A connecting structure of a short wing externally hung on a helicopter

Abstract

The present application relates to a kind of connecting structure of short wing of helicopter external hanging, belong to helicopter technical field, solve the installation and disassembly process complex, time-consuming and labor-consuming of short wing of helicopter external hanging in prior art.The present application includes: butt joint lock hook assembly and locking pin;The butt joint lock hook assembly includes: butt joint lock hook and butt joint connector;The butt joint lock hook and butt joint connector are fixedly installed in external hanging short wing and machine body respectively;After the butt joint lock hook and butt joint connector butt joint, lock by locking pin.The present application realizes the quick installation to external hanging short wing by the quick butt joint and locking of butt joint lock hook assembly, simultaneously, external hanging short wing can be quickly disassembled by pulling out locking pin, save manpower and material resources.

Description

Technical Field

[0001] This invention relates to the field of helicopter technology, and more particularly to a connection structure for external stub wings of helicopters. Background Technology

[0002] The stub wings of commonly used unmanned helicopters are fixed to the fuselage with bolts. To ensure installation reliability, multiple bolts are required for fastening, which takes a long time to install and disassemble and is inconvenient for helicopter maintenance.

[0003] In addition, the short wings that are fixedly connected to the fuselage increase the effective width of the unmanned helicopter. During the vehicle-mounted transport of the unmanned helicopter, a large space is required to place the unmanned helicopter, which creates an economic burden and makes it inconvenient to park the helicopter statically.

[0004] Therefore, a new short-wing connection method is needed to achieve rapid connection and disassembly, shorten operation time, facilitate disassembly during transportation, reduce transportation space requirements, and lower costs. Summary of the Invention

[0005] Based on the above analysis, the present invention aims to provide a connection structure for helicopter external stub wings to solve the problems of complex, time-consuming and labor-intensive installation and disassembly processes in existing helicopter external stub wing connection methods.

[0006] The objective of this invention is mainly achieved through the following technical solutions:

[0007] A connection structure for a helicopter external stub wing includes: a docking hook assembly and a locking pin; the docking hook assembly includes: a docking hook and a docking connector; the docking hook and the docking connector are respectively fixedly installed on the external stub wing and the fuselage; after the docking hook and the docking connector are docked, they are locked by the locking pin.

[0008] Furthermore, the docking hook includes: a first docking hook and a second docking hook; the first docking hook and the second docking hook are rotatably connected.

[0009] Furthermore, the mating joint is provided with a first locking groove, a second locking groove, and a third locking groove.

[0010] Furthermore, the first locking groove, the second locking groove, and the third locking groove are all U-shaped grooves.

[0011] Furthermore, the first locking groove and the second locking groove are perpendicular to each other; the third locking groove is parallel to the first locking groove.

[0012] Furthermore, the first docking hook is equipped with a first docking pin and a second docking pin; the first docking pin can be engaged in the first locking groove; the second docking pin can be engaged in the second locking groove.

[0013] Furthermore, a third docking pin is installed on the second docking hook; the third docking pin can be engaged in the third locking groove.

[0014] Furthermore, a locking plate is provided above the docking joint; the locking plate is provided with a first insertion hole; and the second docking hook is provided with a second insertion hole.

[0015] Furthermore, when the third docking pin is engaged in the third locking groove, the second docking hook covers the outside of the locking piece and the first and second insertion holes overlap.

[0016] Furthermore, the locking pin is installed in the first socket and the second socket.

[0017] The technical solution of this invention can achieve at least one of the following effects:

[0018] 1. This invention provides a rotating docking connection structure for the external stub wing of a large unmanned helicopter, enabling rapid installation and removal of the external stub wing; the installation and removal of the external stub wing is convenient, facilitating the maintenance of the unmanned helicopter, and saving space for the transportation of the unmanned helicopter.

[0019] 2. In the connecting structure of the helicopter external stub wing of the present invention, the docking hook and the docking joint will not undergo relative displacement after docking. Furthermore, the docking hook and the docking joint are connected and fixed by a locking pin, which ensures the reliability and stability of the external stub wing when carrying a load.

[0020] In this invention, the above-described technical solutions can be combined with each other to achieve more preferred combinations. Other features and advantages of this invention will be set forth in the following description, and some advantages may become apparent from the description or be learned by practicing the invention. The objects and other advantages of this invention can be realized and obtained from what is particularly pointed out in the description and drawings. Attached Figure Description

[0021] The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. Throughout the drawings, the same reference numerals denote the same parts.

