A fastening device for an aircraft propeller composite fairing

Abstract

The present invention belongs to the technical field of fasteners and relates to a fastening device for an aircraft propeller composite fairing. It includes a reinforcing plate, a bracket, a snap ring, a fixing pin, a fixing nail, a lock body, a flanging bushing, and a protective sheet; the fixing pins and the fixing nails are respectively in several groups; by adopting a fastening device for an aircraft propeller composite fairing, the device can be used in a smaller space, and multiple groups of fasteners can be used simultaneously to meet the assembly requirements and realize the connection of composite thin-walled parts.

Description

Technical Field

[0001] The present invention belongs to the technical field of fasteners and relates to a fastening device for an aircraft propeller composite fairing. Background Art

[0002] The propeller composite fairing is composed of a mounting plate and a propeller cap, both of which are thin-walled parts and the materials are both carbon fiber and glass fiber. The connection and fastening between the two are relatively difficult, and the requirements are as follows:

[0003] a. The fastening device shall not affect the overall aerodynamic performance of the fairing;

[0004] b. Multiple groups of fasteners are required for the connection to solve the problem of over-positioning;

[0005] c. At the same time, the required space is small;

[0006] d. The connection is safe and reliable;

[0007] e. The connection can be disassembled multiple times and is convenient to disassemble;

[0008] f. The number of holes in the composite material should be minimized;

[0009] g. Once an individual fastener fails, the part cannot fall off randomly, and the safety factor of the aircraft needs to be ensured.

[0010] All of the above problems need to be solved. Summary of the Invention

[0011] The purpose of the present invention is to provide a fastening device for an aircraft propeller composite fairing to solve the fastening problem of a propeller composite fairing.

[0012] The technical solution of the present invention: A fastening device for an aircraft propeller composite fairing, characterized in that it includes a reinforcing plate 1, a bracket 2, a snap ring 3, a fixing pin 4, a fixing nail 5, a lock body 6, a flanged bushing 7, and a protective sheet 8; the fixing pin 4 and the fixing nail 5 are respectively in several groups;

[0013] The reinforcing plate 1 is an annular plate, the edge of which is erected to form a side wall perpendicular to the annular plate surface; the side wall of the reinforcing plate 1 is connected and fixed to the composite propeller cap; a plurality of circular holes are opened on the annular plate surface of the reinforcing plate; the bracket 2 is a circular ring, the edge of which is provided with a plurality of circular holes; the clamping ring 3 is a circular ring, the edge of which is provided with a plurality of waist-shaped grooves and circular grooves; the fixing pin 4 is a pointed waist-shaped pin with a thread at the top, connected to the reinforcing plate 1 by a nut; the fixing nail 5 is a blunt waist-shaped nail with a thread at the top, The lock body 6 is connected to the reinforcing plate 1 through a nut; the lock body 6 is a mechanical switch mechanism, including a spring, a pin and a handle; the snap ring 3 is provided with a pin hole matched with the pin; the handle is connected to the snap ring 3; the spring is connected to the pin; the pin can be inserted into or pulled out of the pin hole by turning the spring; when the pin is pulled out of the pin hole of the snap ring 3, the pin is hidden, and the snap ring 3 is rotated by turning the handle at this time; the flanged bushing 7 is cylindrical, and both ends can be flanged; the protective sheet 8 is an L-shaped gasket, and a round hole is opened on one side of the L-shape;

[0014] The top end of the fixing pin 4 or the fixing nail 5 passes through the circular hole of the reinforcing plate 1 and is fastened with a nut; the snap ring 3 is assembled between the bracket 2 and the hub; the flanged bushing 7 passes through the circular hole of the protective sheet 8, and the flanged bushing 7 is fixed to the protective sheet 8 by flanges on both sides;

[0015] A circular hole on the edge of the bracket 2, a waist-shaped groove on the edge of the clamping ring 3, a circular hole on the protective sheet 8, and a flanged bushing are on the same axis and together constitute a fixing pin hole or a fixing nail hole; the fixing pin hole or the fixing nail hole respectively cooperates with the corresponding fixing pin 4 or fixing nail.

[0016] Furthermore, the side wall of the reinforcing plate 1 is connected and fixed to the composite propeller cap by rivets.

[0017] Furthermore, the number of the fixing pins 4 and the fixing nails 5 is 5 to 8 groups respectively.

[0018] Furthermore, the bracket 2, the retaining ring 3 and the hub are fixedly connected by 10 sets of standard bolt thread parts.

[0019] Beneficial effects of the present invention: The present invention adopts a composite fairing fastening device for aircraft propellers. The device can be used in a relatively small space, and multiple sets of fasteners can be used simultaneously, meeting assembly requirements and realizing the connection of thin-walled composite parts. In addition, the overall aerodynamic shape of the fairing assembly is not affected, and the parts are easy to disassemble. The propeller cap and other parts can be disassembled without removing the bracket from the propeller hub, which is convenient for the maintenance of the propeller in the field. Moreover, the failure of individual parts will not affect the safety of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 Schematic diagram of the reinforcement plate;

[0021] Figure 2 is a schematic diagram of the bracket;

[0022] Figure 3 For the clasp;

[0023] Figure 4 is a schematic diagram of the fixing pin structure;

[0024] Figure 5 It is a schematic diagram of the fixing nail structure;

[0025] Figure 6 It is a schematic diagram of the lock body;

[0026] Figure 7 For the flange bushing;

[0027] Figure 8 For protection film;

[0028] Among them, 1-reinforcement plate, 2-bracket, 3-clamp ring, 4-fixing pin, 5-fixing nail, 6-lock body, 7-flanged bushing, 8-protective sheet. DETAILED DESCRIPTION

[0029] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments:

[0030] like Figures 1 to 6 As shown, a composite fairing fastening device for an aircraft propeller comprises a reinforcing plate 1, a bracket 2, a clamping ring 3, a fixing pin 4, a fixing nail 5, a locking body 6, a flanged bushing 7, and a protective sheet 8.

