CN211281437U - Aircraft with a flight control device - Google Patents
Aircraft with a flight control device Download PDFInfo
- Publication number
- CN211281437U CN211281437U CN201921690423.5U CN201921690423U CN211281437U CN 211281437 U CN211281437 U CN 211281437U CN 201921690423 U CN201921690423 U CN 201921690423U CN 211281437 U CN211281437 U CN 211281437U
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- wing
- fuselage
- connecting piece
- fixing
- locking
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Abstract
The utility model discloses an aircraft, including fuselage and wing, the aircraft still includes latched device and complex connecting piece with it, latched device with the connecting piece set up in the fuselage with the inside of wing, latched device connect in the fuselage or the wing, the one end of connecting piece connect in the wing or the fuselage, the other end of connecting piece is inserted and is located latched device is when pressing during latched device, the connecting piece with latched device can dismantle. The locking mechanism is arranged on the machine body or the wing, the connecting piece is arranged on the wing or the machine body, when the wing is disassembled, the locking mechanism is pressed, the connecting piece is separated from the locking mechanism, the quick disassembly of the machine body and the wing is realized, when the wing is installed, the connecting piece is inserted into the locking mechanism, the quick connection of the wing and the machine body is realized, in the installation and disassembly processes of the wing, the use of tools is not needed, the manual operation can be completed, and the disassembly and the assembly are quick and convenient.
Description
Technical Field
The utility model relates to an aircraft.
Background
The wings and the fuselage of a part of the existing aircraft are integrally formed, cannot be disassembled, so that the packaging size is large, the transportation is very inconvenient, a part of the existing aircraft is provided with a detachable fixing device on the outer surface of the aircraft, the number of parts of the fixing device is large, time and labor are wasted when the wings are disassembled, and the fixing device is arranged in a fixing mode on the outer surface of the aircraft, so that the appearance attractiveness of the aircraft and the pneumatic performance of the aircraft are influenced.
SUMMERY OF THE UTILITY MODEL
The to-be-solved technical problem of the utility model is that the fixing device part is many in order to overcome the connection wing among the prior art and fuselage, and the defect that wastes time and energy when dismantling the wing provides an aircraft.
The utility model discloses an above-mentioned technical problem is solved through following technical scheme:
the utility model provides an aircraft, includes fuselage and wing, aircraft still includes latch mechanism and complex connecting piece with it, latch mechanism with the connecting piece set up in the fuselage with the inside of wing, latch mechanism connect in the fuselage or the wing, the one end of connecting piece connect in the wing or the fuselage, the other end of connecting piece is inserted and is located latch mechanism is when pressing during latch mechanism, the connecting piece with latch mechanism can dismantle.
In the scheme, the locking mechanism is arranged on the fuselage, the connecting piece is arranged on the wing, the locking mechanism can also be arranged on the wing, the connecting piece is arranged on the fuselage, and the locking mechanism and the connecting piece are selectively arranged as required. When the wing is installed, the connecting piece is inserted into the locking mechanism, so that the connection between the wing and the body is realized, when the wing is disassembled, the locking mechanism is pressed, the connecting piece is separated from the locking mechanism, the disassembly between the body and the wing is realized, in the installation and disassembly processes of the wing, tools are not needed, the manual operation can be completed, and the disassembly and the assembly are quick and convenient.
Preferably, latched device is including the fixing base, elastic element, the locking plate that connect gradually, the fixing base cover is located the locking plate, the locking plate can be followed the fixing base slides from top to bottom, elastic element set up in the fixing base with between the locking plate, be used for promoting the locking plate is kept away from the fixing base, the locking plate with be equipped with the confession on the fixing base the passageway that the connecting piece passed, the connecting piece is inserted and is located the passageway is connected in the locking plate, when promoting during the locking plate, the locking plate breaks away from the connecting piece, in order to realize the connecting piece with latched device can dismantle.
In this scheme, elastic element exerts a decurrent effort for the locking plate, locates the connecting piece with the inward flange pressure of the passageway on the locking plate, and the locking plate is connected with the connecting piece, realizes connecting piece and latched device's locking, and when upwards promoting the locking plate, the inward flange of the passageway of locking plate breaks away from the connecting piece, realizes dismantling of connecting piece and latched device, and then realizes dismantling of wing and fuselage.
