A helicopter with docking type externally mounted short wings and a method of connecting them

Abstract

The present application relates to a kind of short wing with docking external hanging of helicopter and its connecting method, belong to helicopter technical field, solve the installation and removal process complex of short wing of external hanging of helicopter in prior art, time-consuming and labor-consuming problem.The present application includes: fuselage, external hanging short wing and docking lock hook component;The external hanging short wing is fixedly connected with fuselage by docking lock hook component;The docking lock hook component includes: docking lock hook, docking joint and locking pin;The docking lock hook and docking joint are fixedly installed on external hanging short wing and fuselage respectively;After the docking of the docking lock hook and docking joint, locking is carried out by locking pin;External hanging short wing is installed on fuselage.The present application is quickly docked and locked by docking lock hook component, the quick installation of external hanging short wing is realized, and external hanging short wing can be quickly disassembled by pulling out locking pin, and storage and transfer are facilitated.

Description

Technical Field

[0001] This invention relates to the field of helicopter technology, and more particularly to a helicopter with docking-type external stub wings and its connection method. 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 helicopter with docking-type external stub wings and its connection method, so as to solve the problems of complex, time-consuming and labor-intensive installation and disassembly processes of existing helicopter external stub wing connection methods.

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

[0007] A helicopter with a docking-type external stub wing includes: a fuselage, an external stub wing, and a docking hook assembly; the external stub wing and the fuselage are connected by one or more sets of docking hook assemblies; the docking hook assembly includes: a docking hook, a docking connector, and a locking pin; 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. Further, 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. The docking connector is provided with a first locking groove, a second locking groove, and a third locking groove.

[0008] Furthermore, the first locking groove, the second locking groove, and the third locking groove are all U-shaped grooves.

[0009] 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.

[0010] 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.

[0011] Furthermore, a third docking pin is installed on the second docking hook; the third docking pin can be engaged in the third locking groove.

[0012] In this invention, the locking pin can be inserted into the second docking hook and the docking joint simultaneously to lock the second docking hook and the docking joint.

[0013] 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.

[0014] 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; the locking pin is installed in the first and second insertion holes.

[0015] A method for connecting external stub wings to a helicopter, wherein the helicopter is a helicopter with docking-type external stub wings as described above, the connection method comprising:

[0016] Step S1: Install the docking hook and docking connector onto the fuselage and external stub wings respectively;

[0017] Step S2: Connect the locking hook and the docking joint;

[0018] Step S3: Lock the second docking hook and docking joint after docking by locking the locking pin; complete the installation of the external stub wing on the fuselage.

[0019] Furthermore, in step S1: the docking hook includes: a first docking hook and a second docking hook; the first docking hook is fixedly installed on the side of the fuselage, and the docking joint is fixedly installed on the side of the external stub wing.

[0020] Furthermore, step S2 includes a first-level docking: inserting the first docking pin on the first docking hook into the first locking groove on the docking joint.

[0021] Furthermore, step S2 also includes a secondary docking: rotating the external short wing causes the docking joint to rotate relative to the first docking lock hook, thereby causing the second docking pin to engage in the second locking groove on the docking joint.

[0022] Furthermore, step S2 also includes three-stage docking: rotating the second docking hook so that the third docking pin engages in the third locking groove on the docking joint.

[0023] Furthermore, in step S3, the mating joint is provided with a first insertion hole, and the second mating hook is provided with a second insertion hole; the locking pin is inserted into the first insertion hole and the second insertion hole.

[0024] Furthermore, when disassembling the external stub wing, it is only necessary to remove the locking pin and separate the docking hook and docking joint of the docking hook assembly; specifically, the separation process of the docking hook assembly is the reverse of the docking process of the docking hook assembly in step S2.

[0025] The technical solution of this invention can achieve at least one of the following effects:

[0026] 1. The external stub wing of the helicopter of the present invention is connected to the fuselage by a rotating docking hook assembly, which realizes the quick installation and removal of the external stub wing; the installation and removal of the external stub wing is convenient, which facilitates the maintenance of the unmanned helicopter and saves space for the transportation of the unmanned helicopter.

[0027] 2. In the helicopter with docking-type external stub wings of the present invention, the docking hook and the docking joint of the docking hook assembly will not undergo relative displacement after docking. Furthermore, the docking hook and the docking joint are connected and fixed by a locking pin, ensuring the reliability and stability of the external stub wings when carrying loads.

