Supporting rod assembly for opening upper opening cover of airplane body

Abstract

The utility model belongs to the technical field of design of supporting rod assemblies for opening upper covering caps of airplane bodies, and particularly relates to a supporting rod assembly for opening an upper covering cap of an airplane body. One end of the supporting rod is hinged to the first support; one end of the bent rod is connected to the other end of the supporting rod, and a ball head is formed at the other end; the second support is connected to the inner side of the wall surface of the covering cap; the buckle is connected to the second support; the lateral support is connected to the inner side of the edge of the opening frame, a vertical sliding groove is formed in the lateral support, and a spherical hole is formed in the top of the vertical sliding groove; when the opening cover is closed in the opening frame, the supporting rod can be clamped on the buckle; when the opening cover is opened from the opening frame, the supporting rod can be separated from the buckle, the ball head can be clamped into the vertical sliding groove through the spherical opening hole by rotating, and the ball head can slide along the vertical sliding groove until the ball head slides to the bottom of the vertical sliding groove in the opening process of the opening cover, so that the opening angle of the opening cover is limited and kept.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of design of a strut assembly for opening an upper hatch of an aircraft body, and particularly relates to a strut assembly for opening an upper hatch of an aircraft body. BACKGROUND

[0002] There are a large number of hatches on an aircraft, and some of the hatches need to be fixed by a strut assembly when being opened, so that the hatches can be reliably kept at a desired opening angle.

[0003] At present, the strut assembly for opening an upper hatch of an aircraft body usually has a complex structure and is not flexible and convenient to operate.

[0004] The present application is proposed in view of the above technical defects. CONTENT OF THE UTILITY MODEL

[0005] The purpose of the present application is to provide a strut assembly for opening an upper hatch of an aircraft body to overcome or alleviate at least one aspect of the known technical defects.

[0006] The technical solution of the present application is as follows:

[0007] A strut assembly for opening an upper hatch of an aircraft body comprises:

[0008] a first support connected to the inner side of a hatch wall;

[0009] a strut hingedly connected to one end of the first support;

[0010] a bent rod connected to the other end of the strut, and having a ball head formed at the other end;

[0011] a second support connected to the inner side of the hatch wall;

[0012] a buckle connected to the second support;

[0013] a lateral support connected to the inner side of a frame edge, and having a vertical sliding slot with a spherical opening at the top of the vertical sliding slot;

[0014] When the hatch is closed in the frame, the strut can be clamped on the buckle;

[0015] When the hatch is opened from the frame, the strut can be disengaged from the buckle, and the ball head can be clamped into the vertical sliding slot through the spherical opening by rotating, the ball head can slide along the vertical sliding slot during the opening of the hatch, and slide to the bottom of the vertical sliding slot, so as to limit and maintain the opening angle of the hatch;

[0016] When the hatch is closed into the frame, the ball head can slide along the vertical sliding slot until it slides to the top of the vertical sliding slot, and then can be taken out through the spherical opening, and after the hatch is closed, the strut can be clamped on the buckle by rotating.

[0017] According to at least one embodiment of the present application, in the above-mentioned strut assembly for opening the upper cover of the aircraft fuselage, the first support and the second support are in an X-shape, and the edges on both sides are connected to the inner side of the cover wall by bolts or welding;

[0018] The support rods and bent rods are connected by threads and stopped by pins;

[0019] The lateral support is in the shape of a "F" (Chinese character for "F"). The edges on both sides are connected by bolts or welded to the inner side of the edge of the frame. The vertical slide is in the shape of a V.

[0020] According to at least one embodiment of the present application, in the above-mentioned strut assembly for opening the upper cover of the aircraft fuselage, the buckle includes:

[0021] The connecting base is connected to the second support through a pin, and is formed with two opposite vertical elastic pieces, each of which has a clamping groove;

[0022] When the mouth cover is closed in the mouth frame, the support rod can be clamped into the two vertical elastic pieces and the two clamping grooves;

[0023] When the mouth cover is opened from the mouth frame, the support rod can be taken out from the two clamping grooves, and then the support rod can be removed from the two vertical elastic sheets.