Preferably, the locking mechanism further includes a pressing member, the pressing member has a hollow accommodating cavity, an opening is formed in a top end of the pressing member, the locking plate is inserted into the opening, the fixing base is sleeved on the pressing member from the top end of the pressing member, the pressing member can slide up and down along the fixing base, two ends of the elastic element respectively abut against an inner wall surface of the fixing base and a top surface of the pressing member, and the pressing member is provided with a connecting hole, which is consistent with the channel in size and direction, for the insertion of the connecting member.
In this scheme, the locking plate card is located on the pressing part, and when the pressing part was promoted to manual, locking plate and pressing part removed together, realized locking and unblock function, set up the convenient manual locking plate that promotes of pressing part, realized unblock latched device.
Preferably, the two end faces of the fixing seat are provided with elongated sliding grooves, and the two end faces of the pressing member are provided with first protruding portions which are slidably disposed in the sliding grooves.
In this scheme, the pressing piece can slide from top to bottom in the fixing base, and the direction of spout is unanimous with the gliding direction of pressing piece, sets up the bellying and slides in the spout, guarantees that the pressing piece slides when sliding in the fixing base, and it is steady to slide to prevent the pressing piece roll-off fixing base.
Preferably, the top surface of the fixing seat is provided with a second protruding portion extending outwards, and an accommodating cavity is formed in the second protruding portion and used for accommodating the upper end of the elastic element.
In this scheme, the holding chamber of second bellying and elastic element's cavity intercommunication, the holding chamber in the second bellying is used for holding elastic element's upper end, carries on spacingly to elastic element, prevents that elastic element is crooked when compressing, improves elastic element's stability.
Preferably, a plurality of ear seats are arranged on the peripheral surface of the fixing seat at intervals, and each ear seat is provided with a first connecting hole.
In this scheme, set up the ear seat and be convenient for fix the inside at fuselage or wing with latched device through first connecting hole.
Preferably, the wing includes a plurality of fixed plates, the fixed plate along the length direction interval of wing set up in the inside of wing, each still be provided with a plurality of second connecting holes on the fixed plate, the one end of connecting piece is passed through the second connecting hole is connected a plurality of the fixed plate is as an organic whole, the other end of connecting piece is inserted and is located the channel connect in the locking plate.
In this scheme, the fixed plate can increase the intensity of wing, also is convenient for set up connecting piece or latched device on the fixed plate simultaneously, only needs to satisfy the terminal surface that the connecting piece stretches out the place and connect in latched device, adopts above-mentioned connection form, more firm when making wing and fuselage be connected.
Preferably, the connecting member includes a lock pin and a fixing rod, two ends of the lock pin are respectively a buckle end and a connecting end, the buckle end is inserted into the channel and connected to the lock plate, the connecting end is connected to one end of the fixing rod, the other end of the fixing rod is connected to the plurality of fixing plates integrally through the second connecting hole, and when the lock plate is pushed, the lock plate is separated from the buckle end, so that the lock pin and the buckle mechanism can be detached.
In this scheme, in order to reduce fuselage weight, still need guarantee joint strength simultaneously, divide into dead lever and lockpin with the connecting piece, conveniently select the connecting piece of different materials.
Preferably, the lock pin is rod-shaped, the end of the buckle end is a conical structure, a first annular groove is formed in the outer peripheral surface of the buckle end, and the lock plate is clamped in the first annular groove.
In the scheme, the conical structure is small in front and large in back and can conveniently slide into the channel, and quick locking is realized. The first annular groove is connected with the locking plate in a clamping mode, and the connecting strength of the locking mechanism is improved.
Preferably, a plurality of second annular grooves are formed in the outer peripheral surface of the connecting end along the length direction at intervals, the fixing rod is of a hollow tubular structure, and the connecting end is bonded in the hollow structure of the fixing rod through glue arranged in the second annular grooves.
