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Helicopter rotor system with flexible beam structure

A helicopter rotor and flexible beam technology, applied in the field of helicopter rotor system, can solve the problem that it is difficult to make full use of the coupling effect of helicopter rotor shimmy and torsional motion

Inactive Publication Date: 2017-01-11
HUNAN UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Traditional articulated and star-shaped flexible rotors are difficult to make full use of the flapping, shimmy and torsional motions of helicopter rotors and their coupling effects

Method used

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  • Helicopter rotor system with flexible beam structure
  • Helicopter rotor system with flexible beam structure
  • Helicopter rotor system with flexible beam structure

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0050] The proposed helicopter rotor system of the application of the present invention is as figure 1 and 2 As shown, the shimmy torsion beam device 5 and the flapping torsion beam device 7 are respectively used to realize the flapping, shimmy and torsional motions of the rotor system. In this device, the waving motion and the shimmy motion are respectively realized by the two devices, and both the waving motion device and the shimmy motion device can be combined with the twisting motion to form a waving torsion beam device and a shimmy torsion beam device.

[0051] The hub connection device 2 is the part connecting the rotor system with the rotor hub of the helicopter body structure. The flexible beam structure is connected to the hub connection device 2 through the inner assembly ring 3 and the outer assembly ring 4, and the inner assembly ring 3 is directly connected to the hub On the connecting device 2 , the outer assembly ring 4 is connected with the inner assembly rin...

Embodiment 2

[0073] In order to make better use of the shimmy swing torsional coupling effect, this embodiment makes the following changes on the basis of the original embodiment 1, as follows Figure 11 The shimmy torsional deformation structure 16 shown with Figure 7 Compared with the vertical plane, the shimmy torsional deformation structure 16 shown is a slope of 45°.

[0074] Such as Figure 13-15 The swinging torsion deformation structure 25 in the swinging torsion beam device 7 shown is also a 45° slope.

[0075] Through the above structural types and connection methods, not only flapping, shimmy and torsional motions can be generated during the movement of the helicopter, but also the effects of flapping torsional coupling and shimmy torsional coupling can be fully utilized, so as to achieve accurate and efficient control of rotor blade 1 motion , and then realize the manipulation and control of the helicopter.

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Abstract

The invention discloses a helicopter rotor system with a flexible beam structure. The helicopter rotor system comprises a blade (1), and further comprises a shimmy torsion beam device (5) and a swing torsion beam device (7). The swing torsion beam device (7) is fixedly connected with the shimmy torsion beam device (5) through side plates (6). The swing torsion beam device (7) is rotatably connected with the blade (1) through a socket device. The helicopter rotor system has the advantages of being simple in structure and the like, the swing, shimmy and torsion and coupling effects of the swing, shimmy and torsion can by fully used, and the dynamic characteristics of the helicopter rotor system are greatly improved. Meanwhile, the helicopter rotor system has the characteristic of high adaptability, and is suitable for rotor structures of various helicopters, such as inarticulate helicopters.

Description

technical field [0001] The invention relates to a helicopter rotor structure, in particular to a helicopter rotor system with a flexible beam structure. Background technique [0002] Since the helicopter has a vertical take-off and landing function, it can be applied to various complex terrains and areas that cannot be reached by fixed-wing aircraft, and has strong adaptability. The rotor provides lift and control force for the helicopter and is one of the core components of the helicopter. It not only has a direct impact on the aerodynamic performance of the helicopter, but also the vibration and noise generated by the rotor blades are the main factors affecting the comfort and fatigue life of the helicopter structure. one. [0003] At present, the helicopter rotor system is mainly articulated or star-shaped flexible rotors, which have the disadvantages of complex structure and low structural efficiency. Helicopter rotors have three types of movement: flapping, shimmy and...

Claims

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Application Information

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IPC IPC(8): B64C27/32
Inventor 任毅如甘磊方棋洪张田田孟少华
Owner HUNAN UNIV
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