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Two-steering-engine fixed-axis variable-pitch rotor wing module and helicopter

A technology for helicopters and rotors, applied in the field of helicopters, can solve the problems of large complexity of rotor power systems and variable pitch control mechanisms, high processing and manufacturing costs, and inconvenient system assembly and assembly.

Pending Publication Date: 2020-03-24
SUZHOU TAOXUN AVIATION TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The complex operating mechanism will not only make the processing and manufacturing cost higher, but also bring inconvenience to the assembly of the entire system assembly
Therefore, the rotor power system and pitch control mechanism in the existing helicopter rotor system not only have very large complexity in the process of design, manufacture and assembly, but also have greater reliability and safety during actual flight. Hidden danger

Method used

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  • Two-steering-engine fixed-axis variable-pitch rotor wing module and helicopter
  • Two-steering-engine fixed-axis variable-pitch rotor wing module and helicopter
  • Two-steering-engine fixed-axis variable-pitch rotor wing module and helicopter

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0037] Such as figure 1 Shown is a fixed-axis and variable-pitch rotor module with two steering gears disclosed in this embodiment, including a central axis 1, a power module 2, a servo mount 3, a propeller hub 4, a rotor pitch-variable member 5, a propeller clamp 6, and a rotor 7. Servo 8, rocker arm 9, connecting rod 10, tilting disc 11, rotating tilting disc 12, centripetal center piece 13, pitch-changing link 14, rotor pitch-changing side rod 15, tilting disc limiter 16 One end of the central axis 1 is fixedly connected to the base of the power module 2, and the other end is fixedly connected to the servo mounting seat 3 to form a fixed frame structure in the center of the system; the propeller hub 4 is fixedly connected to the torque output end of the power module 2 , one end of the rotor pitch changer 5 is hinged to the propeller hub 4, and the other end is hinged to one end of the propeller clip 6; the other end of the propeller clip 6 is hinged to the root of the rotor...

Embodiment 2

[0042] This embodiment discloses a coaxial double-deck variable pitch helicopter, such as Figure 3 to Figure 5One configuration is shown. The coaxial double-deck variable-pitch helicopter is equipped with two sets of fixed-axis variable-pitch rotor systems as described in Embodiment 1; the two sets of fixed-axis variable-pitch rotor systems are coaxially assembled.

[0043] This embodiment discloses a coaxial double-deck variable-pitch helicopter, and its coaxial assembly method is any one of the following four types:

[0044] 1. If image 3 As shown, the two sets of power modules 2 are external;

[0045] 2. If Figure 4 As shown, the two sets of power modules 2 are all placed in the middle;

[0046] 3-4, such as Figure 5 As shown, one set of power modules 2 is placed in the middle, and the other set of power modules 2 is placed up or down.

[0047] In the coaxial double-deck variable-pitch helicopter disclosed in this embodiment, the power module 2 can be any one of d...

Embodiment 3

[0049] This embodiment discloses a coaxial single-deck variable pitch helicopter, such as Figure 6 to Figure 9 One configuration is shown. The coaxial single-layer variable-pitch helicopter includes two sets of rotor systems; the two sets of rotor systems are coaxially assembled; one set is configured as the fixed-axis variable-pitch rotor system described in Embodiment 1, and the other set of rotor systems It is a fixed-axis non-variable-pitch rotor system; such as figure 2 The fixed-axis non-variable-pitch rotor system includes a central shaft 1 , a power module 2 , a paddle clamp assembly 17 , a paddle clamp 6 , and a rotor 7 . Wherein, the central shaft 1 is fixedly connected to the power module 2; the torque output shaft of the power module 2 is fixedly connected to the paddle clamp assembly piece 17, and one end of the paddle clamp 6 is hinged to one end of the paddle clamp assembly piece 17, The other end is hinged with rotor 7 roots.

[0050] This embodiment discl...

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PUM

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Abstract

The invention discloses a two-steering-engine fixed-axis variable-pitch rotor wing module The Two-steering-engine fixed-axis variable-pitch rotor wing module comprises a central shaft, a power module,a server mounting seat, a propeller hub, a rotor wing variable-pitch part, a propeller clamp, a rotor wing, servers, a rocker arm, a connecting rod, a tilting disc, a rotary tilting disc, a variable-pitch connecting rod, a rotor wing variable-pitch part side rod, tilting disc extension rods and tilting disc limiters. According to the scheme, two servers are adopted to control variable pitch, heading and lifting motion is adjusted by increasing and decreasing rotating speed control, rolling and pitching motion is adjusted by the inclination angle of the periodic torque conversion mechanism, and a variable pitch mechanism and a synchronous mechanism in the variable pitch control system are integrally designed. According to the invention, a helicopter control mechanism and a synchronizationstructure are greatly simplified. Meanwhile, a fixed shaft scheme is adopted, so that the size of the whole rotor system is reduced, and the problems of poor stability, vibration, friction and the like during movement of the slender rotating shaft are avoided. In addition, the scheme is simple and compact in structure, and can be combined and designed as a standardized module. The invention further discloses a plurality of different types of helicopter configurations adopting the fixed-axis variable-pitch rotor wing system.

Description

technical field [0001] The invention relates to the field of helicopters, in particular to a fixed-axis and variable-pitch rotor module with two steering gears and a helicopter. Background technique [0002] Existing helicopter rotor systems usually include a rotor power system and a variable-pitch control system. Among them, the rotor power system includes a power module, a connecting shaft, a rotor mechanism and the like. In the existing scheme, the distance between the rotor mechanism and the power module is usually far, and it needs to be connected by a slender connecting shaft. During the periodic rotation, problems such as instability, vibration, and friction will occur. The variable-distance control system includes complex control mechanisms such as a distance-variable mechanism and a synchronous mechanism. The complex operating mechanism will not only make the processing and manufacturing cost higher, but also bring inconvenience to the assembly of the entire syste...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/59B64C27/625
CPCB64C27/59B64C27/625B64U10/10
Inventor 葛讯沈元郭述臻李良伟刘卫东
Owner SUZHOU TAOXUN AVIATION TECH CO LTD