In this scheme, the lockpin bonds in the hollow structure in the dead lever, and the annular recess of multichannel second can hold more glue, improves the bonding effect.
Preferably, a hole is formed in the bottom surface of the fuselage or the wing, the pressing piece is located in the hole, and when the pressing piece is pressed through the hole, the connecting piece and the locking mechanism can be detached.
In this scheme, the hole sets up on the bottom surface, can prevent that dust or rainwater from directly getting into the inside of fuselage through the hole. The locking mechanism and the connecting piece are arranged inside the fuselage and the wings, and the pressing piece is arranged in the hole of the fuselage or the wing, so that the locking mechanism can be conveniently unlocked manually through the hole, the fuselage and the wing can be manually disassembled without tools, and the wing dismounting efficiency is improved.
Preferably, the number of the wings is two, two the wings are symmetrically arranged on two sides of the fuselage, each end face of one end, close to the fuselage, of each wing is a first binding face, the first binding face is bound to the side face of the fuselage, and the connecting piece penetrates through the first binding face so that the wings are connected to the fuselage.
In this scheme, the first binding face of wing is laminated in the side of fuselage better to set up two wing symmetries in the both sides of fuselage, improved the aerodynamic performance of aircraft.
On the basis of the common knowledge in the field, the above preferred conditions can be combined at will to obtain the preferred embodiments of the present invention.
The utility model discloses an actively advance the effect and lie in: the locking mechanism is arranged on the machine body or the wing, the connecting piece is arranged on the wing or the machine body, when the wing is disassembled, the locking mechanism is pressed, the connecting piece is separated from the locking mechanism, the quick disassembly of the machine body and the wing is realized, when the wing is installed, the connecting piece is inserted into the locking mechanism, the quick connection of the wing and the machine body is realized, in the installation and disassembly processes of the wing, the use of tools is not needed, the manual operation can be completed, and the disassembly and the assembly are quick and convenient.
Drawings
Fig. 1 is a schematic structural diagram of an aircraft according to a preferred embodiment of the present invention.
Fig. 2 is a schematic structural diagram of a latch mechanism according to a preferred embodiment of the present invention.
Fig. 3 is a schematic structural diagram of the latch mechanism, the fixing plate and the connecting member according to a preferred embodiment of the present invention.
Description of reference numerals:
fuselage 1
Wing 2
First abutting surface 22
Fixed seat 31
Connecting hole 341
Channel 35
Connecting piece 4
Locking pin 41
First annular groove 411
Second annular groove 412
Fixing rod 42
Detailed Description
The present invention will be more clearly and completely described below by way of examples and with reference to the accompanying drawings, but the present invention is not limited thereto.
As shown in fig. 1-3, this embodiment discloses an aircraft, which includes a fuselage 1 and a wing 2, and the aircraft further includes a locking mechanism 3 and a connecting member 4 engaged with the locking mechanism 3, where the locking mechanism 3 and the connecting member 4 are disposed inside the fuselage 1 and the wing 2, the locking mechanism 3 is connected to the fuselage 1 or the wing 2, one end of the connecting member 4 is connected to the wing 2 or the fuselage 1, and the other end of the connecting member 4 is inserted into the locking mechanism 3, and when the locking mechanism 3 is pressed, the connecting member 4 is detachable from the locking mechanism 3.
In this embodiment, the latch mechanism 3 is disposed on the fuselage 1, the connecting member 4 is disposed on the wing 2, or the latch mechanism 3 may be disposed on the wing 2, the connecting member 4 is disposed on the fuselage 1, and the latch mechanism 3 and the connecting member 4 are selectively disposed as required. When the wing 2 is installed, the connecting piece 4 is inserted into the locking mechanism 3, the quick connection between the wing 2 and the body 1 is realized, when the wing 2 is disassembled, the locking mechanism 3 is pressed, the connecting piece 4 is separated from the locking mechanism 3, the disassembly between the body 1 and the wing 2 is realized, in the installation and disassembly processes of the wing 2, tools are not needed, manual operation can be completed, and the disassembly and the assembly are quick and convenient.
