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Multi-harmonic multi-input multi-output feedforward self-adaptive controlling method for helicopter body vibration

An adaptive control and helicopter technology, which is applied in the direction of motor vehicles, rotorcraft, transportation and packaging, etc., can solve problems such as inability to control multi-harmonics, and achieve the effect of solving insufficient control effects

Active Publication Date: 2017-07-14
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

Algorithms currently used include frequency-domain-based DFT method, time-domain-based H∞ control, Fx-LMS method, etc. However, these algorithms only control the vibration of the main passing frequency or the vibration of a single load, and cannot address the multiple vibrations of the body. Harmonics make control

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  • Multi-harmonic multi-input multi-output feedforward self-adaptive controlling method for helicopter body vibration
  • Multi-harmonic multi-input multi-output feedforward self-adaptive controlling method for helicopter body vibration
  • Multi-harmonic multi-input multi-output feedforward self-adaptive controlling method for helicopter body vibration

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[0033] The present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the present invention, but not to limit the present invention. In addition, it should be noted that, for the convenience of description, only some structures related to the present invention are shown in the drawings but not all structures.

[0034] Below in conjunction with accompanying drawing the technical scheme of invention is described in detail, the system block diagram of multi-harmonic multi-input multi-output feed-forward adaptive control method of helicopter body vibration is as follows figure 1 As shown, the specific steps include:

[0035] S1, according to the passing frequency ω of the helicopter rotor r , the control harmonic order R is determined from the vibration spectrum measured by the helicopter body, and the harmonic basis functi...

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Abstract

The invention discloses a multi-harmonic multi-input multi-output feedforward self-adaptive controlling method for helicopter body vibration and belongs to the field of active controlling of helicopter vibration. Aiming at the characteristic of helicopter body vibration under stimulation of the rotor vibration load with multi-stage harmonic frequency and multiple directions and based on the minimum mean square error method and harmonic coefficient identification, the multi-input multi-output feedforward self-adaptive controlling method of helicopter body vibration under the multi-harmonic and multi-load simulation is put forward, so that the purpose of reducing helicopter body vibration is achieved, and when the vibration phase, vibration amplitude and vibration frequency are changed, the good self-adaptive controlling performance is achieved.

Description

technical field [0001] The invention belongs to the technical field of helicopter vibration active control, and discloses a helicopter body vibration multi-harmonic multi-input multi-output feedforward adaptive control method. Background technique [0002] During the flight of the helicopter, the blades are always in an unsteady aerodynamic environment. When flying forward, the blades correspond to different aerodynamic forces at different azimuth angles and different blade radii, which generate a large vibration load, and these vibration loads generate a strong excitation response on the helicopter body. The main frequency component of the rotor vibration load transmitted to the body is rNΩ, where r is the number of harmonics, r=1, 2, 3,..., N is the number of blades, and Ω is the rotor speed. These frequencies are called the passing frequency of the rotor , where the low-order part plays a major role in the helicopter vibration. In order to effectively reduce the vibrati...

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Application Information

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IPC IPC(8): B64C27/51
CPCB64C27/51
Inventor 孟德夏品奇
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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