Improved wing quick-mount structure for model airplane

Abstract

The utility model relates to model technology field especially is a kind of quick mounting structure of improved model wing.The quick mounting structure of improved model wing, including the locking device being arranged in fuselage, the plug-in device being arranged in wing;Locking device includes rebounder, locking piece being arranged in rebounder;First clamping port is set on locking piece;The pressing end of locking piece is stretched out from fuselage;Plug-in device includes lock bar;First clamping port on locking piece can be clamped on lock bar.Lock bar is inserted into locking device, then the pressing end of locking piece is pressed, so that first clamping port on locking piece clamps lock bar, the assembly of fuselage and wing is completed.Fuselage and wing are unlocked, the pressing end of locking piece is pressed again, and locking piece and lock bar are unlocked.Lock bar is clamped by first clamping port of locking piece, so that the stress of lock bar is more balanced and stable, and firmness is better, and there is no problem of loosening.In addition, this design is unlocked or locked by pressing type, and it is more convenient to operate.

Description

Technical Field

[0001] This utility model relates to the field of model aircraft technology, and in particular to an improved quick-assembly structure for model aircraft wings. Background Technology

[0002] Model aircraft is a general term for various aircraft models. It includes model airplanes and other model flying machines. To save space and prevent damage during transportation and packaging, the wings of model aircraft are usually removed before packaging and transport to ensure their safety.

[0003] To quickly detach the wings from the fuselage, a quick-release mechanism is usually used. Some commercially available model airplanes use a hook-and-loop fastener system to assemble the fuselage and wings. Both the fuselage and wings have hooks; during assembly, the hooks on the fuselage and wings engage. However, this hook-and-loop fastening system only applies force to one side, resulting in relatively poor stability.

[0004] For example, Chinese patent application number CN202321074570.6 discloses a quick-release mechanism for the wing of a model airplane. Specifically, it discloses that "a locking block has a ramp on the side opposite to the spring, two locking blocks are symmetrically arranged, and two guide posts have slots on opposite sides for the ramp to engage. During locking block assembly, the spring is sleeved on the locking block's sleeve rod, then the locking block housing is installed, the cover plate is placed, and then screws are used to tighten it. Then, they are installed together into a fixing component and tightened with screws; after the two locking blocks are assembled, they are then installed onto the main wing along with the fixing component." The ramp on the locking block forms the first barb; the slot on the guide post forms the second barb. This design uses barbs to engage the components, but the barb engagement design is unilaterally stressed, resulting in poor stability. Utility Model Content

[0005] In view of this, the present invention addresses the deficiencies of the existing technology and its main purpose is to provide an improved quick-release structure for model aircraft wings. The locking rod is locked by the locking component on the rebound device, which not only distributes the force evenly but also has good firmness, thereby overcoming the shortcomings of the existing technology.

[0006] To achieve the above objectives, the present invention adopts the following technical solution: This application provides an improved quick-install structure for a model aircraft wing, including a locking device disposed on the fuselage and a plug-in device disposed on the wing; the locking device includes a rebound device and a locking member disposed on the rebound device; the locking member is provided with a first latch; the pressing end of the locking member extends from the fuselage and can be pressed; the plug-in device includes a locking rod; the first latch on the locking member can be engaged with the locking rod.

[0007] Preferably, the locking device further includes a first mounting base; a first mounting groove is provided on the machine body; the rebounder is disposed in the first mounting groove; the first mounting base is disposed on the machine body and covers the first mounting groove; a first hole is provided on the first mounting base; the locking rod can extend into the first hole; the pressing end of the locking member extends out from the first mounting base; The locking device further includes a second mounting base; a second mounting groove is provided on the wing; the locking rod is disposed on the base; the base is embedded in the second mounting groove; the second mounting base is disposed close to the wing and covers the second mounting groove; the locking rod extends from the second mounting base.

[0008] Preferably, the fuselage is provided with a third mounting slot; the first mounting base is provided with a female head, which is embedded in the third mounting slot; the wing is provided with a fourth mounting slot; and the second mounting base is provided with a male head, which is embedded in the fourth mounting slot.