In the embodiment, the elastic element 32 is a spring, and the elastic element 32 may be replaced by other components having an elastic contraction function. Elastic element 32 exerts a decurrent effort for locking sheet 33, locates connecting piece 4 with the inward flange pressure of passageway 35 on the locking sheet 33, and locking sheet 33 is connected with connecting piece 4, realizes the locking of connecting piece 4 and latched device 3, and when upwards promoting locking sheet 33, the inward flange of passageway 35 of locking sheet 33 breaks away from connecting piece 4, realizes dismantling of connecting piece 4 and latched device 3, and then realizes dismantling of wing 2 and fuselage 1.
The locking mechanism 3 further includes a pressing member 34, the pressing member 34 has a hollow accommodating cavity, an opening 343 is disposed at a top end of the pressing member 34, the locking plate 33 is inserted into the opening 343, the fixing base 31 is sleeved on the pressing member 34 from the top end of the pressing member 34, the pressing member 34 can slide up and down along the fixing base 31, two ends of the elastic element 32 respectively abut against an inner wall surface of the fixing base 31 and a top surface of the pressing member 34, and the pressing member 34 is provided with a connecting hole 341 with a size and a direction consistent with those of the passage 35 for the insertion of the connecting member 4.
In this embodiment, the locking piece 33 is clamped on the pressing piece 34, when the pressing piece 34 is pushed manually, the locking piece 33 and the pressing piece 34 move together to realize the locking and unlocking functions, and the pressing piece 34 is arranged to facilitate the manual pushing of the locking piece 33 and protect fingers when being pressed.
The two end surfaces of the fixed seat 31 are provided with elongated sliding grooves 311, the two end surfaces of the pressing member 34 are provided with first protruding portions 342, and the first protruding portions 342 are slidably disposed in the sliding grooves 311.
In this embodiment, the pressing member 34 can slide up and down in the fixing base 31, the direction of the sliding slot 311 is the same as the sliding direction of the pressing member 34, and the protrusion is arranged to slide in the sliding slot 311, so that when the pressing member 34 slides in the fixing base 31, the sliding is stable, and the pressing member 34 is prevented from sliding out of the fixing base 31.
The top surface of the fixing base 31 is provided with a second protrusion 312 extending outward, and a receiving cavity is provided in the second protrusion 312 and is used for receiving the upper end of the elastic element 32.
In this embodiment, the elastic element 32 is a spring, the accommodating cavity of the second protruding portion 312 is communicated with the cavity for accommodating the elastic element 32, and the accommodating cavity in the second protruding portion 312 is used for accommodating the upper end of the spring, so that the spring is limited, the spring is prevented from being inclined when being compressed, and the stability of the spring is improved.
A plurality of ear seats 313 are spaced apart from each other on the outer peripheral surface of the fixing seat 31, and each ear seat 313 is provided with a first connection hole 3131. The ear mount 313 is provided to facilitate the fixing of the latch mechanism 3 inside the fuselage 1 or wing 2 through the first attachment aperture 3131.
In this embodiment, the fixing plate 21 can increase the strength of the wing 2, and at the same time, the fixing plate 21 can be conveniently provided with the connecting piece 4 or the locking mechanism 3, and only the requirement that the connecting piece 4 extends out of the end face and is connected to the locking mechanism 3 is met, by adopting the above connection form, the wing 2 is more firmly connected with the fuselage 1, and one or more fixing plates 21 are selectively arranged according to the requirement.
The connecting member 4 includes a lock pin 41 and a fixing rod 42, the two ends of the lock pin 41 are a fastening end 414 and a connecting end 415 respectively, the fastening end 414 is inserted into the channel 35 and connected to the locking plate 33, the connecting end 415 is connected to one end of the fixing rod 42, the other end of the fixing rod 42 is connected to the plurality of fixing plates 21 through the second connecting hole 211 as a whole, when the locking plate 33 is pushed, the locking plate 33 is separated from the fastening end 414, so as to realize that the lock pin 41 can be detached from the latch mechanism 3. The lock pin 41 is rod-shaped, the end of the locking end 414 is a conical structure 413, a first annular groove 411 is arranged on the outer peripheral surface of the locking end 414, and the locking piece 33 is clamped in the first annular groove 411. A plurality of second annular grooves 412 are formed at intervals on the outer peripheral surface of the connecting end 415 along the length direction of the connecting end, the fixing rod 42 is a hollow tubular structure, and the connecting end 415 is bonded in the hollow structure of the fixing rod 42 through glue arranged in the second annular grooves 412.
