CN117657422A - Connecting structure of external short wing of helicopter - Google Patents

Abstract

The invention relates to a connecting structure of an externally hung short wing of a helicopter, belongs to the technical field of helicopters, and solves the problems that in the prior art, the mounting and dismounting processes of the externally hung short wing of the helicopter are complex, and time and labor are wasted. The invention comprises the following steps: butt-joint lock hook component and locking pin; the butt lock hook assembly includes: the butt-joint lock hook and the butt-joint connector; the butt-joint lock hook and the butt-joint connector are respectively and fixedly arranged on the external short wing and the airframe; after the butt lock hook and the butt joint are in butt joint, the butt lock hook and the butt joint are locked through the locking pin. According to the invention, the butt-joint lock hook assembly is quickly butted and locked, so that the quick installation of the externally hung short wing is realized, and meanwhile, the externally hung short wing can be quickly disassembled by pulling out the locking pin, so that the manpower and material resources are saved.

Description

Connecting structure of external short wing of helicopter

Technical Field

The invention relates to the technical field of helicopters, in particular to a connecting structure of an externally hung short wing of a helicopter.

Background

The short wings of the common unmanned helicopter are fixedly connected to the fuselage through bolts, so that a plurality of bolts are required to be used for fastening in order to ensure the installation reliability, the installation and disassembly time is long, and the maintenance of the helicopter is inconvenient.

In addition, the short wing fixedly connected with the fuselage can increase the effective width of the unmanned helicopter, and in the vehicle-mounted transfer process of the unmanned helicopter, the unmanned helicopter needs to be placed in a large space, so that economic burden is caused, and the unmanned helicopter is inconvenient to park statically.

Therefore, a new short wing connection mode is needed to be provided, quick connection and disassembly are realized, the operation time is shortened, the disassembly in the transferring process is convenient, the requirement on transferring space is reduced, and the cost is reduced.

Disclosure of Invention

In view of the above analysis, the invention aims to provide a connection structure of an external short wing of a helicopter, which is used for solving the problems of complex installation and disassembly process, time and labor waste of the existing connection mode of the external short wing of the helicopter.

The aim of the invention is mainly realized by the following technical scheme:

a connection structure for a helicopter external winglet comprising: butt-joint lock hook component and locking pin; the butt lock hook assembly includes: the butt-joint lock hook and the butt-joint connector; the butt-joint lock hook and the butt-joint connector are respectively and fixedly arranged on the external short wing and the airframe; after the butt lock hook and the butt joint are in butt joint, the butt lock hook and the butt joint are locked through the locking pin.

Further, the butt lock hook includes: the first butt-joint lock hook and the second butt-joint lock hook; the first butt-joint lock hook and the second butt-joint lock hook are rotationally connected.

Further, the butt joint is provided with a first locking groove, a second locking groove and a third locking groove.

Further, the first locking groove, the second locking groove and the third locking groove are all U-shaped grooves.

Further, 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.

Further, a first butt joint pin and a second butt joint pin are arranged on the first butt joint lock hook; the first butt joint pin can be clamped into the first locking groove; the second docking pin is capable of being snapped into the second locking groove.

Further, a third butt joint pin is arranged on the second butt joint lock hook; the third docking pin is capable of being snapped into the third locking groove.

Further, a locking piece is arranged above the butt joint; the locking piece is provided with a first jack; and a second jack is arranged on the second butt-joint lock hook.

Further, when the third butt joint pin is clamped into the third locking groove, the second butt joint lock hook is covered outside the locking piece, and the first jack and the second jack are overlapped.

Further, the locking pin is installed in the first and second insertion holes.

The technical scheme of the invention can at least realize one of the following effects:

1. the invention designs a rotary butt joint connecting structure for the externally hung short wings of the large unmanned helicopter, and realizes the rapid installation and disassembly of the externally hung short wings; the external short wing is convenient to install and detach, is convenient for maintenance of the unmanned helicopter, and can save space for transportation of the unmanned helicopter.