[0022] Figure 1 This invention relates to the connection structure for helicopter external stub wings;

[0023] Figure 2 This is the first docking hook of the connecting structure for the helicopter external stub wing of the present invention;

[0024] Figure 3 The docking joint is the connection structure of the helicopter external stub wing of the present invention;

[0025] Figure 4 This is the second docking hook of the connecting structure for the helicopter external stub wing of the present invention;

[0026] Figure 5 The docking hook assembly of the connecting structure of the helicopter external stub wing of the present invention is in the separated state;

[0027] Figure 6 This is the first-stage docking state of the docking lock hook assembly of the connecting structure of the helicopter external stub wing of the present invention;

[0028] Figure 7 This is the secondary docking state of the docking hook assembly of the connecting structure of the helicopter external stub wing of the present invention;

[0029] Figure 8 This is the three-stage docking state of the docking lock hook assembly of the connecting structure of the helicopter external stub wing of the present invention;

[0030] Figure 9 This refers to the limiting state of the locking pin in this invention;

[0031] Figure 10 This is the released state of the locking pin of the present invention.

[0032] Figure label:

[0033] 1-First docking hook; 2-Dock joint; 3-Second docking hook; 4-External stub wing; 5-Fuselage; 6-Locking pin; 7-First docking pin; 8-Hinge shaft; 9-Second docking pin; 10-Third docking pin;

[0034] 11-First superior branch auricle; 12-First inferior branch auricle;

[0035] 21-Second superior branch auricle; 22-Second inferior branch auricle;

[0036] 101-First pin mounting hole; 102-Second pin mounting hole; 103-First hinge hole; 104-Locking hook base;

[0037] 201-First locking groove; 202-Second locking groove; 203-Third locking groove; 204-Locking piece; 205-First insertion hole;

[0038] 301 - Second hinge hole; 302 - Third pin mounting hole; 303 - Second insertion hole; 304 - Fixing block; 305 - Limiting cover; 306 - Spring;

[0039] 601 - Pin cap; 602 - First rod section; 603 - Second rod section. Detailed Implementation

[0040] The preferred embodiments of the present invention will now be described in detail with reference to the accompanying drawings, which constitute a part of the present invention and are used together with the embodiments of the present invention to illustrate the principles of the present invention, but are not intended to limit the scope of the present invention.

[0041] Example 1

[0042] One specific embodiment of the present invention discloses a connection structure for a helicopter external stub wing, such as... Figure 1-4 As shown, it includes: a docking lock hook assembly and a locking pin 6; the docking lock hook assembly includes: a docking lock hook and a docking connector 2; the docking lock hook and the docking connector 2 are respectively fixedly installed on the external stub wing 4 and the fuselage 5; after the docking lock hook and the docking connector 2 are docked, they are locked by the locking pin 6.

[0043] Specifically, such as Figure 1 As shown, the first docking hook 1 is fixedly installed on the side of the fuselage 5, and the docking joint 2 is fixedly installed on the side of the external stub wing 4.

[0044] Furthermore, such as Figure 1 As shown, the external stub wing 4 and the fuselage 5 are connected by two or more sets of docking hook assemblies.

[0045] Specifically, when using two or more sets of docking hook assemblies to connect the fuselage 5 and the external stub wing 4, the two or more sets of docking hook assemblies are arranged side by side, and the docking hooks and docking joints 2 of the two or more sets of docking hook assemblies can dock simultaneously. After docking, the docking hook assemblies are locked by the locking pin 6.

[0046] In this embodiment, after two or more sets of docking hook assemblies are docked, the docking hook and docking connector 2 can be connected, and the connection between the external stub wing 4 and the fuselage 5 can be achieved simultaneously. Furthermore, a locking pin 6 is installed between the docking hook and the docking connector 2 to lock the docking hook assembly, achieving a two-stage connection fixation and ensuring the stability of the connection between the external stub wing 4 and the fuselage 5.

[0047] In one specific embodiment of the present invention, such as Figure 1 As shown, the docking hook includes: a first docking hook 1 and a second docking hook 3; the first docking hook 1 and the second docking hook 3 are rotatably connected.

[0048] Furthermore, such as Figure 2 As shown, the first docking hook 1 is provided with a first hinge hole 103; as Figure 4 As shown, the second docking hook 3 is provided with a second hinge hole 301. Figure 5 As shown, a hinge shaft 8 is installed in the first hinge hole 103 and the second hinge hole 301, and the second docking hook 3 is hinged above the first docking hook 1 via the hinge shaft 8.

[0049] In one specific embodiment of the present invention, the structure of the first docking hook 1 is as follows: Figure 2 As shown.

[0050] Specifically, the first docking hook 1 consists of a hook base 104 and a double-ear structure; and the hook base 104 and the double-ear structure are an integral structure. The hook base 104 is fixedly connected to the machine body 5 by welding or bolts.