[0009] Preferably, the female connector includes a first outer shell and a first terminal module; at least one first channel is provided inside the first outer shell, and a first limiting groove is provided on the first terminal module; the first terminal module is inserted into the first channel, and a first limiting rib on the inner wall of the first channel is embedded in the first limiting groove; The male connector includes a second outer shell and a second terminal module; at least one second channel is provided inside the second outer shell; a first limiting step is provided on the second terminal module; a second limiting step is provided on the inner wall of the second channel; the second terminal module extends out from the second channel, and the second limiting step is blocked on the first limiting step; a spring piece on the second outer shell rests on the second terminal module; The second terminal module is inserted into the first channel, and the first terminal module and the second terminal module are connected.

[0010] Preferably, the second housing includes a main body and a frame; the main body and the frame are integrally formed, and at least two connecting parts are provided between the main body and the frame; the spring extends from the frame and can press against the back of the second terminal module.

[0011] Preferably, a second limiting rib is provided in the first channel, which can block the front end of the second terminal module.

[0012] Preferably, a third limiting rib is provided in the first channel, which can block the front end of the first terminal module.

[0013] Preferably, the first housing is provided with a first mounting ear; a first screw passes through the first mounting ear and fixes the first housing to the fuselage; the second housing is provided with a second mounting ear; a second screw passes through the second mounting ear and fixes the second housing to the wing. Preferably, there are four first channels and four second channels; each first channel contains a first terminal module; and at least one second channel contains a second terminal module.

[0014] Preferably, the length of the first channel is greater than the length of the second channel, and the length of the second terminal module inserted into the first channel is not less than one-third of the length of the first channel.

[0015] This invention has significant advantages and beneficial effects compared with existing technologies. Specifically, as shown in the above technical solution, the rebound device is equipped with a locking component, and the locking component has a first latch. The locking rod extends from the side of the wing. When the wing and fuselage are assembled, the locking rod is inserted into the locking device, and then the pressing end of the locking component is pressed, causing the first latch on the locking component to engage the locking rod, allowing the fuselage and wing to be assembled together. When the fuselage and wing are unlocked, simply pressing the pressing end of the locking component again will move the locking component away from the locking rod, allowing the locking rod to be pulled out of the locking device. Because the first latch engages the locking rod, this design makes the force on the locking rod more balanced and stable, resulting in better stability and eliminating the problem of loosening.

[0016] In addition, this design uses a press-to-unlock mechanism, making it more convenient to operate. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the fuselage and wing separation state according to an embodiment of the present invention.

[0018] Figure 2 This is an exploded view of an embodiment of the present invention.

[0019] Figure 3 This is an exploded view of an embodiment of the present invention.

[0020] Figure 4 This is a schematic diagram showing the state changes of the locking member and locking rod according to an embodiment of this utility model.

[0021] Figure 5 This is a schematic diagram of the connection state of the female and male connectors according to an embodiment of this utility model.

[0022] Figure 6 This is an exploded view of the connector according to an embodiment of the present invention.

[0023] Figure 7 This is a cross-sectional schematic diagram of a connector according to an embodiment of the present invention.

[0024] Figure 8 This is a partial structural schematic diagram of the connector according to an embodiment of the present invention.

[0025] Figure 9 This is a partial structural schematic diagram of the connector according to an embodiment of the present invention.

[0026] Figure 10 This is an exploded view of the connector according to an embodiment of the present invention.

[0027] Figure 11 This is an exploded view of a model aircraft according to an embodiment of this utility model.

[0028] Explanation of reference numerals in the attached diagram: 10. Female connector; 110. First outer shell; 111. First mounting ear; 112. First channel; 114. First limiting rib; 115. Second limiting rib; 117. Third limiting rib; 120. First terminal module; 121. First limiting groove; 20. Male connector; 210. Second outer shell; 211. Second mounting ear; 212. Main body; 213. Connecting part; 214. Frame part; 215. Second channel; 216. Second limiting step; 217. Spring; 220. Second terminal module; 221. First limiting step; 310. Body; 311. Third mounting groove; 312. First mounting groove; 410. Locking device; 411. 412. First mounting base; 413. First hole; 414. Rebound device; 415. Locking element; 416. Pressing end; 417. First bayonet; 518. Wing; 519. Second mounting slot; 510. Fourth mounting slot; 611. Plug-in device; 612. Second mounting base; 613. Locking rod; 614. Second bayonet. Detailed Implementation

[0029] To further illustrate the technical means and effects adopted by this utility model in order to achieve the intended utility model purpose, the following detailed description of the specific implementation methods, structure, features and effects of this utility model is provided in conjunction with the accompanying drawings and preferred embodiments.