2. According to the connecting structure of the external short wing of the helicopter, the butt-joint lock hook and the butt-joint connector cannot generate relative displacement after being butted, and further, the butt-joint lock hook and the butt-joint connector are connected and fixed through the locking pin, so that the reliability and stability of the external short wing when loading load are ensured.

In the invention, the technical schemes can be mutually combined to realize more preferable combination schemes. Additional features and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. The objectives and other advantages of the invention may be realized and attained by the structure particularly pointed out in the written description and drawings.

Drawings

The drawings are only for purposes of illustrating particular embodiments and are not to be construed as limiting the invention, like reference numerals being used to refer to like parts throughout the several views.

FIG. 1 is a connection structure of an external short wing of a helicopter of the invention;

FIG. 2 is a first mating shackle of a connection structure for a helicopter external winglet of the present invention;

FIG. 3 is a butt joint of the connection structure of the helicopter external winglet of the present invention;

FIG. 4 is a second mating shackle of the connection structure of the helicopter outer wing tab of the present invention;

FIG. 5 is a view showing a separated state of a butt lock hook assembly of a connection structure of an external short wing of a helicopter according to the present invention;

FIG. 6 is a first-stage docked state of the docking latch hook assembly of the connection structure of the helicopter external tab of the present invention;

FIG. 7 is a secondary docked state of the docking latch hook assembly of the connection structure of the helicopter external tab of the present invention;

FIG. 8 is a three-stage docked state of the docking latch hook assembly of the connection structure of the helicopter external tab of the present invention;

FIG. 9 is a limit state of the locking pin of the present invention;

fig. 10 is a state of releasing the limit of the lock pin of the present invention.

Reference numerals:

1-a first butt lock hook; 2-butt joint; 3-a second butt lock hook; 4-externally hanging short wings; 5-fuselage; 6-locking pins; 7-a first docking pin; 8-a hinge shaft; 9-a second docking pin; 10-a third docking pin;

11-a first upper lug; 12-a first lower ear;

21-a second upper ear; 22-a second inferior ear;

101-a first pin shaft mounting hole; 102-a second pin shaft mounting hole; 103-a first hinge hole; 104-a latch hook base;

201-a first locking groove; 202-a second locking groove; 203-a third locking groove; 204-locking piece; 205-a first jack;

301-a second hinge hole; 302-a third pin mounting hole; 303-a second jack; 304-a fixed block; 305-limiting cover; 306-a spring;

601—pin cap; 602-a first stem; 603-a second stem.

Detailed Description

The following detailed description of preferred embodiments of the invention is made in connection with the accompanying drawings, which form a part hereof, and together with the description of the embodiments of the invention, are used to explain the principles of the invention and are not intended to limit the scope of the invention.

Example 1

In one embodiment of the present invention, a connection structure for a helicopter external short wing is disclosed, as shown in fig. 1-4, comprising: a butt-joint lock hook assembly and a locking pin 6; the butt lock hook assembly includes: a butt lock hook and a butt joint 2; the butt-joint lock hook and the butt-joint connector 2 are respectively and fixedly arranged on the external short wing 4 and the machine body 5; after the butt lock hook is in butt joint with the butt joint connector 2, the butt lock hook is locked through a locking pin 6.

Specifically, as shown in fig. 1, the first butt-joint latch hook 1 is fixedly installed on the side surface of the fuselage 5, and the butt-joint connector 2 is fixedly installed on the side surface of the external short wing 4.

Further, as shown in fig. 1, the external short wing 4 and the body 5 are connected through two or more groups of butt-joint latch hook assemblies.

Specifically, when the fuselage 5 and the external short wing 4 are connected by adopting two groups/multiple groups of butt-joint lock hook assemblies, the two groups/multiple groups of butt-joint lock hook assemblies are arranged in parallel, the butt-joint lock hooks of the two groups/multiple groups of butt-joint lock hook assemblies and the butt-joint connector 2 can be simultaneously butted, and after the butt joint is completed, the locking of the butt-joint lock hook assemblies is realized through the locking pin 6.