[0051] like Figure 2 As shown, the lock hook base 104 is provided with two support ears, specifically: a first upper support ear 11 and a first lower support ear 12.

[0052] like Figure 2 As shown, the first lower support ear 12 is provided with a first pin mounting groove, and the first pin mounting groove is provided with first pin mounting holes 101 on both sides; the first pin mounting holes 101 are used to install the first mating pin 7, and the first mating pin 7 is fixedly installed in the first pin mounting holes 101.

[0053] like Figure 2 As shown, the first upper support ear 11 is provided with a first hinge hole 103 and a second pin mounting groove; wherein, the first hinge hole 103 is used for hinged installation of the second docking hook 3; the second pin mounting groove is provided with second pin mounting holes 102 on both sides, the second pin mounting holes 102 are used for installing the second docking pin 9, and the second docking pin 9 is fixedly installed in the second pin mounting holes 102.

[0054] In one specific embodiment of the present invention, the mating joint 2 is as follows: Figure 3 As shown.

[0055] Specifically, the docking joint 2 is fixedly connected to the external short wing 4 or is an integral structure. The docking joint 2 includes: a second upper support ear 21 and a second lower support ear 22.

[0056] like Figure 3 As shown, the bottom of the second lower support ear 22 is provided with a first locking groove 201, which is used to cooperate with the first docking pin 7; when the first docking hook 1 is docked with the docking connector 2, the first docking pin 7 is engaged in the first locking groove 201, as shown. Figure 5 As shown.

[0057] like Figure 3 As shown, the side of the second upper support ear 21 is provided with a second locking groove 202, which is used to engage with the second docking pin 9 on the first docking hook 1; when the first docking hook 1 engages with the docking connector 2, the second docking pin 9 is engaged in the second locking groove 202, as shown. Figure 6 As shown.

[0058] like Figure 3As shown, a locking plate 204 is provided above the second upper support ear 21, and a first insertion hole 205 is provided on the locking plate 204. The first insertion hole 205 is used to cooperate with the second insertion hole 303 on the second docking hook 3; as shown Figure 8 As shown, after the second docking hook 3 is docked with the docking connector 2, the first insertion hole 205 and the second insertion hole 303 are aligned. The locking pin 6 is inserted into the first insertion hole 205 and the second insertion hole 303, which can lock the second docking hook 3 and the docking connector 2. Figure 8 As shown.

[0059] In one specific embodiment of the present invention, such as Figure 3 As shown, the first locking groove 201, the second locking groove 202, and the third locking groove 203 are all U-shaped grooves. Alternatively, the first locking groove 201, the second locking groove 202, and the third locking groove 203 are all semi-circular grooves.

[0060] Furthermore, such as Figure 3 As shown, the first locking groove 201 and the second locking groove 202 are perpendicular to each other; the third locking groove 203 is parallel to the first locking groove 201.

[0061] In one specific embodiment of the present invention, the second docking hook 3 is as follows: Figure 4 As shown.

[0062] Specifically, the second docking hook 3 is a slot structure with a groove.

[0063] The second docking hook 3 has a first groove at one end, a second groove at the other end, and a third groove in the middle.

[0064] The first groove has second hinge holes 301 on both sides for mounting. The second groove has third pin mounting holes 302 on both sides for mounting. The third pin mounting holes 302 are fixedly installed in the third pin mounting holes 302. The third groove can cooperate with the locking piece 204. The third groove has second insertion holes 303 on both sides. When the second insertion holes 303 are aligned with the first insertion hole 205, they are used to install the locking pin 6.

[0065] When implementing, such as Figure 5-8 As shown:

[0066] like Figure 5 As shown, when the fuselage 5 and the external stub wing 4 are separated: the first docking hook 1 is equipped with a first docking pin 7 and a second docking pin 9; the second docking hook 3 is equipped with a third docking pin 10. The docking joint 2 is provided with a first locking groove 201, a second locking groove 202 and a third locking groove 203. A locking plate 204 is provided above the docking joint 2; the locking plate 204 is provided with a first insertion hole 205; the second docking hook 3 is provided with a second insertion hole 303.

[0067] like Figure 6 As shown, the first connecting pin 7 is connected to the first locking groove 201. When the first connecting pin 7 is inserted into the first locking groove 201, the inner wall of the first pin mounting groove of the first lower support ear 12 is in contact with the outer side of the second lower support ear 22.

[0068] like Figure 7 As shown, the second docking pin 9 docks with the second locking groove 202; when the second docking pin 9 is inserted into the second locking groove 202, the inner wall of the second pin mounting groove of the first upper support ear 11 is in contact with the outer side of the second upper support ear 21 of the docking joint 2.