[0030] Please refer to Figures 1 to 11 As shown, it illustrates the specific structure of a preferred embodiment of the present invention, which is an improved quick-assembly structure for model aircraft wings.

[0031] During the assembly of the fuselage 310 and wing 510, the first latch 416 of the locking component 414 engages the locking rod 612. This design ensures a more balanced and stable force distribution on the locking rod 612, resulting in better stability and eliminating the possibility of loosening between the locking component 414 and the locking rod 612. Furthermore, this design allows for easy unlocking or locking with a simple press, making operation more convenient.

[0032] This application provides an improved quick-release structure for a model aircraft wing, including a locking device 410 disposed on the fuselage 310 and a connecting device 610 disposed on the wing 510. The locking device 410 includes a rebounder 413 and a locking member 414 disposed on the rebounder 413. The locking member 414 is provided with a first latch 416. The pressing end 415 of the locking member 414 extends from the fuselage 310 and can be pressed. The connecting device 610 includes a locking rod 612. The first latch 416 on the locking member 414 can be engaged with the locking rod 612. The rebounder 413 is a hardware component that can be popped out by pressing and retracted by pressing again. In this embodiment, the rebounder 413 can be a spring-type rebounder 413. The locking member 414 can be connected to the driving end of the rebounder 413 by threading, welding, or crimping; the locking member 414 can also be integrally formed with the driving end of the rebounder 413. The rebound mechanism 413 drives the locking member 414 to move up and down. The locking lever 612 has a ring-shaped second latch 613. When the rebound mechanism 413 retracts, the locking member 414 moves upward, and the first latch 416 on the locking member 414 engages with the second latch 613 on the locking lever 612. This locks the locking member 414 and the locking lever 612 together, resulting in more even force distribution, a more robust structure, and preventing loosening. When unlocking is required, simply press the pressing end 415 of the locking member 414, and the rebound mechanism 413 will pop out, separating the locking member 414 and the locking lever 612. At this point, the fuselage 310 and the wing 510 can be separated. Therefore, this quick-release structure is simpler and more convenient to operate than the barbed hook structure in the prior art. Furthermore, Preferably, the locking device 410 further includes a first mounting base 411; a first mounting groove 312 is provided on the body 310; the rebounder 413 is disposed in the first mounting groove 312; the first mounting base 411 is disposed on the body 310 and covers the first mounting groove 312; a first hole 412 is provided on the first mounting base 411; the locking rod 612 can extend into the first hole 412; the pressing end 415 of the locking member 414 extends from the bottom of the first mounting base 411. The rebounder 413 can be screwed into the first mounting groove 312, which can improve the stress strength at the connection position and provide better load-bearing capacity. After the rebound device 413 and the locking member 414 are assembled into the first mounting groove 312, the contoured first mounting base 411 covers the first mounting groove 312. The first mounting base 411 is provided with a first hole 412 to allow the locking rod 612 to extend into the locking member 414, so that the locking member 414 can lock the locking rod 612. The pressing end 415 of the locking member 414 extends from the first mounting base 411. By pressing the pressing end 415 of the locking member 414, unlocking or locking can be achieved, which is very convenient to operate.