In this embodiment, the fixing rod 42 is a hollow carbon fiber tube, which can reduce the weight of the wing 2, but it is difficult to form a slot on the fixing rod, so the lock pin 41 made of aluminum alloy is connected to the end of the fixing rod 42, and the lock pin 41 is provided with a first annular groove 411 to be engaged with the locking piece 33. The conical structure 413 is smaller at the front and larger at the back to facilitate sliding into the locking channel 35. The connecting end 415 of the rod-shaped lock pin 41 is inserted into and bonded to the hollow tubular fixing rod 42, and in order to improve the connecting effect, a plurality of second annular grooves 412 are formed in the lock pin 41 to accommodate more glue, so that the bonding effect between the lock pin 41 and the fixing rod 42 is improved, and the lock pin 41 and the fixing rod 42 are connected more firmly.
The bottom surface of the fuselage 1 or the wing 2 is provided with a hole, the pressing piece 34 is positioned in the hole, and when the pressing piece 34 is pushed through the hole, the connecting piece 4 and the locking mechanism 3 can be detached.
In this embodiment, the holes are provided on the underside of the aircraft, which prevents dust or rain water from entering the interior of the fuselage 1 directly through the holes. The locking mechanism 3 and the connecting piece 4 are arranged inside the fuselage 1 and the wing 2, and the pressing piece 34 is arranged in the hole of the fuselage 1 or the wing 2, so that the locking mechanism 3 can be conveniently unlocked manually through the hole, manual disassembly of the fuselage 1 and the wing 2 can be realized without tools, and the disassembly and assembly efficiency of the wing 2 is improved. The holes are not shown.
The quantity of wing 2 is two, and two wing 2 symmetries set up in the both sides of fuselage 1, and the terminal surface that each wing 2 is close to the one end of fuselage 1 is first binding face 22, and first binding face 22 is laminated in the side of fuselage 1, and first binding face 22 is passed to connecting piece 4 for wing 2 connects in fuselage 1.
In this embodiment, the first attaching surfaces 22 of the wings 2 are attached to the lateral surfaces of the fuselage 1, and the two wings 2 are symmetrically arranged on the two sides of the fuselage 1, so that the aerodynamic performance of the aircraft is improved.
Although specific embodiments of the present invention have been described above, it will be understood by those skilled in the art that this is by way of example only and that the scope of the invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the spirit and the principles of the present invention, and these changes and modifications are all within the scope of the present invention.
Claims (12)
1. The utility model provides an aircraft, includes fuselage and wing, its characterized in that, aircraft still includes latch mechanism and complex connecting piece with it, latch mechanism with the connecting piece set up in the fuselage with the inside of wing, latch mechanism connect in the fuselage or the wing, the one end of connecting piece connect in the wing or the fuselage, the other end of connecting piece is inserted and is located latch mechanism is when pressing during latch mechanism, the connecting piece with latch mechanism can dismantle.
2. The aircraft according to claim 1, wherein the locking mechanism comprises a fixing seat, an elastic element, and a locking plate, which are sequentially connected, the fixing seat is sleeved on the locking plate, the locking plate can slide up and down along the fixing seat, the elastic element is disposed between the fixing seat and the locking plate for pushing the locking plate to be away from the fixing seat, the locking plate and the fixing seat are provided with a channel for the connecting piece to pass through, the connecting piece is inserted into the channel and connected to the locking plate, and when the locking plate is pushed, the locking plate is separated from the connecting piece, so that the connecting piece can be detached from the locking mechanism.