[0024] According to at least one embodiment of the present application, in the above-mentioned strut assembly for opening the upper cover of the aircraft fuselage, the top of a vertical elastic piece is curled outward to form a mounting through hole;

[0025] The top of the other vertical elastic piece is bent outward to form a bayonet;

[0026] The buckle also includes:

[0027] A rectangular frame wrench, one edge of which is installed in the mounting through hole, and the opposite edge can be clamped into the two vertical elastic pieces on the support rod. After being clamped in the two clamping grooves, it is clamped into the bayonet by rotation to limit the support rod from escaping the two clamping grooves and its vertical elastic pieces. After being removed from the bayonet, the support rod can be removed from the two clamping grooves, and then escaping the two vertical elastic pieces.

[0028] According to at least one embodiment of the present application, the above-mentioned aircraft fuselage upper cover opening strut assembly further includes:

[0029] A single-ear support is connected to the first support via a pin;

[0030] The double-ear joint is connected to one end of the support rod facing the first support through threads and is stopped by a pin. It is connected to the single-ear support through a pin shaft. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Figure 1is a schematic diagram of the strutting rod assembly for opening the hatch on the aircraft body when the hatch is closed;

[0032] Figure 2 is a schematic diagram of the strutting rod assembly for opening the hatch on the aircraft body when the hatch is closed;

[0033] Figure 3 is a schematic diagram of the strutting rod assembly for opening the hatch on the aircraft body when the hatch is closed;

[0034] Figure 4 is a schematic diagram of the strutting rod assembly for opening the hatch on the aircraft body when the hatch is closed;

[0035] Figure 5 is a schematic diagram of the strutting rod assembly for opening the hatch on the aircraft body when the hatch is closed;

[0036] Figure 6 is a schematic diagram of the strutting rod assembly for opening the hatch on the aircraft body when the hatch is closed;

[0037] Figure 7 is a schematic diagram of the strutting rod assembly for opening the hatch on the aircraft body when the hatch is closed;

[0038] wherein:

[0039] 1-first support; 2-hatch; 3-strutting rod; 4-bent rod; 5-second support; 6-buckle; 7-lateral support; 8-hatch frame; 9-connection base; 10-single ear support; 11-double ear joint; 12-rectangular frame wrench.

[0040] In order to better illustrate the embodiments, some components in the drawings may be omitted, enlarged or reduced, and do not represent the actual product size. In addition, the drawings are only used for illustrative description and cannot be understood as a limitation of the application. DETAILED DESCRIPTION

[0041] In order to make the technical solutions of the application and its advantages clearer, the technical solutions of the application will be further described in detail below with reference to the drawings. It should be understood that the specific embodiments described herein are only part of the embodiments of the application, and are only used to explain the application, but not to limit the application. It should be noted that, in order to facilitate description, only parts related to the application are shown in the drawings, and other related parts can be referred to the usual design.

[0042] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should have the usual meanings understood by those skilled in the art in the field to which this application belongs. The words indicating orientation used in the description of this application 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 means 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.

[0043] In addition, it should be noted that, unless otherwise clearly stipulated 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.

[0044] A strut assembly for opening an upper cover of an aircraft body, such as Figure 3 Shown, including:

[0045] The first support 1 is connected to the inner side of the wall of the cover 2;

[0046] A support rod 3, one end of which is hinged to the first support 1;

[0047] The bent rod 4 has one end connected to the other end of the support rod 3 and the other end is formed with a ball head. Figure 4 As shown;

[0048] The second support 5 is connected to the inner side of the wall of the cover 2;

[0049] Buckle 6, connected to the second support 5;

[0050] The lateral support 7 is connected to the inner side of the edge of the mouth frame 8 and has a vertical slide groove thereon, and the top of the vertical slide groove has a spherical opening;

