Aircraft canopy supporting rod fastening structure and fastening method thereof

Abstract

The invention belongs to the technical field of design of aircraft canopy supporting rod fastening structures, and particularly relates to an aircraft canopy supporting rod fastening structure and a fastening method thereof.The aircraft canopy supporting rod fastening structure comprises a force bearing block, a bolt and a nut; the bearing block is hinged to one end of the supporting rod; the other end of the supporting rod is hinged to the cabin cover, the cabin cover is installed on the cabin force bearing frame, and a strip-shaped installation hole is formed in the cabin force bearing frame. The bolt penetrates through the strip-shaped through hole, and the head is rectangular; anti-rotation grooves are formed in the top ends of the bolts; the nut is screwed on the bolt; the nut is a butterfly nut; the rectangular heads of the adjusting bolts are parallel to the strip-shaped mounting holes in the cockpit force bearing frame and can penetrate through the strip-shaped mounting holes, the rectangular heads of the adjusting bolts are perpendicular to the strip-shaped mounting holes in the cockpit force bearing frame, the nuts are tightened, the force bearing block can be fastened to the cockpit force bearing frame, and therefore the supporting rods are fastened, and the cockpit cover is supported at the opening position.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft canopy support rod fastening structure design, and specifically relates to an aircraft canopy support rod fastening structure and a fastening method thereof. Background Art

[0002] When an aircraft with a canopy is parked, in some cases, it is necessary to support the canopy in an open position with a support rod. For this purpose, an aircraft canopy support rod fastening structure is designed to fasten the support rod to support the canopy in an open position.

[0003] Currently, the aircraft canopy support rod fastening structure is designed with a complex structure, which makes it difficult to ensure reliable fastening of the support rod, presents a great safety hazard, and is heavy and bulky. In addition, it is difficult to operate and has no adjustment function.

[0004] This application is proposed in view of the above-mentioned technical defects. Summary of the invention

[0005] The purpose of the present application is to provide an aircraft canopy support rod fastening structure and a fastening method thereof, so as to overcome or alleviate at least one aspect of the known technical defects.

[0006] The technical solution of this application is:

[0007] On the one hand, an aircraft canopy support rod fastening structure is provided, comprising a load-bearing block, a bolt, and a nut;

[0008] The load-bearing block is hinged at one end of the support rod;

[0009] The other end of the support rod is hinged on the cockpit cover, and the cockpit cover is installed on the cockpit bearing frame, and the cockpit bearing frame is provided with a strip-shaped mounting hole;

[0010] The bolt passes through the strip-shaped through hole, and the head is rectangular; the top of the bolt has an anti-rotation groove;

[0011] The nut is screwed onto the bolt; the nut is a butterfly nut;

[0012] Adjust the rectangular head of the bolt to be parallel to the strip mounting hole on the cockpit load-bearing frame and be able to pass through the strip mounting hole. Adjust the rectangular head of the bolt to be perpendicular to the strip mounting hole on the cockpit load-bearing frame and tighten the nut to fasten the load-bearing block to the cockpit load-bearing frame, thereby fastening the support rod and supporting the cockpit cover in the open position.

[0013] According to at least one embodiment of the present application, in the above-mentioned aircraft canopy support rod fastening structure, the load-bearing block and the support rod are hinged with pins through the cooperation of a single-double-ear structure.

[0014] According to at least one embodiment of the present application, in the above-mentioned aircraft canopy support rod fastening structure, the anti-rotation groove at the top end of the bolt is in a straight line shape.

[0015] According to at least one embodiment of the present application, in the above-mentioned aircraft canopy support rod fastening structure, the load-bearing block is made of metal with good salt spray resistance, light weight and wear resistance;

[0016] The bolts are made of metal that is good in salt spray resistance, light in weight and wear-resistant;

[0017] The nut is made of metal with good salt spray resistance, light weight and wear resistance.