[0033] The locking device 410 further includes a second mounting base 611; a second mounting groove 511 is provided on the wing 510; the locking rod 612 is disposed on the base; the base is embedded in the second mounting groove 511; the second mounting base 611 is tightly disposed on the wing 510 and covers the second mounting groove 511; the locking rod 612 extends from the second mounting base 611. The locking rod 612 can be mounted on the base by screws or integrally formed with the base. During assembly, the locking rod 612 is fixed to the base by screws, and then the base is inserted into the second mounting groove 511 from bottom to top. Then, the second mounting groove 511 is covered by the contoured second mounting base 611, while the locking rod 612 protrudes from the second mounting base 611. This design can increase the load-bearing capacity of the wing 510 and also facilitate the locking of the locking rod 612 with the locking member 414. The first mounting base 411 and the second mounting base 611 can be assembled using screws.

[0034] Preferably, the fuselage 310 is provided with a third mounting groove 311; the first mounting base 411 is provided with a female connector 10, which is embedded in the third mounting groove 311; the wing 510 is provided with a fourth mounting groove 512; and the second mounting base 611 is provided with a male connector 20, which is embedded in the fourth mounting groove 512. The connector includes a male connector 20 and a female connector 10. During assembly, the female connector 10 is embedded in the third mounting groove 311, and then the female connector 10 is fixed to the first mounting base 411 with screws. The male connector 20 is embedded in the fourth mounting groove 512, and then the male connector 20 is fixed to the second mounting base 611 with screws. This assembly method is very simple and convenient.

[0035] Preferably, the female connector 10 includes a first outer shell 110 and a first terminal module 120; the first outer shell 110 has at least one first channel 112, and the first terminal module 120 has a first limiting groove 121; the first terminal module 120 is inserted into the first channel 112, and the first limiting rib 114 on the inner wall of the first channel 112 is embedded in the first limiting groove 121; the male connector 20 includes a second outer shell 210 and a second terminal module 220; the second outer shell 210 has at least one second channel 215; the second terminal module 220 has a first limiting step 221; the inner wall of the second channel 215 has a second limiting step 216; the second terminal module 220 extends out of the second channel 215, and the second limiting step blocks the first limiting step 221; a spring piece on the second outer shell 210 abuts against the second terminal module 220; the second terminal module 220 is inserted into the first channel 112, and the first terminal module 120 and the second terminal module 220 are connected. The first outer shell 110 and the second outer shell 210 are preferably insulating shells, manufactured using injection molding. The first outer shell 110 has two or more first channels 112, or it can have only one. The second outer shell 210 has two or more second channels 215, or it can have only one. In this embodiment, there are four first channels 112 and four second channels 215. Therefore, four first terminal modules 120 can be inserted into the first outer shell, and four terminal modules can also be inserted into the second outer shell. During assembly, the first terminal modules 120 can be inserted into all four first channels 112 firstly, and the second terminal modules 220 can be installed in the second channels 215 as needed. This assembly method is just one example; the specific method can be determined according to requirements.

[0036] When the first terminal module 120 is inserted into the first channel 112, the first limiting rib 114 provided on the inner wall of the first channel 112 is embedded into the first limiting groove 121 on the first terminal module 120, so that the first terminal module 120 is fixed in the first channel 112 and will not loosen. When the second terminal module 220 passes through the second channel 215, the second limiting step 216 blocks the first limiting step 221, and the spring piece 217 on the second housing 210 abuts against the second terminal module 220, so that the second terminal module 220 is fixed in the second channel 215. It can be seen that the assembly method of the second terminal module 220 is very simple and efficient. When the second terminal module 220 is inserted into the first channel 112, the first terminal module and the second terminal module 220 can conduct electricity.

[0037] Preferably, the second outer casing 210 includes a main body 212 and a frame 214; the main body 212 and the frame 214 are integrally formed, and at least two connecting portions 213 are provided between the main body 212 and the frame 214; the spring piece 217 extends from the frame 214 and can abut against the back of the second terminal module 220. The spring piece 217 is inclined inward and can abut against the back of the second terminal module 220, thus confining the second terminal module 220 within the second channel 215. The spring piece 217 can abut against one second terminal module 220 or simultaneously fix multiple second terminal modules 220. The gap between the main body 212 and the frame 214 allows the spring clip 217 to be easily moved by hand or with a screwdriver. This releases the back of the second terminal module 220, allowing it to exit the second channel 215. Therefore, disassembling the second terminal module 220 is very convenient. Conversely, simply pushing the second terminal module 220 into the second channel 215 will cause the spring clip 217 to automatically press against the back of the module. This assembly structure is very simple and efficient.