In this embodiment, after the two/more groups of butt-joint latch hook assemblies are butt-jointed, the butt-joint latch hook and the butt-joint connector 2 can be connected, and meanwhile, the external short wing 4 and the machine body 5 can be connected. Further, the locking pin 6 is arranged between the butt-joint lock hook and the butt-joint connector 2, so that the butt-joint lock hook assembly can be locked, the secondary connection fixation is realized, and the connection stability between the external short wing 4 and the machine body 5 is ensured.

In one embodiment of the present invention, as shown in fig. 1, the butt lock hook includes: a first butt-joint lock hook 1 and a second butt-joint lock hook 3; the first butt-joint lock hook 1 and the second butt-joint lock hook 3 are rotatably connected.

Further, as shown in fig. 2, a first hinge hole 103 is provided on the first butt lock hook 1; as shown in fig. 4, the second butt lock hook 3 is provided with a second hinge hole 301. As shown in fig. 5, the hinge shaft 8 is installed in the first hinge hole 103 and the second hinge hole 301, and the second mating lock hook 3 is hinge-installed above the first mating lock hook 1 through the hinge shaft 8.

In one embodiment of the present invention, the first butt lock hook 1 is structured as shown in fig. 2.

Specifically, the first butt-joint latch hook 1 is composed of a latch hook base 104 and a binaural structure; and the latch hook base 104 and the binaural structure are an integral structure. The latch hook base 104 is fixedly connected with the body 5 by welding or bolts.

As shown in fig. 2, the latch hook base 104 is provided with an upper and a lower lugs, specifically: a first upper lug portion 11 and a first lower lug portion 12.

As shown in fig. 2, a first pin shaft mounting groove is formed in the first lower supporting lug part 12, and first pin shaft mounting holes 101 are formed in two sides of the first pin shaft mounting groove; the first pin shaft mounting hole 101 is used for mounting the first docking pin 7, and the first docking pin 7 is fixedly mounted in the first pin shaft mounting hole 101.

As shown in fig. 2, a first hinge hole 103 and a second pin shaft mounting groove are formed in the first upper lug portion 11; wherein, the first hinging hole 103 is used for hinging and installing the second butt-joint lock hook 3; second pin shaft mounting holes 102 are formed in two sides of the second pin shaft mounting groove, the second pin shaft mounting holes 102 are used for mounting the second butt joint pins 9, and the second butt joint pins 9 are fixedly mounted in the second pin shaft mounting holes 102.

In one embodiment of the invention, the butt joint 2 is shown in fig. 3.

Specifically, the butt joint 2 is fixedly connected with the externally hung short wing 4 or is in an integral structure. The butt joint 2 includes: a second upper ear portion 21 and a second lower ear portion 22.

As shown in fig. 3, a first locking groove 201 is formed at the bottom of the second lower support lug 22, and the first locking groove 201 is used for being matched with the first docking pin 7; when the first butt lock hook 1 is in butt joint with the butt joint 2, the first butt pin 7 is clamped in the first locking groove 201, as shown in fig. 5.

As shown in fig. 3, a second locking groove 202 is formed on the side surface of the second upper supporting lug part 21, and the second locking groove 202 is used for being matched with the second butting pin 9 on the first butting latch hook 1; when the first butt lock hook 1 is in butt joint with the butt joint 2, the second butt lock pin 9 is clamped in the second lock groove 202, as shown in fig. 6.

As shown in fig. 3, a locking piece 204 is arranged above the second upper supporting lug part 21, a first jack 205 is arranged on the locking piece 204, and the first jack 205 is used for being matched with a second jack 303 on the second butt locking hook 3; as shown in fig. 8, after the second mating lock hook 3 is mated with the mating connector 2, the first jack 205 and the second jack 303 are aligned, and the locking pin 6 is inserted into the first jack 205 and the second jack 303, so that the second mating lock hook 3 and the mating connector 2 can be locked, as shown in fig. 8.