[0051] When the flap 2 is closed in the flap frame 8, the support rod 3 can be clamped on the buckle 6, as shown in FIG. Figure 1 As shown;

[0052] When the cover 2 is opened from the frame 8, the support rod 3 can be disengaged from the buckle 6, and the ball head can be inserted into the vertical slide groove through the spherical opening by rotating. The ball head can slide along the vertical slide groove until it slides to the bottom of the vertical slide groove during the opening process of the cover 2, thereby limiting and maintaining the opening angle of the cover 2. Figure 2 As shown;

[0053] When the door 2 is closed in the frame 8, the ball head can slide along the vertical slot until the top of the vertical slot, and then be taken out through the spherical opening. After the door 2 is closed, the support rod 3 can be clamped to the buckle 6 by rotating.

[0054] In the support rod assembly for opening the door on the aircraft body, the first support 1 arranged inside the wall of the door 2 is designed as the rotating support of the support rod 3 and the bent rod 4, the second support 5 and the buckle 6 arranged inside the wall of the door 2 are designed as the fixed support of the support rod 3 and the bent rod 4 when the door 2 is closed in the frame 8, and the cooperation between the ball head on the bent rod 4 and the vertical slot on the lateral support 7 arranged inside the edge of the frame 8 is designed as the guide for opening the door 2 from the frame 8, and the opening angle of the door 2 can be limited and maintained. The overall structure is compact, and the operation is flexible and convenient.

[0055] In some optional embodiments of the support rod assembly for opening the door on the aircraft body, the first support 1 and the second support 5 are in the shape of a few characters, and the two side edges are connected or welded inside the wall of the door 2 by bolts.

[0056] The support rod 3 and the bent rod 4 are threadedly connected and stopped by a pin;

[0057] The lateral support 7 is in the shape of a few characters, and the two side edges are connected or welded inside the edge of the frame 8 by bolts; the vertical slot is in the shape of V, as shown in Figure 5

[0058] In some optional embodiments of the support rod assembly for opening the door on the aircraft body, the buckle 6 comprises:

[0059] A connecting base 9 is connected to the second support 5 by a pin, and two opposite vertical elastic pieces are formed on the connecting base 9, and the two vertical elastic pieces have clamping grooves and are in the shape of corrugation;

[0060] When the door 2 is closed in the frame 8, the support rod 3 can be clamped into the two vertical elastic pieces and clamped in the two clamping grooves;

[0061] When the door 2 is opened from the frame 8, the support rod 3 can be taken out of the two clamping grooves, and then the support rod 3 is taken out of the two vertical elastic pieces.

[0062] In some optional embodiments of the support rod assembly for opening the door on the aircraft body, the top of one vertical elastic piece is curled outward to form a mounting through hole;

[0063] The top of the other vertical elastic piece is bent outward to form a bayonet;

[0064] The buckle 6 further comprises:

[0065] A rectangular frame wrench 12, as shown in Figure 6 ​As shown, one side edge is installed in the installation through hole, and the opposite edge can be clamped into the two vertical elastic pieces after the support rod 3 is clamped into the two clamping grooves, and then clamped into the clamping hole by rotating, so as to limit the support rod 3 from being taken out of the two clamping grooves and the vertical elastic pieces. After the support rod 3 is taken out of the clamping hole, the support rod 3 can be taken out of the two clamping grooves and then taken out of the two vertical elastic pieces.

[0066] In some optional embodiments, the above-mentioned support rod assembly for opening the upper cover of the aircraft body further comprises:

[0067] The single-ear support 10 is connected to the first support 1 through a pin shaft;

[0068] The double-ear joint 11 is connected to the end of the support rod 3 towards the first support 1 through a threaded connection and is fixed by a pin, and is connected to the single-ear support 10 through a pin shaft. Figure 7

[0069] The embodiments in the specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the embodiments can be referred to each other. In the case of no conflict, the embodiments in the application and the technical features in the embodiments can be combined to obtain new embodiments.

