Active control test platform and method for vibration of near space aircraft model

Abstract

The utility model relates to an active control test platform and a method for vibration of a near space aircraft model. The test platform leads an aircraft model distributed and stuck with a piezoelectric sensor and an actuator to be hung on an aluminum alloy outer framework, and is connected with a function signal generator of a power amplifier to drive an exciter fixed on the aluminum alloy outer framework and lead the aircraft model connected with the exciter to generate a vibration response; and a vibration response signal is collected by the piezoelectric sensor, and is outputted on the power amplifier and acted on the piezoelectric actuator through the operation of a computer inserted with a data acquisition and output card. The active control test platform has the characteristics of convenient composition, simple structure, and good expandability. The method can provide experimental verification realization means for the active control method for the vibration of the near space aircraft model, and provide technical realization supports for exploring the further practical applications of relevant control theories and methods.

Description

technical field [0001] The invention relates to the field of active vibration control of piezoelectric intelligent structures, in particular to an experimental platform and method for active vibration control of an aircraft model near space. Background technique [0002] Real-time monitoring and effective control of aircraft structural vibration / flutter has always been a crucial issue in the field of aerospace technology, especially for near-space vehicles. The body materials of near-space vehicles are mainly composed of light-weight, high-strength, high-modulus titanium alloys and composite materials. The optimized advanced aerodynamic layout makes the aircraft body more streamlined, narrow and long, and the wings are getting thinner and thinner. The flexibility and elasticity of the wing structure are enhanced, but the bending and torsional stiffness is getting smaller and smaller; when the aircraft’s angle of attack is disturbed, the change of the thrust vector will chang...

AI Technical Summary

Problems solved by technology

The body materials of near-space vehicles are mainly composed of light-weight, high-strength, high-modulus titanium alloys and composite materials. The optimized advanced aerodynamic layout makes the aircraft body more streamlined, narrow and long, and the wings are getting thinner and thinner. The flexibility and elasticity of the wing structure are enhanced, but the bending and torsional stiffness is getting smaller and smaller; when the aircraft’s angle of attack is disturbed, the change of the thrust vector will change the pitching moment acting on the aircraft, and the body’s elasticity will cause the aircraft to generate Structural deformation, and the lower vibration deformation modal frequency is very close to the short-period motion frequency of the aircraft, which will not only affect the short-period motion of the aircraft, but also aggravate the deformation of the aircraft, so the bending deformation of the fuselage will affect the performance of the propulsion system. Conversely, the propulsion system further affects the dynamic response of the rigid body or intensifies the elastic motion; and because there are many disturbance factors such as real gas effect, shock boundary layer interference, rare gas characteristics and thermal barriers in the high-speed flow field where the aircraft is located, it is very easy to induce and aggravate The airframe structure vibrates strongly; when the high-speed flight of the aircraft is excited by uncertain disturbances, the airframe and wing structure may produce complex aeroelastic dynamic instability under the joint action of aerodynamic force, structural elastic force and structural inertial force phenomenon, the consequences of the occurrence of this structural flutter state are often catastrophic

[0003] Once the traditional passive structure is manufactured, it can only passively accept the impact of the environment, and cannot dynamically monitor the performance of the aircraft, let alone respond to environmental changes. Currently, the concept of intelligent material structure is used to realize active vibration monitoring. Due to the high difficulty and importance of technology Its application value has received extensive attention and in-depth research by researchers in related fields at home and abroad, but it is far from mature in theoretical research and engineering practice.

Existing experimental platforms and methods are mostly aimed at simple models such as cantilever beams and cantilever plates, and are difficult to apply to complex models such as aircraft

Images