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Helicopter main rotor wing spar composite structure and assembling method thereof

A composite structure and main rotor technology, applied in rotorcraft, aircraft assembly, motor vehicles, etc., can solve the problems of inconvenient spar weight adjustment, cumbersome process, and reduced production efficiency, so as to improve product quality, production efficiency, and operation simple effect

Pending Publication Date: 2022-07-22
上海喆航航空科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] When manufacturing complex composite parts in the aviation industry, it is often necessary to manufacture them in multiple steps to avoid multiple model splits due to closed corners, in this case composite structures of pre-assembled parts are recommended, among them, helicopter One of the most critical parts of the main rotor blade is the wing spar, which is the longitudinal dynamic element of the blade. The existing assembly structure of the wing spar composite structure is not convenient for adjusting the weight of the spar during assembly. At the same time, the composite structure Poor strength and cumbersome process, resulting in poor product quality, inconvenient production, and reduced production efficiency

Method used

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  • Helicopter main rotor wing spar composite structure and assembling method thereof
  • Helicopter main rotor wing spar composite structure and assembling method thereof
  • Helicopter main rotor wing spar composite structure and assembling method thereof

Examples

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Embodiment 1

[0025] A composite structure of a helicopter main rotor spar, comprising a spar body 1, the spar body 1 is covered with an inner bag layer 2; the top of the spar body 1 is provided with a plastic part 3, and the plastic part 3 is provided with a metal part 4 ; The spar body 1, the plastic parts 3 and the metal parts 4 are covered with a cover layer 5; the cover layer 5 is covered with an outer bag layer 6.

[0026] Specifically, the inner bag layer 2 includes a front inner bag 21 and a rear inner bag 22, and the junction of the front inner bag 21 and the rear inner bag 22 is chamfered.

[0027] It is worth noting that the inner bag layer 2 and the outer bag layer 6 are polyethylene protective films; the cover layer 5 is made of prepreg material.

Embodiment 2

[0029] An assembling method for assembling the described helicopter main rotor spar compound, comprising the following steps:

[0030] Step 1: wrap the inner bag layer 2 on the outside of the spar body 1, and squeeze it through a scraper, so that the inner bag layer 2 is completely covered on the outer surface of the spar body 1;

[0031] Step 2: Place the plastic part 3 and the metal part 4 on the top of the spar body 1 according to the requirements of the counterweight, and coat the cover layer 5 of the prepreg material on the outside, and let the cover layer 5 dry at room temperature for 15-20 minutes ;

[0032] Step 3: The outer bag layer 6 is then pasted on the surface of the cover layer 5 and squeezed by a scraper, so that the outer bag layer 6 is completely covered on the outer surface of the cover layer 5 .

[0033] It is not difficult to see from the above content that in the helicopter main rotor spar composite structure and its assembling method, the spar body 1 ca...

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Abstract

The invention relates to the technical field of helicopter part assembly, in particular to a helicopter main rotor wing spar composite structure which comprises a spar body wrapped with an inner bag layer. A plastic part is arranged at the top of the spar body, and a metal part is arranged on the plastic part; the spar body, the plastic part and the metal part are coated with a covering layer; and an outer bag layer is coated outside the covering layer. The assembling method comprises the following steps that the outer portion of the spar body is wrapped with the inner bag layer; the plastic part and the metal part are placed at the top end of the spar body according to the balance weight requirement, and the outer portion of the plastic part and the outer portion of the metal part are coated with a covering layer made of prepreg; and an outer bag layer is pasted on the surface of the covering layer. The toughness of the spar body can be maintained through the inner bag layer, the covering layer and the outer bag layer, meanwhile, balance weight adjustment is facilitated, operation is easy, and the product quality and the production efficiency are improved.

Description

technical field [0001] The invention relates to the technical field of assembling helicopter parts, in particular to a composite structure of a main rotor spar of a helicopter and an assembling method thereof. Background technique [0002] When manufacturing complex composite parts in the aerospace industry, it is often necessary to manufacture in multiple steps to avoid multiple model splits due to closed angles. In this case, composite structures with pre-assembled parts are recommended, where helicopters One of the most critical components of the main rotor blade is the spar, which is the longitudinal dynamic element of the blade. The existing spar composite structure assembly structure is not convenient to adjust the weight of the spar during assembly. The strength is poor and the process is cumbersome, resulting in poor product quality, inconvenient production, and reduced production efficiency. In view of this, we propose a helicopter main rotor spar composite structu...

Claims

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Application Information

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IPC IPC(8): B64C27/473B64F5/10
CPCB64C27/473B64F5/10
Inventor 孙志武
Owner 上海喆航航空科技有限公司