In one embodiment of the present invention, as shown in fig. 3, the first locking groove 201, the second locking groove 202 and the third locking groove 203 are U-shaped grooves. Alternatively, the first locking groove 201, the second locking groove 202 and the third locking groove 203 are all semicircular grooves.

Further, as shown in fig. 3, 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.

In one embodiment of the present invention, the second mating lock hook 3 is shown in fig. 4.

Specifically, the second butt lock hook 3 has a slot structure with a groove.

One end of the second butt-joint lock hook 3 is provided with a first groove, the other end is provided with a second groove, and the middle part is provided with a third groove.

Second hinge holes 301 are formed in two sides of the first groove, and third pin shaft mounting holes 302 are formed in two sides for mounting the second groove; the third docking pin 10 is fixedly mounted in the third pin mounting hole 302. The third groove can be matched with the locking piece 204, and second jacks 303 are arranged on two sides of the third groove; the second receptacle 303, when aligned with the first receptacle 205, is used to mount the locking pin 6.

In practice, as shown in FIGS. 5-8:

as shown in fig. 5, when the fuselage 5 and the plug-in winglet 4 are in a separated state: a first butt joint pin 7 and a second butt joint pin 9 are arranged on the first butt joint lock hook 1; a third docking pin 10 is mounted on the second docking latch hook 3. The butt joint 2 is provided with a first locking groove 201, a second locking groove 202 and a third locking groove 203. A locking piece 204 is arranged above the butt joint 2; the locking piece 204 is provided with a first jack 205; the second butt lock hook 3 is provided with a second jack 303.

As shown in fig. 6, when the first docking pin 7 is docked with the first locking groove 201 and the first docking pin 7 is engaged with the first locking groove 201, the inner side wall surface of the first pin shaft mounting groove of the first lower lug portion 12 is bonded to the outer side surface of the second lower lug portion 22.

As shown in fig. 7, the second docking pin 9 is docked with the second locking groove 202; when the second docking pin 9 is locked in the second locking groove 202, the inner side wall surface of the second pin shaft mounting groove of the first upper support lug 11 is attached to the outer side surface of the second upper support lug 21 of the docking head 2.

As shown in fig. 8, when the third docking pin 10 is docked with the third locking groove 203, the second docking lock hook 3 is rotated so that the third docking pin 10 is caught in the third locking groove 203. At this time, the second butt lock hook 3 is covered outside the lock piece 204, and the first jack 205 and the second jack 303 overlap; the locking pin 6 can be inserted into the first insertion hole 205 and the second insertion hole 303.

As shown in fig. 1, the locking pin 6 is inserted into the first butt lock hook 1 and the second butt lock hook 3, and the butt lock hook assembly is butt-jointed. The first butt-joint lock hook 1 is fixed on the machine body 5 through riveting or screwing, the butt joint 2 is riveted at one end of the front edge position of the externally-hung short wing 4, and the butt joint 2 and the externally-hung short wing 4 are integrally designed; after the butt joint of the plurality of groups of butt joint latch hook assemblies is completed, the connection of the external short wing 4 and the airframe 5 is completed.

The connecting structure of the helicopter externally hung short wing is made of 7075-T6 aviation aluminum alloy, so that the strength and the rigidity are ensured, the force transmission route is short, the weight of the connecting structure is saved by carrying out weight reduction design according to the force transmission condition.

Example 2

An embodiment of the present invention was modified based on example 1.

In order to avoid the locking pin 6 from being separated from the first butt-locking hook 1 and the second butt-locking hook 3, in this embodiment, the locking pin 6 is configured to be bendable, and a limiting component is disposed on a side surface of the second butt-locking hook 3, as shown in fig. 9 and 10.

Specifically, the lock pin 6 includes: a pin cap 601, a first stem 602, and a second stem 603; wherein, the pin cap 601 is fixedly connected with the first rod portion 602, and the length of the pin cap 601 is larger than the diameter of the first rod portion 602; the second rod 603 is hinged to the first rod 602, and both the first rod 602 and the second rod 603 can pass through the first jack 205 and the second jack 303.

