Piezoelectric composite material helicopter blade structure and control method thereof

A technology of piezoelectric composite materials and composite material layers, which is applied in the direction of rotorcraft, motor vehicles, aircraft assembly, etc., can solve the problems of not meeting the requirements of helicopter vibration reduction performance, rising maintenance costs, excessive energy consumption, etc., and achieve weight Lightweight, improved performance and service life, and reduced noise

CN104590558AInactive Publication Date: 2015-05-06HUNAN UNIV
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Publication Date
2015-05-06
Estimated Expiration
Not applicable · inactive patent

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Abstract

The invention discloses a piezoelectric composite material helicopter blade structure and a control method thereof. A piezoelectric composite material is embedded into a composite material lamination structure of a rotor blade. An analysis model is established and is capable of accurately describing the motion rule of the rotor blade based on a structure model, an aerodynamic force model, a piezoelectric composite material model and the like, and further accurately calculates the dynamics characteristics of the rotor blade. According to the control method, a controller is employed for controlling the rotor blade, a Kalman observer is employed for obtaining rotor blade data under the condition of white noise interference, and the rotor blade data is taken as input variable for controlling, and further by using the controller to control the input voltage of the piezoelectric composite material, the purpose of controlling blade dynamics response and deformation is finally realized. The provided model establishing method and the control method have relatively high versatility and accuracy, help to accurately obtain dynamics characteristics of the helicopter rotor blade, and are high in control efficiency.
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Description

technical field

[0001] The invention belongs to the field of helicopter dynamics, in particular to a piezoelectric composite material helicopter blade structure and a control method thereof, which can be used in the design and manufacture of helicopter rotor blades. Background technique

[0002] Helicopters, with their unique vertical take-off and landing and air-hovering capabilities, can complete tasks that fixed-wing aircraft cannot complete, and have been widely used in national defense and civilian applications. However, excessive vibration levels have seriously affected the ride quality of the occupants, the fatigue life of structural components, and the normal operation of airborne equipment, and have become the biggest obstacle restricting the use of helicopters. Therefore, vibration and noise reduction is one of the important contents of helicopter research and design.

[0003] Traditional vibration reduction methods mainly use passive vibration absorption or vibra...

Examples

Embodiment

[0118] This example provides a rotor blade using piezoelectric composite material, the rotor blade model is established by using the analysis model of the present invention, and its vibration is controlled by the control method of the present invention. The main parameters of the rotor are as follows: the span length of the rotor is 16m, the chord length is 1m, the mass per unit length is 0.75kg / m, the position of the elastic axis and the center of gravity are at 50% of the chord length, the bending stiffness in the span direction is 2×104N·m2, the chord The bending stiffness in the longitudinal direction is 4×106N m2, the torsional stiffness is 1×104N m2, the rated speed of the rotor is Ω=432rpm, the section flexibility matrix (the stiffness matrix is ​​the inverse matrix of the flexibility matrix, as shown in formula (21)) and The inertia matrix looks like this:

[0119] U V ...