Trailing edge variable camber wing driven by piezoelectric fiber materials

Abstract

The invention provides a trailing edge variable camber wing driven by piezoelectric fiber materials. The wing comprises a leading edge fixing section with the invariable camber, a trailing edge flexible deformation section with the variable camber and a piezoelectric fiber composite material driver used for adjusting the change degree of the trailing edge flexible deformation section. The trailingedge flexible deformation section comprises a flexible wing rib, a stringer, a deformation skin, a segmented deformation skin and a segmented deformation skin fixing device. Voltage excitation is applied to the piezoelectric fiber composite material drivers, generated torque is transmitted to the flexible wing rib structure through the skin, and continuous and smooth change of the shape of the trailing edge of the wing is achieved. The wing structure mass can be greatly reduced, noise is reduced, the stealth characteristic is improved, the corresponding deformation control system is combined,accurate control over wing camber changes in the flight process can be achieved, the maneuvering and stall characteristics of an airplane are improved, and the task adaptability of the airplane is greatly enhanced.

Description

technical field [0001] The invention relates to the technical field of aviation products, in particular to a trailing edge variable camber wing driven by a piezoelectric fiber material. Background technique [0002] With the continuous improvement of aircraft performance requirements in the military and civilian fields, traditional wings have bottlenecks in improving aircraft mission adaptability and improving aircraft aerodynamic efficiency, and it is urgent to explore effective and feasible solutions. Wing deformation technology provides a new method and new idea for improving the mission adaptability of aircraft. [0003] The concept of morphing wing design has been around for a long time. In 1903, the first airplane of the Wright brothers realized the control of the flight state by twisting and deforming the wings. In 1920, Parker proposed the concept of variable camber wing design combining mechanical motion and compliance structure. Since the 1980s, active wing defo...

AI Technical Summary

Problems solved by technology

At the current stage, although researchers at home and abroad have carried out a lot of research on wing deformation technology, there are still some problems that limit the application and development of this technology.

For example, in the mission adaptive wing project in the United States, an adaptive variable camber structure with multi-joints was designed for the F-111 aircraft, and a traditional hydraulic drive was used to drive the camber of the wing to change, but in the end due to the complex deformation structure, the weight loss was large and other reasons stopped further research on the project

Relevant researchers from Nanjing University of Aeronautics and Astronautics and Northwestern Polytechnical University have successively designed multi-articulated variable camber adaptive wings driven by multiple stepping motors, which also have the disadvantages of complex structure and easy jamming. The aerodynamic gain does not even offset the weight loss due to the addition of deformable structures

In addition to traditional drive mechanisms such as motors and hydraulics, intelligent material drives such as aerodynamic muscles, shape memory alloys, and ultrasonic motors are also widely used in the design of deformable wings, but there are corresponding limitations, such as the drive of shape memory alloys. The rate is slow, it is difficult to achieve fast and accurate tracking of wing deformation commands

The control accuracy of pneumatic muscles is average, and there is hysteresis effect

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