Specifically, a pin rod placement groove for placing the second rod portion 603 is provided on the side surface of the second butt lock hook 3; as shown in fig. 9, after the locking pin 6 passes through the second butt lock hook 3, the second lever portion 603 is turned to be placed in the pin lever placing groove.

Specifically, the spacing subassembly includes: a fixed block 304, a limit shield 305 and a spring 306.

As shown in fig. 9, the fixed block 304 is fixedly mounted on the side surface of the second butt lock hook 3 by welding or bonding, the limit cover 305 is covered outside the fixed block 304, and the limit cover 305 is connected with the fixed block 304 by a spring 306.

Further, when the second rod portion 603 is bent upwards and placed in the pin rod placing groove, the limiting cover 305 moves downwards under the action of the elastic force of the spring 306, and then the limiting cover 305 limits the second rod portion 603, so that the second rod portion 603 cannot rotate relative to the first rod portion 602, and the locking pin 6 is prevented from falling off.

As shown in fig. 10, the limiting cover 305 is pulled upwards to compress the spring 306, the limiting cover 305 moves upwards, and the pin rod placing groove is completely exposed; at this time, the second rod portion 603 can be pressed into the pin accommodating groove, or the second rod portion 603 can be taken out of the pin accommodating groove.

In this embodiment, the installation process of the locking pin 6 is:

rotating the second rod portion 603 so as to be coaxial with the first rod portion 602, and penetrating the locking pin 6 into the first insertion hole 205 and the second insertion hole 303; the second rod portion 603 penetrates out of the other side of the second butt locking hook 3, the limiting cover 305 is pulled upwards to expose the pin rod placing groove, the second rod portion 603 is rotated to be bent upwards and placed in the pin rod placing groove, the limiting cover 305 is loosened, the limiting cover 305 moves downwards under the action of the elastic force of the spring 306, rotation of the second rod portion 603 is limited, and the locking pin 6 is prevented from falling off. At this time, the lock pin 6 cannot be displaced relative to the second butt lock hook 3, and the second butt lock hook 3 is fixed integrally with the lock piece 204 as shown in fig. 9.

As shown in fig. 10, the process of extracting the lock pin 6 is:

the limiting cover 305 is pulled upward to expose the pin rod placing groove, the second rod portion 603 is rotated to be taken out of the pin rod placing groove, the second rod portion 603 is coaxial with the first rod portion 602 (the second rod portion 603 and the first rod portion 602 are positioned on the same straight line), the locking pin 6 is pulled outward, and the locking pin 6 is pulled out of the second butt lock hook 3 and the locking piece 204. At this time, the second butt lock hook 3 and the first butt lock hook 1 can rotate relatively, and then the butt lock hook and the butt joint 2 can be separated.

In this embodiment, the limiting cover 305 limits the second rod portion 603, so that the locking pin 6 and the second butt locking hook 3 are combined into a whole; and further ensures the connection stability of the butt-joint lock hook assembly. Compression spring 306 upwards pulls limiting cover 305, and limiting cover 305 releases the spacing of second pole portion 603, can pull out locking round pin 6 this moment, and then can follow third locking groove 203 with second butt joint latch hook 3 and unscrew, realizes the dismantlement of outer short wing 4.

In this embodiment, the connection reliability of the fuselage 5 and the external short wing 4 is ensured by multistage limiting. Specifically, after the butt joint 2 and the butt lock hook are in butt joint, the butt joint 2 and the butt lock hook cannot relatively move, so that the first-stage limiting is realized; further, a locking pin 6 is inserted into the first butt locking hook 1 and the second butt locking hook 3 for locking, so that the secondary limit is realized; further, set up spacing subassembly in the outside of second butt joint latch hook 3, prevent that locking pin 6 from sliding out, and then avoid first butt joint latch hook 1 and second butt joint latch hook 3 to take place relative rotation, further guarantee the connection reliability, realized tertiary spacing.