3. The aircraft according to claim 2, wherein the latch mechanism further comprises a pressing member having a hollow accommodating cavity, an opening is formed at a top end of the pressing member, the locking plate is inserted into the opening, the fixing base is sleeved on the pressing member from the top end of the pressing member, the pressing member can slide up and down along the fixing base, two ends of the elastic element respectively abut against an inner wall surface of the fixing base and a top surface of the pressing member, and a connecting hole is formed in the pressing member, which is consistent with the size and direction of the passage, for the insertion of the connecting member.
4. The aircraft according to claim 3, wherein the fixing seat is provided with elongated sliding grooves on both end surfaces thereof, and the pressing member is provided with first protrusions on both end surfaces thereof, wherein the first protrusions are slidably disposed in the sliding grooves.
5. The aircraft according to claim 2, wherein the top surface of the fixed seat is provided with a second protrusion extending outward, and a receiving cavity is provided in the second protrusion for receiving the upper end of the elastic element.
6. The aircraft of claim 2, wherein a plurality of ear seats are spaced apart on the outer peripheral surface of the fixed seat, and each of the ear seats is provided with a first connecting hole.
7. The aircraft according to claim 2, wherein the wing includes a plurality of fixing plates, the fixing plates are disposed at intervals in the interior of the wing along the length direction of the wing, each fixing plate is further provided with a plurality of second connecting holes, one end of the connecting member is integrally connected to the plurality of fixing plates through the second connecting holes, and the other end of the connecting member is inserted into the channel and connected to the locking plate.
8. The aircraft of claim 7, wherein the connecting member comprises a lock pin and a fixing rod, the lock pin has a fastening end and a connecting end at two ends, the fastening end is inserted into the channel and connected to the lock plate, the connecting end is connected to one end of the fixing rod, the other end of the fixing rod is connected to the plurality of fixing plates through the second connecting hole, and when the lock plate is pushed, the lock plate is separated from the fastening end to achieve the effect that the lock pin is detachable from the locking mechanism.
9. The vehicle of claim 8 wherein said locking pin is rod shaped, said snap end is conically configured at an end thereof, said snap end having a peripheral surface with a first annular groove, said locking tab being engaged in said first annular groove.
10. The aircraft of claim 9, wherein the connecting end is provided with a plurality of second annular grooves spaced apart along a length of the connecting end, the fixing rod is a hollow tubular structure, and the connecting end is bonded to the hollow structure of the fixing rod by glue disposed in the second annular grooves.
11. The aircraft of claim 3, wherein a hole is formed in a bottom surface of the fuselage or the wing, the pressing member is located in the hole, and the connecting member is detachable from the latch mechanism when the pressing member is pressed through the hole.
12. The aircraft according to any one of claims 1 to 11, wherein the number of the wings is two, two of the wings are symmetrically disposed on both sides of the fuselage, an end surface of each of the wings close to one end of the fuselage is a first abutting surface, the first abutting surface abuts against a side surface of the fuselage, and the connecting member passes through the first abutting surface for connecting the wings to the fuselage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921690423.5U CN211281437U (en) | 2019-09-30 | 2019-09-30 | Aircraft with a flight control device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921690423.5U CN211281437U (en) | 2019-09-30 | 2019-09-30 | Aircraft with a flight control device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211281437U true CN211281437U (en) | 2020-08-18 |
Family
ID=72025809
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921690423.5U Active CN211281437U (en) | 2019-09-30 | 2019-09-30 | Aircraft with a flight control device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN211281437U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114572417A (en) * | 2022-03-23 | 2022-06-03 | 沃飞长空科技(成都)有限公司 | Quick locking device and aircraft comprising same |
| EP4253227A1 (en) * | 2022-03-28 | 2023-10-04 | Shanghai Autoflight Co., Ltd. | Quick-release wing structure and an unmanned aerial vehicle using the same |
-
2019
- 2019-09-30 CN CN201921690423.5U patent/CN211281437U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114572417A (en) * | 2022-03-23 | 2022-06-03 | 沃飞长空科技(成都)有限公司 | Quick locking device and aircraft comprising same |
| EP4253227A1 (en) * | 2022-03-28 | 2023-10-04 | Shanghai Autoflight Co., Ltd. | Quick-release wing structure and an unmanned aerial vehicle using the same |
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