Helicopter Structural Response Active Control System Using Piezoelectric Laminated Actuators

A technology of structural response and actuator, applied in the direction of rotorcraft, aircraft, motor vehicles, etc., can solve the problems of restricting the performance of the control system and vibration control, large additional mass, slow response speed, etc., to achieve strong following control ability, additional Lightweight and responsive effects

Inactive Publication Date: 2016-01-06
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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AI Technical Summary

Problems solved by technology

However, the inertial actuators or hydraulic actuators commonly used in helicopter active vibration control systems have greatly reduced and restricted the performance of the control system and the effect of vibration control due to their shortcomings such as large additional mass, narrow operating frequency band, and slow response speed.

Method used

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  • Helicopter Structural Response Active Control System Using Piezoelectric Laminated Actuators
  • Helicopter Structural Response Active Control System Using Piezoelectric Laminated Actuators
  • Helicopter Structural Response Active Control System Using Piezoelectric Laminated Actuators

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Embodiment Construction

[0017] The technical solution of the present invention will be described in detail below with reference to the accompanying drawings, which disclose, without limitation, the active control system for structural response of a helicopter using piezoelectric laminated actuators of the present invention.

[0018] Such as figure 1 As shown, a helicopter structure response active control system using piezoelectric laminated actuators, including helicopter body structure, computer, digital signal generator, D / A converter, low-pass filter, power amplifier, vibrator , piezoelectric stacked actuator, signal conditioner, ICP acceleration sensor, DSP embedded controller, piezoelectric stacked actuator is installed on the described helicopter body structure, the installation of piezoelectric stacked actuator There can be many ways, such as directly installed in the structure of the helicopter body, such as figure 2 shown; installed outside the helicopter body structure with the help of s...

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Abstract

The invention discloses a helicopter structural response active control system employing a piezoelectric stack actuator, and relates to the technical field of helicopter vibration control. The system comprises a helicopter body structure, a computer, a digital signal generator, a D / A converter, a low pass filter, a power amplifier, an oscillator, a piezoelectric stack actuator, a signal conditioner, an ICP acceleration sensor and a DSP embedded controller. The computer and the helicopter airframe structure input / output circuit. The computer outputs a vibration signal to act on the airframe structure, so that vibration acceleration signals produced by the airframe return to the computer; and then the computer outputs a control signal to control the airframe vibration, so as to play the role of helicopter vibration control. The helicopter vibration control system provided by the invention has advantages of light additional weight of the actuator, wide frequency band, high response speed, strong aligning control ability and good control effect.

Description

technical field [0001] The invention discloses a helicopter structural response active control system using a piezoelectric laminated actuator, which belongs to the technical field of helicopter vibration control. Background technique [0002] Because the helicopter rotor works in an asymmetric and unsteady aerodynamic environment, the vibration level of the helicopter body is very high, which affects the flight performance of the helicopter. Therefore, helicopter vibration control plays a very important role in improving the flight performance of helicopters. Currently, structural response active control is considered to be the most practical new technology for helicopter vibration active control, which can effectively reduce the vibration level of helicopters. However, the inertial actuators or hydraulic actuators commonly used in helicopter active vibration control systems have greatly reduced and restricted the performance of the control system and the effect of vibrati...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C27/00
Inventor 夏品奇宋来收
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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