In the invention, when the connection structure of the external short wing of the helicopter in the embodiment 1 or the embodiment 2 is adopted to connect and detach the external short wing, the connection between the external short wing 4 and the fuselage 5 can be realized through the mutual butt joint and locking of the lock hook butt joint structures.

Compared with the prior art, the technical scheme provided by the invention has at least one of the following beneficial effects:

1. when the connecting structure of the external short wing of the helicopter is used, the single external short wing 4 is quickly installed on the helicopter body 5 for only about 80 seconds and quickly detached for only about 40 seconds by combining with the operation evaluation of a real object.

2. The connecting structure has the advantages of light weight, compact structure, convenient and flexible assembly and disassembly, convenient operation and high reliability; in the ground transportation process of the unmanned helicopter, the external short wing 4 can be detached at any time, so that the occupied space of the unmanned helicopter during vehicle-mounted transportation is effectively saved, and the unmanned helicopter is convenient to transport and meanwhile the cost is saved.

3. According to the connecting structure of the external short wing of the helicopter, through mutual butt joint of the three groups of butt joint pins and the locking grooves, 6 degrees of freedom between the first butt joint lock hook 1 and the butt joint connector 2 are limited, and the relative positions of the first butt joint lock hook 1 and the butt joint connector 2 are ensured to be fixed.

4. According to the connecting structure of the external short wing of the helicopter, the screw is not required to be fixed in the whole process, and the process of repeatedly screwing or unscrewing the screw is omitted when the external short wing is installed or disassembled, so that the operation is simple and convenient, time and labor are saved, and the labor in the installation or disassembly process is saved.

The present invention is not limited to the above-mentioned embodiments, and any changes or substitutions that can be easily understood by those skilled in the art within the technical scope of the present invention are intended to be included in the scope of the present invention.

Claims (10)

1. A connection structure for a helicopter external winglet, comprising: a butt-joint lock hook assembly and a locking pin (6); the butt lock hook assembly includes: a butt lock hook and a butt joint (2); the butt-joint lock hook and the butt-joint connector (2) are respectively and fixedly arranged on the external short wing (4) and the machine body (5); after the butt lock hook is in butt joint with the butt joint connector (2), the butt lock hook is locked through a locking pin (6).

2. The helicopter skin attachment configuration of claim 1 wherein said docking shackle comprises: a first butt-joint lock hook (1) and a second butt-joint lock hook (3); the first butt-joint lock hook (1) and the second butt-joint lock hook (3) are rotatably connected.

3. The connection structure of the helicopter external short wing according to claim 2, characterized in that the butt joint (2) is provided with a first locking groove (201), a second locking groove (202) and a third locking groove (203).

4. A connection structure of a helicopter external winglet according to claim 3, characterized in that the first (201), second (202) and third (203) locking grooves are U-shaped grooves.

5. The helicopter skin attachment configuration according to claim 3 or 4, wherein 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).

6. The connection structure of the helicopter external short wing according to claim 5, characterized in that the first butt lock hook (1) is provided with a first butt pin (7) and a second butt pin (9); the first docking pin (7) can be snapped into the first locking groove (201); the second docking pin (9) can be snapped into the second locking groove (202).

7. The connection structure of the helicopter external short wing according to claim 6, characterized in that said second docking latch hook (3) is fitted with a third docking pin (10); the third docking pin (10) can be snapped into the third locking groove (203).

8. The connection structure of the helicopter external short wing according to claim 7, characterized in that a locking piece (204) is arranged above the butt joint (2); the locking piece (204) is provided with a first jack (205); and a second jack (303) is arranged on the second butt-joint lock hook (3).

9. The connection structure of the helicopter external short wing according to claim 8, characterized in that when the third docking pin (10) is clamped into the third locking groove (203), the second docking latch hook (3) is covered outside the locking piece (204) and the first jack (205) and the second jack (303) coincide.

10. The connection structure of a helicopter external tab according to claim 9, characterized in that said locking pin (6) is mounted in said first (205) and second (303) receptacles.