[0069] like Figure 8 As shown, when the third docking pin 10 mates with the third locking groove 203, the second docking hook 3 is rotated to make the third docking pin 10 engage in the third locking groove 203. At this time, the second docking hook 3 covers the outside of the locking piece 204, and the first insertion hole 205 and the second insertion hole 303 coincide; the locking pin 6 can be inserted into the first insertion hole 205 and the second insertion hole 303.

[0070] like Figure 1 As shown, the locking pin 6 is inserted into the first docking hook 1 and the second docking hook 3, and the docking hook assembly is completed. The first docking hook 1 is fixed to the fuselage 5 by riveting or screwing, and the docking joint 2 is riveted to one end of the leading edge of the external stub wing 4. The docking joint 2 and the external stub wing 4 are designed as a single unit. After the docking of multiple sets of docking hook assemblies is completed, the external stub wing 4 and the fuselage 5 are connected.

[0071] All parts of the connecting structure for the helicopter external stub wing of the present invention are made of 7075-T6 aviation aluminum alloy. While ensuring strength and rigidity, the force transmission path is short, and a weight reduction design has been carried out according to the force transmission situation to save the weight of the connecting structure.

[0072] Example 2

[0073] One specific embodiment of the present invention is an improvement on embodiment 1.

[0074] To prevent the locking pin 6 from detaching from the first docking hook 1 and the second docking hook 3, in this embodiment, the locking pin 6 is configured as a bendable structure, and a limiting component is provided on the side of the second docking hook 3, such as... Figure 9 , Figure 10 As shown.

[0075] Specifically, the locking pin 6 includes: a pin cap 601, a first rod portion 602, and a second rod portion 603; wherein, the pin cap 601 is fixedly connected to the first rod portion 602, and the length of the pin cap 601 is greater than the diameter of the first rod portion 602; the second rod portion 603 is hinged to the first rod portion 602, and both the first rod portion 602 and the second rod portion 603 can pass through the first insertion hole 205 and the second insertion hole 303.

[0076] Specifically, the side of the second docking hook 3 is provided with a pin placement groove for placing the second rod portion 603; such as Figure 9 As shown, after the locking pin 6 passes through the second docking hook 3, the second rod part 603 is rotated to place it in the pin placement groove.

[0077] Specifically, the limiting component includes: a fixing block 304, a limiting cover 305, and a spring 306.

[0078] like Figure 9 As shown, the fixing block 304 is fixedly installed on the side of the second docking hook 3 by welding or bonding, the limiting cover 305 is covered on the outside of the fixing block 304, and the limiting cover 305 and the fixing block 304 are connected by a spring 306.

[0079] Furthermore, when the second rod portion 603 is bent upward and placed in the pin placement groove, the limiting cover 305 moves downward under the elastic force of the spring 306, thereby limiting the second rod portion 603 through the limiting cover 305, so that the second rod portion 603 cannot rotate relative to the first rod portion 602, and preventing the locking pin 6 from falling off.

[0080] like Figure 10 As shown, pull the limiting cover 305 upward to compress the spring 306. The limiting cover 305 moves upward, and the pin placement groove is fully exposed. At this time, the second rod part 603 can be pressed into the pin placement groove, or the second rod part 603 can be taken out from the pin placement groove.

[0081] In this embodiment, the installation process of the locking pin 6 is as follows:

[0082] Rotate the second rod 603 to make it coaxial with the first rod 602, and insert the locking pin 6 into the first insertion hole 205 and the second insertion hole 303; the second rod 603 protrudes from the other side of the second docking hook 3, pull the limiting cover 305 upward to expose the pin placement groove, rotate the second rod 603 to bend it upward and place it in the pin placement groove, release the limiting cover 305, and the limiting cover 305 moves downward under the elastic force of the spring 306, restricting the rotation of the second rod 603 and preventing the locking pin 6 from falling off. At this time, the locking pin 6 cannot be displaced relative to the second docking hook 3, and the second docking hook 3 is fixed to the locking piece 204 as one piece, such as Figure 9 As shown.

[0083] like Figure 10As shown, the process of pulling out the locking pin 6 is as follows:

[0084] Pull the limiting cover 305 upwards to expose the pin placement slot. Rotate the second rod 603 to remove it from the pin placement slot, and make the second rod 603 coaxial with the first rod 602 (the second rod 603 and the first rod 602 are on the same straight line). Pull the locking pin 6 outwards to remove the locking pin 6 from the second docking hook 3 and the locking piece 204. At this time, the second docking hook 3 and the first docking hook 1 can rotate relative to each other, thereby separating the docking hook from the docking joint 2.

