion amplitude is reduced. The continuous variable camber trailing edge is adopted to suppress stall flutter of the wing, a control mode which cannot be achieved by traditional rigid trailing edge deflection can be achieved, and stall flutter is effectively suppressed.

Description

technical field [0001] The invention relates to a construction method for stall flutter closed-loop control of a wing with a trailing edge with continuously variable camber along the chord direction and the span direction. Background technique [0002] The synthesis of aeroservoelasticity refers to the design of active control laws for a given aircraft performance index to form a closed-loop feedback, so as to achieve the expected index and improve system performance (Edited by Yang Chao. Aircraft Aeroelastic Principles [M]. Published by Beijing University of Aeronautics and Astronautics Society, 2011). Stall flutter is a dynamic aeroelastic stability problem, and it is also one of the key issues concerned in the synthesis of aeroservoelasticity. [0003] In the design of traditional aircraft, the steering gear is used to drive the deflection of the rigid trailing edge, combined with the closed-loop control law to achieve stability control for such problems (Song Chen, Wu Z...

AI Technical Summary

Problems solved by technology

Stall flutter and large deformation of the trailing edge are both nonlinear problems. The main problem of the existing methods is that the ability to deal with nonlinear problems is weak, and the design methods and ideas do not fully consider the characteristics of the continuously variable camber trailing edge. The existing work only The situation that the deformation is the same along the span direction is considered, that is, only a quasi-three-dimensional deformation is realized (Zhao Shiwei. Deformable wing structure design and aeroelastic research [D]. Beihang University, 2020)

Moreover, due to the complex aerodynamic characteristics of the continuously variable camber trailing edge, high-precision flow field analysis methods are required, resulting in long design cycles and high difficulty in iterative optimization

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