[0018] On the other hand, a method for fastening an aircraft canopy support rod is provided, which is implemented based on any of the above-mentioned aircraft canopy support rod fastening structures, and comprises:

[0019] Adjust the rectangular head of the bolt to be parallel to the strip-shaped mounting hole on the cabin bearing frame, and pass the entire rectangular head of the bolt through the strip-shaped mounting hole on the cabin bearing frame;

[0020] Adjust the rectangular head of the adjusting bolt to be perpendicular to the strip-shaped mounting hole on the cockpit bearing frame;

[0021] Insert a wrench into the anti-rotation groove, tighten the nut, and fasten the load-bearing block to the cockpit load-bearing frame.

[0022] This application has at least the following beneficial technical effects:

[0023] Provided are a fastening structure for a support rod of an aircraft canopy and a fastening method thereof. The overall structure of the support rod fastening structure for an aircraft canopy is simple, and the weight and volume are small, so that reliable fastening of the support rod can be ensured. The fastening of the support rod can be achieved by simply adjusting the parallelism and verticality of the rectangular head of the bolt and the strip-shaped mounting hole on the cabin load-bearing frame, and tightening the nut, etc., and the operation is simple and convenient. In addition, when the nut is loose, the bearing block can be slid by utilizing the clearance between the strip-shaped through hole on the bearing block and the bolt, so that the fastening state of the support rod can be adjusted, and the opening position of the canopy can be adjusted, and the structure has a certain adjustment function. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 is a schematic diagram of an aircraft canopy support rod fastening structure provided in an embodiment of the present application;

[0025] Figure 2 is a schematic diagram of a bolt provided in an embodiment of the present application;

[0026] Figure 3 is a schematic diagram of a nut provided in an embodiment of the present application;

[0027] Figure 4is a schematic diagram of fastening a support rod by a cockpit canopy support rod fastening structure provided in an embodiment of the present application;

[0028] in:

[0029] 1-load-bearing block; 2-bolt; 3-nut; 4-support rod; 5-cockpit load-bearing frame.

[0030] In order to better illustrate the present embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and should not be construed as limitations on the present application. DETAILED DESCRIPTION

[0031] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be described in further detail in detail and in detail with reference to the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design.

[0032] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall have the usual meanings understood by those of ordinary skill in the art to which this application belongs. The words used in the description of this application to indicate orientation are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "include" used in the description of this application indicates that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0033] In addition, it should be noted that, unless otherwise clearly specified and limited, the words "installation", "connection" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Technical personnel in the field can understand its specific meaning in this application according to the specific circumstances.

[0034] An aircraft canopy support rod fastening structure, such as Figure 1 As shown, it includes a load-bearing block 1, a bolt 2, and a nut 3.

[0035] The load-bearing block 1 is hinged at one end of the support rod 4, and can be specifically hinged by a single-ear and double-ear structure with a pin. There is a strip through hole on the load-bearing block 1. The load-bearing block 1 is made of metal with good salt spray resistance, light weight and wear resistance.

[0036] The other end of the support rod 4 is hinged on the cockpit cover, and the cockpit cover is installed on the cockpit load-bearing frame 5. The cockpit load-bearing frame 5 is provided with a strip-shaped installation hole.

[0037] The bolt 2 is provided through the strip-shaped through hole, and the head is rectangular. The top of the bolt 2 has an anti-rotation groove, which is in a straight line shape. The bolt 2 is made of metal with good salt spray resistance, light weight, and wear resistance, such as Figure 2 shown.

[0038] Nut 3 is a butterfly nut, which is screwed onto bolt 2. Nut 3 is made of metal with good salt spray resistance, light weight and wear resistance, such as Figure 3 shown.

[0039] The rectangular head of the adjustment bolt 2 is parallel to the strip mounting hole on the cabin bearing frame 5 and can pass through the strip mounting hole. The rectangular head of the adjustment bolt 2 is perpendicular to the strip mounting hole on the cabin bearing frame 5. Tightening the nut 3 can fasten the bearing block 1 to the cabin bearing frame 5, thereby fastening the support rod 4 and supporting the cockpit cover in the open position, such as Figure 4 shown.

[0040] When tightening the nut 3, a wrench can be inserted into the anti-rotation groove to prevent the bolt 2 from rotating, so that the rectangular head is parallel to the strip mounting hole on the cabin load-bearing frame 5 and then escapes from the strip mounting hole.