[0028] 3. The method for connecting external stub wings of a helicopter according to the present invention involves connecting and assembling the external stub wing and the fuselage together through a docking hook assembly. The docking hook assembly achieves docking and fixation of relative position through a three-stage docking method, thereby enabling rapid installation of the external stub wing and ensuring that the external stub wing and the fuselage will not shift relative to each other after installation, thus preventing the stub wing from wobbling.

[0029] 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

[0030] 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.

[0031] Figure 1 The present invention relates to a helicopter with docking-type external stub wings;

[0032] Figure 2 The first docking hook of the docking hook assembly for a helicopter with docking-type external stub wings according to the present invention;

[0033] Figure 3 The present invention relates to a docking joint for a docking hook assembly of a helicopter with a docking-type external stub wing.

[0034] Figure 4The second docking hook of the docking hook assembly for a helicopter with docking-type external stub wings according to the present invention;

[0035] Figure 5 This is the separated state of the docking hook assembly of the helicopter with docking-type external stub wings according to the present invention;

[0036] Figure 6 This is the first-stage docking state of the docking hook assembly of the helicopter with docking-type external stub wings according to the present invention;

[0037] Figure 7 This is the second-stage docking state of the docking hook assembly of the helicopter with docking-type external stub wings according to the present invention;

[0038] Figure 8 This is the three-stage docking state of the docking hook assembly for a helicopter with docking-type external stub wings according to the present invention;

[0039] Figure 9 This refers to the limiting state of the locking pin in this invention;

[0040] Figure 10 This indicates the release state of the locking pin in this invention.

[0041] Figure label:

[0042] 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;

[0043] 11-First superior branch auricle; 12-First inferior branch auricle;

[0044] 21-Second superior branch auricle; 22-Second inferior branch auricle;

[0045] 101-First pin mounting hole; 102-Second pin mounting hole; 103-First hinge hole; 104-Locking hook base;

[0046] 201-First locking groove; 202-Second locking groove; 203-Third locking groove; 204-Locking piece; 205-First insertion hole;

[0047] 301 - Second hinge hole; 302 - Third pin mounting hole; 303 - Second insertion hole; 304 - Fixing block; 305 - Limiting cover; 306 - Spring;

[0048] 601 - Pin cap; 602 - First rod section; 603 - Second rod section. Detailed Implementation

[0049] 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.

[0050] Example 1

[0051] One specific embodiment of the present invention discloses a helicopter with docking-type external stub wings, such as... Figure 1-4 As shown, it includes: external stub wings 4, fuselage 5, and docking hook assembly.

[0052] like Figure 1 As shown, the docking lock assembly includes: a docking lock hook, a docking connector 2, and a locking pin 6; the docking lock hook and the docking connector 2 are respectively fixedly installed on the external stub wing 4 and the fuselage 5; specifically, as shown... Figure 1 As shown, the first docking hook 1 is fixedly installed on the side of the fuselage 5, and the docking connector 2 is fixedly installed on the side of the external stub wing 4. After the docking hook and the docking connector 2 are docked, they are locked by the locking pin 6.

[0053] 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.

[0054] 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.

[0055] 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.

[0056] 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.

[0057] 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 5As 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.

[0058] In one specific embodiment of the present invention, the first docking hook 1 is as follows: Figure 2 As shown.

[0059] 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.

[0060] 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.

[0061] 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.

[0062] 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.

[0063] In one specific embodiment of the present invention, the mating joint 2 is as follows: Figure 3 As shown.

[0064] 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.

[0065] 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.

[0066] like Figure 3As 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.

[0067] like Figure 3 As 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.

[0068] 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.

[0069] 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.

[0070] In one specific embodiment of the present invention, the second docking hook 3 is as follows: Figure 4 As shown.

[0071] Specifically, the second docking hook 3 is a slot structure with a groove.

[0072] 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.

[0073] 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.

[0074] When implementing, such as Figure 5-8 As shown:

[0075] like Figure 5As 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.

[0076] 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.

[0077] 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.

[0078] 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.

[0079] 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.

[0080] All parts of the helicopter with docking-type external stub wings of the present invention are made of 7075-T6 aviation aluminum alloy. While ensuring strength and rigidity, the force transmission path is short, and the weight reduction design is carried out according to the force transmission situation, saving the weight of the connecting structure.