[0085] In this embodiment, the locking pin 6 and the second docking hook 3 are integrated by limiting the second rod portion 603 through the limiting cover 305; thereby ensuring the connection stability of the docking hook assembly. The compression spring 306 pulls the limiting cover 305 upwards, releasing the limiting cover 305 from the second rod portion 603. At this point, the locking pin 6 can be pulled out, and the second docking hook 3 can be unscrewed from the third locking groove 203, thus achieving the disassembly of the external stub wing 4.

[0086] In this embodiment, multi-level limiting ensures the reliability of the connection between the fuselage 5 and the external stub wing 4. Specifically, after the docking joint 2 and the docking hook are docked, they cannot move relative to each other, achieving the first-level limiting; further, locking pins 6 are inserted into the first docking hook 1 and the second docking hook 3 to lock them, achieving the second-level limiting; further, a limiting component is set on the outside of the second docking hook 3 to prevent the locking pin 6 from slipping out, thereby avoiding relative rotation between the first docking hook 1 and the second docking hook 3, further ensuring the reliability of the connection, achieving the third-level limiting.

[0087] In this invention, when connecting and disassembling the external stub wing of a helicopter using the connection structure of Embodiment 1 or Embodiment 2, the connection between the external stub wing 4 and the fuselage 5 can be achieved through the mutual docking and locking of the locking hook docking structure.

[0088] Compared with the prior art, the technical solution provided by the present invention has at least one of the following beneficial effects:

[0089] 1. When using the helicopter external stub wing connection structure of the present invention, based on actual operation evaluation, it takes only about 80 seconds to quickly install a single external stub wing 4 on the fuselage 5, and only about 40 seconds to quickly remove it.

[0090] 2. The connection structure of the present invention is lightweight, compact, easy to install and disassemble, convenient to operate, and highly reliable. During the ground transportation of the unmanned helicopter, the external stub wing 4 can be removed at any time, effectively saving the space occupied by the unmanned helicopter during vehicle transportation, facilitating transportation and saving costs.

[0091] 3. The connecting structure of the helicopter external stub wing of the present invention, through the mutual docking of three sets of docking pins and locking grooves, realizes the restriction of six degrees of freedom between the first docking hook 1 and the docking joint 2, and ensures the fixation of their relative positions.

[0092] 4. The connecting structure of the helicopter external stub wing of the present invention does not require screw fixing throughout the entire process. When installing or removing the external stub wing, the process of repeatedly tightening or unscrewing screws is omitted, making the operation simple, time-saving, and labor-saving, and saving manpower in the installation or removal process.

[0093] The above description is only a preferred embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention.

Claims

1. A connection structure for a helicopter external stub wing, characterized in that, include: The docking lock hook assembly includes a docking lock hook and a docking connector (2); the docking lock hook and the docking connector (2) are respectively fixedly installed on the external stub wing (4) and the fuselage (5); after the docking lock hook and the docking connector (2) are docked, they are locked by the locking connector (6); The docking hook includes: a first docking hook (1) and a second docking hook (3); the first docking hook (1) and the second docking hook (3) are rotatably connected; The mating joint (2) is provided with a first locking groove (201), a second locking groove (202) and a third locking groove (203); The first docking hook (1) is equipped with a first docking pin (7) and a second docking pin (9); the first docking pin (7) can be engaged in the first locking groove (201); the second docking pin (9) can be engaged in the second locking groove (202); The second docking hook (3) is equipped with a third docking pin (10); the third docking pin (10) can be engaged in the third locking groove (203); A locking plate (204) is provided above the docking joint (2); a first insertion hole (205) is provided on the locking plate (204); a second insertion hole (303) is provided on the second docking hook (3).

2. The connection structure for a helicopter external stub wing according to claim 1, characterized in that, The first locking groove (201), the second locking groove (202) and the third locking groove (203) are all U-shaped grooves.

3. The connection structure for a helicopter external stub wing according to claim 1 or 2, characterized in that, The first locking groove (201) and the second locking groove (202) are perpendicular to each other; the third locking groove (203) is parallel to the first locking groove (201).

4. The connection structure for a helicopter external stub wing according to claim 1, characterized in that, When the third docking pin (10) is engaged in the third locking groove (203), the second docking hook (3) covers the outside of the locking piece (204) and the first insertion hole (205) and the second insertion hole (303) overlap.

5. The connection structure for a helicopter external stub wing according to claim 4, characterized in that, The locking pin (6) is installed in the first socket (205) and the second socket (303).

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