[0070] So far, the technical solution of the application has been described in combination with the preferred embodiments shown in the drawings. Those skilled in the art should understand that the protection scope of the application is obviously not limited to these specific embodiments. Without deviating from the principles of the application, those skilled in the art can make equivalent changes or replacements to the related technical features. The technical solutions after the changes or replacements will fall within the protection scope of the application.​

Claims

1. A strut assembly for opening an upper cover of an aircraft fuselage, characterized in that: It comprises: a first support (1) connected to the inner side of the wall of the cover (2); a support rod (3) hinged to one end of the first support (1); a bent rod (4) connected to the other end of the support rod (3) and having a ball head at the other end; a second support (5) connected to the inner side of the wall of the cover (2); a buckle (6) connected to the second support (5); a lateral support (7) connected to the inner side of the edge of the frame (8) and having a vertical sliding groove with a spherical opening at the top; When the cover (2) is closed in the frame (8), the support rod (3) can be clamped in the buckle (6); When the cover (2) is opened from the frame (8), the support rod (3) can be disengaged from the buckle (6), and by rotating the ball head can be clamped into the vertical sliding groove through the spherical opening, and the ball head can slide along the vertical sliding groove during the opening of the cover (2) until it slides to the bottom of the vertical sliding groove, thereby limiting and maintaining the opening angle of the cover (2); When the cover (2) is closed into the frame (8), the ball head can slide along the vertical sliding groove until it slides to the top of the vertical sliding groove, and then it can be taken out through the spherical opening, and after the cover (2) is closed, the support rod (3) can be clamped into the buckle (6) by rotating.

2. The support rod assembly for opening the cover on the aircraft body according to claim 1, wherein: the first support (1) and the second support (5) are in the shape of a Chinese character, and the two side edges are connected to the inner side of the wall of the cover (2) by bolts or welding; the support rod (3) and the bent rod (4) are threadedly connected and stopped by a pin; the lateral support (7) is in the shape of a Chinese character, and the two side edges are connected to the inner side of the edge of the frame (8) by bolts or welding; and the vertical sliding groove is in the shape of a V.

3. The support rod assembly for opening the cover on the aircraft body according to claim 1, wherein: the buckle (6) comprises: a connecting base (9) connected to the second support (5) by a pin, and having two opposite vertical elastic pieces formed thereon, and the two vertical elastic pieces have clamping grooves; when the cover (2) is closed in the frame (8), the support rod (3) can be clamped into the two vertical elastic pieces and clamped in the two clamping grooves; when the cover (2) is opened from the frame (8), the support rod (3) can be taken out of the two clamping grooves, and then the support rod (3) is disengaged from the two vertical elastic pieces.

4. The support rod assembly for opening the cover on the aircraft body according to claim 3, wherein: the top of one vertical elastic piece is curled outward to form a mounting through hole; the top of the other vertical elastic piece is bent outward to form a bayonet; the buckle (6) further comprises: a rectangular frame wrench (12) having one side edge mounted in the mounting through hole and opposite edges capable of being clamped into the bayonet by rotating after the support rod (3) is clamped into the two vertical elastic pieces and clamped in the two clamping grooves, so as to limit the support rod (3) from disengaging from the two clamping grooves and the two vertical elastic pieces, and after the support rod (3) is taken out of the two clamping grooves and the two vertical elastic pieces by taking out from the bayonet, the support rod (3) can be taken out of the two clamping grooves and then disengaged from the two vertical elastic pieces.

5. The support rod assembly for opening the cover on the aircraft body according to claim 1, further comprising: a single ear support (10) connected to the first support (1) by a pin shaft. ​ The double ear joint (11) is connected to the single ear joint (10) by a pin shaft connection, and is connected to the strut (3) by a threaded connection at the end of the strut (3) facing the first support (1).

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