[0081] Example 2

[0082] One specific embodiment of the present invention is an improvement on embodiment 1.

[0083] 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.

[0084] 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.

[0085] 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.

[0086] Specifically, the limiting component includes: a fixing block 304, a limiting cover 305, and a spring 306.

[0087] 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.

[0088] 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.

[0089] 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.

[0090] 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.

[0091] 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.

[0092] Example 3

[0093] In one specific embodiment of the present invention, a method for connecting external stub wings of a helicopter is provided, wherein the external stub wings are connected and disassembled using a helicopter with docking-type external stub wings as described in Embodiment 1 or Embodiment 2.

[0094] In this embodiment, the installation method of the external stub wing 4 is as follows: Figures 5-8 As shown.

[0095] The connection method includes:

[0096] Step S1: Install the docking hook and docking connector 2 onto the fuselage 5 and the external stub wing 4 respectively;

[0097] Step S2: Connect the locking hook and the docking connector 2 together;

[0098] Step S3: Lock the second docking hook 3 and docking joint 2 after docking by locking pin 6; complete the installation of the external stub wing 4 on the fuselage 5.

[0099] In step S1: the docking hooks include: a first docking hook 1 and a second docking hook 3; the first docking hook 1 is fixedly installed on the side of the fuselage 5, and the docking connector 2 is fixedly installed on the side of the external stub wing 4.

[0100] Step S2 includes:

[0101] Step S21:

[0102] First-level docking: Insert the first docking pin 7 on the first docking hook 1 into the first locking groove 201 on the docking joint 2.

[0103] Specifically, such as Figure 6 As shown, when the first connecting pin 7 is engaged in 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.

[0104] Step S22:

[0105] Secondary docking: Rotate the external short wing 4 to make the docking joint 2 rotate relative to the first docking hook 1, thereby causing the second docking pin 9 to engage in the second locking groove 202 on the docking joint 2.

[0106] Specifically, such as Figure 7 As shown, during the process of the second docking pin 9 being engaged with the docking joint 2, the first docking locking hook 1 rotates around the axis of the first docking pin 7, while the first docking pin 7 rotates in the first locking groove 201. When the second docking pin 9 is engaged with 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 surface of the second upper support ear 21 of the docking joint 2.

[0107] Step S23:

[0108] Three-stage docking: Rotate the second docking hook 3 to make the third docking pin 10 engage in the third locking groove 203 on the docking joint 2.

[0109] Specifically, such as Figure 8 As shown, in step S23, the second docking hook 3 rotates clockwise relative to the first docking hook 1 around the hinge shaft 8, thereby engaging the third docking pin 10 into the third locking groove 203. At this time, the second docking hook 3 covers the outside of the locking plate 204. The locking plate 204 of the docking joint 2 is provided with a first insertion hole 205, and the second docking hook 3 is provided with a second insertion hole 303, with the first insertion hole 205 and the second insertion hole 303 coinciding; the locking pin 6 can be inserted into the first insertion hole 205 and the second insertion hole 303. This invention achieves the restriction of 6 degrees of freedom between the first docking hook 1 and the docking joint 2 through the mutual docking of three sets of docking pins and locking grooves. After the docking of the docking hook and the docking joint 2 is completed, the relative position of the docking hook and the docking joint 2 is fixed, restricting the relative displacement and relative rotation between the external stub wing 4 and the fuselage 5.

[0110] In step S3, the locking pin 6 is inserted into the first insertion hole 205 and the second insertion hole 303 to achieve the combined fixation of the docking joint 2 and the docking lock hook. In this invention, by inserting the locking pin 6 into the second docking lock hook 3 and the locking piece 204, the connection reliability of the docking lock hook and the docking joint 2 is ensured, thereby ensuring the installation reliability of the external stub wing 4 and the fuselage 5.

[0111] Further, in step S4: when disassembling the external stub wing 4, it is only necessary to pull out the locking pin 6 and separate the docking hook and docking joint 2 of the docking hook assembly; specifically, the separation process of the docking hook assembly is the reverse of the docking process of the docking hook assembly in step S2.