[0041] The aircraft cockpit cover support rod fastening structure disclosed in the above embodiment has a simple overall structure, and is small in weight and volume, and can ensure reliable fastening of the support rod 4. Moreover, the fastening of the support rod 4 is achieved only by adjusting the parallelism and verticality of the rectangular head of the bolt 2 and the strip mounting hole on the cockpit load-bearing frame 5, and tightening the nut 3 and other simple operations. The operation is simple and convenient. In addition, when the nut 3 is loose, the clearance between the strip through hole on the load-bearing block 1 and the bolt 2 can be utilized to slide the load-bearing block 1, so as to adjust the fastening state of the support rod 4 and the opening position of the cockpit cover, and the structure has a certain adjustment function.

[0042] A method for fastening a support rod of an aircraft canopy is implemented based on the aircraft canopy support rod fastening structure disclosed in the above embodiment, comprising:

[0043] Adjust the rectangular head of the bolt 2 to be parallel to the strip-shaped mounting hole on the cabin bearing frame 5, and pass the entire rectangular head of the bolt 2 through the strip-shaped mounting hole on the cabin bearing frame 5;

[0044] Adjust the rectangular head of the adjusting bolt 2 to be perpendicular to the strip-shaped mounting hole on the cabin bearing frame 5;

[0045] Insert a wrench into the anti-rotation groove, tighten the nut 3, and fasten the load-bearing block 1 to the cabin load-bearing frame 5.

[0046] The aircraft canopy support rod fastening method disclosed in the above embodiment is implemented based on the aircraft canopy support rod fastening structure disclosed in the above embodiment, and the description is relatively simple. For specific related matters, please refer to the relevant description of the aircraft canopy support rod fastening structure part. Its technical effects can also refer to the technical effects of the relevant parts of the aircraft canopy support rod fastening structure, which will not be repeated here.

[0047] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the scope of protection of the present application.

Claims

1. An aircraft canopy support rod fastening structure, characterized in that: It comprises a load-bearing block (1), a bolt (2) and a nut (3); The load-bearing block (1) is hinged to one end of the support rod (4); The other end of the support rod (4) is hinged on the cockpit cover, and the cockpit cover is installed on the cockpit load-bearing frame (5), and the cockpit load-bearing frame (5) is provided with a strip-shaped installation hole; The bolt (2) is arranged to pass through the strip-shaped through hole, and the head thereof is rectangular; the top end of the bolt (2) is provided with an anti-rotation groove; The nut (3) is threaded onto the bolt (2); the nut (3) is a butterfly nut; The rectangular head of the adjusting bolt (2) is parallel to the strip mounting hole on the cabin load-bearing frame (5) and can pass through the strip mounting hole. The rectangular head of the adjusting bolt (2) is perpendicular to the strip mounting hole on the cabin load-bearing frame (5). The nut (3) is tightened to fasten the load-bearing block (1) to the cabin load-bearing frame (5), thereby fastening the support rod (4) and supporting the cabin cover in the open position.

2. The aircraft canopy support rod fastening structure according to claim 1, characterized in that: The load-bearing block (1) and the support rod (4) are hinged by pins through the cooperation of a single-ear and double-ear structure.

3. The aircraft canopy support rod fastening structure according to claim 2, characterized in that: The anti-rotation groove at the top end of the bolt (2) is in a straight line shape.

4. The aircraft canopy support rod fastening structure according to claim 3, characterized in that: The load-bearing block (1) is made of metal having good salt spray resistance, light weight and wear resistance; The bolt (2) is made of metal having good salt spray resistance, light weight and wear resistance; The nut (3) is made of metal having good salt spray resistance, light weight and wear resistance.

5. A method for fastening an aircraft canopy support rod, implemented based on the aircraft canopy support rod fastening structure according to claim 4, characterized in that: include: The rectangular head of the adjustment bolt (2) is parallel to the strip-shaped mounting hole on the cabin load-bearing frame (5), and the rectangular head of the entire bolt (2) is passed through the strip-shaped mounting hole on the cabin load-bearing frame (5); Adjust the rectangular head of the adjusting bolt (2) to be perpendicular to the strip-shaped mounting hole on the cabin load-bearing frame (5); Insert a wrench into the anti-rotation groove, tighten the nut (3), and fasten the load-bearing block (1) to the cabin load-bearing frame (5).

Images