Piezoelectric composite material helicopter blade structure and control method thereof

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.

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...

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Problems solved by technology

[0003] Traditional vibration reduction methods mainly use passive vibration absorption or vibration isolation devices, but this leads to increased weight and increased maintenance costs, which can no longer meet the requirements of the new generation of helicopters for vibration reduction performance

Active vibration reduction control appeared in the 1990s, including high-order harmonic control and independent control of a single blade, but the early active control technology also brought some negative effects while achieving vibration reduction, such as increasing structural weight and aerodynamic resistance. , excessive energy consumption, complex power plant, etc.

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