[0112] Furthermore, when using the connection structure of Embodiment 2, specifically:

[0113] 1) When assembling the external stub wing 4, the installation process of the locking pin 6 in step S3 is as follows:

[0114] Step S31: 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;

[0115] Step S32: The second rod 603 extends out from the other side of the second docking hook 3, pulls the limiting cover 305 upward to expose the pin placement groove, rotates the second rod 603 to bend it upward and place it in the pin placement groove;

[0116] Step S33: Release the limiting cover 305. Under the elastic force of the spring 306, the limiting cover 305 moves downward, restricting the rotation of the second rod 603 and preventing the locking pin 6 from falling off.

[0117] 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 a whole. Figure 9 As shown.

[0118] 2) When disassembling the external short wing 4, the process of pulling out the locking pin 6 is as follows:

[0119] Step S41: Pull the limit cover 305 upward to expose the pin placement slot;

[0120] Step S42: 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).

[0121] Step S43: Pull the locking pin 6 outward to remove it 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.

[0122] Furthermore, the separation process of the docking hook and the docking joint 2 is the reverse of the docking process in step S2.

[0123] Compared with the prior art, the technical solution provided by the present invention has at least one of the following beneficial effects:

[0124] 1. The helicopter external stub wing connection method of the present invention, combined with actual operation evaluation, shows that 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.

[0125] 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.

[0126] 3. The method for connecting helicopter external stub wings of the present invention does not require screw fixing throughout the entire process. When installing or removing the external stub wings, 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.

[0127] 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 helicopter with docking-type external stub wings, characterized in that, include: The fuselage (5), external stub wings (4), and docking hook assembly; The external stub wing (4) and the fuselage (5) are connected by one or more sets of docking hook assemblies; the docking hook assembly includes: docking hook, docking connector (2) and locking pin (6); the docking hook and docking connector (2) are respectively fixedly installed on the external stub wing (4) and the fuselage (5); after the docking hook and docking connector (2) are docked, they are locked by locking pin (6); The docking hooks include: 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 docking 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).

2. The helicopter with docking-type external stub wings according to claim 1, characterized in that, The locking pin (6) can be inserted into the second docking hook (3) and the docking joint (2) at the same time to lock the second docking hook (3) and the docking joint (2); The locking pin (6) is a bendable structure. The side of the second docking hook (3) is provided with a limiting component. The limiting component includes a fixing block (304), a limiting cover (305) and a spring (306). The fixing block (304) is fixedly installed on the side of the second docking hook (3). The limiting cover (305) covers the outside of the fixing block (304). The limiting cover (305) and the fixing block (304) are connected by the spring (306). The bending part of the locking pin (6) is limited by the limiting cover (305).

3. A method for connecting external stub wings to a helicopter, characterized in that, The helicopter is the helicopter with docking-type external stub wings as described in any one of claims 1-2, and the connection method includes: Step S1: Install the docking hook and docking connector (2) onto the fuselage (5) and the external stub wing (4) respectively; Step S2: Connect the locking hook and the docking connector (2) together; Step S3: Lock the second docking hook (3) and docking joint (2) after docking by locking pin (6) to complete the installation of the external stub wing (4) on the fuselage (5).

4. The method for connecting external stub wings of a helicopter according to claim 3, characterized in that, In step S1: the docking hook includes: a first docking hook (1) and a second docking hook (3); the first docking hook (1) is fixedly installed on the side of the fuselage (5), and the docking connector (2) is fixedly installed on the side of the external stub wing (4).

5. The method for connecting external stub wings of a helicopter according to claim 3, characterized in that, Step S2 includes a first-level docking: inserting the first docking pin (7) on the first docking hook (1) into the first locking groove (201) on the docking joint (2).

6. The method for connecting external stub wings of a helicopter according to claim 5, characterized in that, Step S2 further includes a secondary docking: rotating the external short wing (4) to make the docking joint (2) rotate relative to the first docking hook (1), thereby causing the second docking pin (9) to be engaged in the second locking groove (202) on the docking joint (2).

7. The method for connecting external stub wings of a helicopter according to claim 6, characterized in that, Step S2 further includes three-stage docking: rotating the second docking hook (3) so that the third docking pin (10) is engaged in the third locking groove (203) on the docking joint (2).

8. The method for connecting external stub wings of a helicopter according to claim 3, characterized in that, In step S3, the docking connector (2) is provided with a first insertion hole (205), and the second docking hook (3) is provided with a second insertion hole (303); the locking pin (6) is inserted into the first insertion hole (205) and the second insertion hole (303).

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