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Electronic speed controller controlled variable-pitch rotor system module and helicopter

A technology of electronic control and system modules, which is applied in the field of helicopters, can solve the problems of large complexity of rotor power system and variable pitch control mechanism, hidden dangers of reliability and safety, and inconvenient system assembly, so as to reduce processing and assembly time, Avoid the effect of stability and improve battery life

Pending Publication Date: 2020-06-09
南京韬讯航空科技有限公司
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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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  • Electronic speed controller controlled variable-pitch rotor system module and helicopter
  • Electronic speed controller controlled variable-pitch rotor system module and helicopter
  • Electronic speed controller controlled variable-pitch rotor system module and helicopter

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0051] Such as figure 1 Shown is a variable-pitch rotor system module disclosed in this embodiment. One end of the lead-lag variable-pitch clip 7 is fixedly connected to one end of the blade 8, and the other end of the lead-lag variable-pitch clip 7 is connected to the flapping connector 6. One end of the waving connector 6 is hinged with the propeller hub 5; the propeller hub 5 is fixedly connected with the power output shaft of the power module 2; in the rotor system, two blades 8, two A lead-lag variable pitch propeller clip 7; the angle measurement unit 3 is to measure the rotation position angle of the power module 2, and is installed coaxially with the power module 2; the electronic governor 4 can control the power module 2 at various positions in the rotation, and change the output Torque; the angle measurement unit 3 detects the angle information of the rotational position of the power module 2, and after obtaining the angle information, the electronic governor 4 contr...

Embodiment 2

[0060] This embodiment discloses a coaxial double-deck variable pitch helicopter, such as Figure 6 to Figure 8 One configuration is shown. The coaxial double-deck variable-pitch helicopter is equipped with two sets of variable-pitch rotor system modules controlled by electric regulation as in Embodiment 1; the two sets of variable-pitch rotor system modules controlled by electric regulation are coaxially assembled.

[0061] This embodiment discloses a coaxial double-deck variable-pitch helicopter, and its coaxial assembly method is any one of the following four types:

[0062] 1. If Image 6 As shown, the two sets of power modules 2 are external;

[0063] 2. If Figure 7 As shown, the two sets of power modules 2 are all placed in the middle;

[0064] 3-4, such as Figure 8 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.

[0065] In the coaxial double-deck variable-pitch helicopter disclosed in this...

Embodiment 3

[0067] This embodiment discloses a coaxial single-deck variable pitch helicopter, such as Figure 9 to Figure 12 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 of them is configured as the variable-pitch rotor system module controlled by the electric control of Embodiment 1, and the other set of rotor systems is fixed-axis without variable pitch rotor system; such as Figure 5 The fixed-axis non-variable-pitch rotor system includes a central shaft 1 , a power module 2 , a propeller hub assembly 9 , a propeller clip 10 , and a propeller blade 8 . Wherein, the central shaft 1 is fixedly connected with the power module 2; the torque output shaft of the power module 2 is fixedly connected with the hub assembly piece 9; The roots are hinged.

[0068] This embodiment discloses a coaxial single-deck variable-pitch helicopter, and its coaxial assembly metho...

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Abstract

The invention discloses an electronic speed controller controlled variable-pitch rotor system module, which comprises a central shaft, a power module, an angle measuring unit, an electronic speed controller, a propeller hub, a flapping connecting piece, lead-lag variable-pitch propeller clamps and propeller blades. According to the invention, a serverless periodic variable-pitch scheme is adopted,the power module is controlled by the electronic speed controller to periodically change torque, a rotor can make lagging or advancing action through dynamic torque output, and the blade pitch can bechanged while the propeller blades move in an advancing or lagging mode through the special structure adopted by the invention. The variable pitch effect of a traditional swash plate is obtained by passively coupling horizontal hinges moving vertically and horizontally and responding to pulse torque; in order to achieve the variable pitch purpose, a variable pitch rotor system in the prior art isgenerally provided with a complex control connecting rod mechanism, and the manufacturing difficulty is large, the cost is high and the service life is short. According to the invention, the structure is greatly simplified, the traditional complex control mechanism is abandoned, the weight of the rotor system is reduced, and the material cost and the manufacturing difficulty are lowered.

Description

technical field [0001] The invention relates to the field of helicopters, in particular to an electronically controlled variable-pitch rotor system module and a helicopter. Background technique [0002] Existing helicopter rotor systems usually include a rotor power system and a variable-pitch control system. The rotor power system includes power modules, connecting shafts, rotor mechanisms, etc. 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 system assembly. Therefore, the ...

Claims

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Application Information

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IPC IPC(8): B64C11/30B64C11/44B64D35/00B64D27/00
CPCB64C11/30B64C11/44B64D27/00B64D35/00Y02T50/40
Inventor 葛讯沈元郭述臻李良伟刘卫东
Owner 南京韬讯航空科技有限公司
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