[0031] The number of the fixing pins 4 and the fixing nails 5 is 5 to 8 groups respectively.

[0032] The reinforcing plate 1 is an annular plate, the edge of which stands upright to form a side wall perpendicular to the annular plate surface; the side wall of the reinforcing plate 1 is connected and fixed to the composite propeller cap by rivets; a plurality of circular holes are opened on the annular plate surface of the reinforcing plate; the bracket 2 is a circular ring, the edge of which is provided with a plurality of circular holes; the retaining ring 3 is a circular ring, the edge of which is provided with a plurality of waist-shaped grooves and circular grooves; the fixing pin 4 is a pointed waist-shaped pin with a thread at the top, connected to the reinforcing plate 1 by a nut; the fixing nail 5 is a blunt waist-shaped nail with a thread at the top, connected to the reinforcing plate 1 by a nut The lock body 6 is a mechanical switch mechanism, including a spring, a pin and a handle; the snap ring 3 is provided with a pin hole matched with the pin; the handle is connected to the snap ring 3; the spring is connected to the pin; the pin can be inserted into or pulled out of the pin hole by turning the spring; when the pin is pulled out of the pin hole of the snap ring 3, the pin is hidden, and at this time, the handle is turned, and the snap ring 3 is rotated to achieve the locking of the fairing, and the fairing can also be opened by the same token; the flanged bushing 7 is a cylindrical shape, and both ends can be flanged; the protective sheet 8 is an L-shaped gasket, and a round hole is opened on one side of the L-shape;

[0033] The top end of the fixing pin 4 or the fixing nail 5 passes through the round hole of the reinforcing plate 1 and is fastened with a nut; the snap ring 3 is assembled between the bracket 2 and the hub; the flanged bushing 7 passes through the round hole of the protection piece 8, and the flanged bushing 7 and the protection piece 8 are fixed by flanging on both sides;

[0034] A round hole at the edge of the bracket 2, a waist-shaped groove at the edge of the snap ring 3, the round hole of the protection piece 8, and the flanged bushing are on the same axis, jointly forming a fixing pin hole or a fixing nail hole; the fixing pin hole or the fixing nail hole is respectively matched with the corresponding fixing pin 4 or fixing nail.

[0035] The bracket 2, the snap ring 3, and the hub are fixedly connected by 10 sets of bolt thread standard parts.

Claims

1. A fastening device for an aircraft propeller composite fairing, characterized in that: The fastening device comprises a reinforcing plate (1), a bracket (2), a snap ring (3), a fixing pin (4), a fixing nail (5), a lock body (6), a flanged bushing (7), and a protective sheet (8); the fixing pins (4) and the fixing nails (5) are respectively 5 to 8 groups; The reinforcing plate (1) is an annular plate, the edge of which is erected to form a side wall perpendicular to the annular plate surface; the side wall of the reinforcing plate (1) is connected and fixed to the composite propeller cap by rivets; a plurality of circular holes are opened on the annular plate surface of the reinforcing plate; the bracket (2) is a circular ring, the edge of which is provided with a plurality of circular holes; the clamping ring (3) is a circular ring, the edge of which is provided with a plurality of waist-shaped grooves and circular grooves; the fixing pin (4) is a pointed waist-shaped pin with a thread at the top, and is connected to the reinforcing plate (1) by a nut; the fixing nail (5) is a blunt waist-shaped nail with a thread at the top , connected to the reinforcing plate (1) through a nut; the lock body (6) is a mechanical switch mechanism, including a spring, a pin and a handle; the snap ring (3) is provided with a pin hole matched with the pin; the handle is connected to the snap ring (3); the spring is connected to the pin; the pin can be inserted into or pulled out of the pin hole by turning the spring; when the pin is pulled out of the pin hole of the snap ring (3), the pin is hidden, and at this time, the snap ring (3) is rotated by turning the handle; the flanged bushing (7) is cylindrical, and both ends can be flanged; the protective sheet (8) is an L-shaped gasket, and a round hole is opened on one side of the L-shape; The top end of the fixing pin (4) or the fixing nail (5) passes through the circular hole of the reinforcing plate (1) and is fastened with a nut; the snap ring (3) is assembled between the bracket (2) and the hub; the flanged bushing (7) passes through the circular hole of the protective sheet (8), and the flanged bushing (7) is fixed to the protective sheet (8) by flanges on both sides; A circular hole on the edge of the bracket (2), a waist-shaped groove on the edge of the clamping ring (3), a circular hole of the protective sheet (8), and a flanged bushing are on the same axis and together form a fixing pin hole or a fixing nail hole; the fixing pin hole or the fixing nail hole are respectively matched with the corresponding fixing pin (4) or fixing nail.

2. The fastening device for the aircraft propeller composite fairing according to claim 1, wherein: The bracket (2), the clamping ring (3) and the propeller hub are fixedly connected by 10 groups of bolt thread standard parts.

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