[0038] Specifically, the frame portion 214 has a frame-like structure, and at least two connecting portions 213 connect the frame portion 214 to the main body portion 212. The frame portion 214 and the main body portion 212 are injection molded into a single unit, and the connecting portions 213 are plate-shaped. In this embodiment, the frame portion 214 and the main body portion 212 are connected by three connecting portions 213, which enhances the strength of the connection between the frame portion 214 and the main body portion 212.

[0039] Preferably, a second limiting rib 115 is provided within the first channel 112, which can stop the front end of the second terminal module 220. The second limiting rib 115 can control the insertion depth of the second terminal module 220 in the first channel 112, ensuring that the second terminal module 220 is inserted in place. The first terminal module 120 is provided with a first chamfer 123, which can provide clearance for the second limiting rib 115.

[0040] Preferably, a third limiting rib 117 is provided within the first channel 112, which can stop the front end of the first terminal module 120. The third limiting rib 117 can control the position of the first terminal module 120 within the first channel 112. The second terminal module 220 is provided with a second chamfer 223, which can provide clearance for the third limiting rib 117. The third limiting step 124 on the first terminal module 120 also provides positioning for the first terminal module 120.

[0041] Preferably, the first housing 110 is provided with a first mounting ear 111; a first screw passes through the first mounting ear 111 and fixes the first housing 110 to the first mounting base 411; the second housing 210 is provided with a second mounting ear 211; a second screw passes through the second mounting ear 211 and fixes the second housing 210 to the second mounting base 611. The first mounting ear 111 is inserted into the first mounting base 411 and then fixed to the first mounting base 411 with a screw; the second mounting ear 211 is inserted into the second mounting base 611 and then fixed to the second mounting base 611 with a screw. It can be seen that the assembly of the connector is very simple and efficient.

[0042] Preferably, there are four first channels 112 and two channels 215; each first channel 112 contains a first terminal module 120; and at least one second channel 215 contains a second terminal module 220. Preferably, all first channels 112 contain first terminal modules 120, and the second channels 215 can be used to insert second terminal modules 220 as needed. This design is very flexible and facilitates the upgrading and optimization of the wing 510.

[0043] Preferably, the length of the first channel 111 is greater than the length of the second channel 215, and the length of the second terminal module 220 inserted into the first channel 112 is not less than one-third of the length of the first channel 112. This design can improve the rigidity between the first outer shell 110 and the second outer shell 210, and improve the bending resistance of the connection between the wing 510 and the fuselage 310.

[0044] In summary, the key design feature of this invention lies in the locking element 414 on the rebound device 413, which has a first latch 416. The locking rod 612 extends from the side of the wing 510. When assembling the wing 510 and fuselage 310, the locking rod 612 is inserted into the locking device 410, and then the pressing end 415 of the locking element 414 is pressed, causing the first latch 416 on the locking element 414 to engage the locking rod 612, allowing the fuselage 310 and wing 510 to be assembled together. To unlock, simply press the pressing end 415 of the locking element 414 again, and the locking element 414 will move away from the locking rod 612, allowing the locking rod 612 to be withdrawn from the locking device 410. This design makes the force on the locking rod 612 more balanced and stable, with better stability and no risk of loosening; it also makes operation more convenient.

[0045] The above description is merely a preferred embodiment of the present utility model and is not intended to limit the present utility model in any way. Although the present utility model has been disclosed above with reference to a preferred embodiment, it is not intended to limit the present utility model. Any person skilled in the art can make some modifications or alterations to the above-disclosed technical content to create equivalent embodiments without departing from the scope of the present utility model. Any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present utility model without departing from the scope of the present utility model shall still fall within the scope of the present utility model.

Claims

1. An improved quick-assembly structure for model aircraft wings, characterized in that: Includes a locking device (410) installed on the fuselage (310) and a plug-in device (610) installed on the wing (510). The locking device (410) includes a rebounder (413) and a locking member (414) disposed on the rebounder (413); the locking member (414) is provided with a first bayonet (416); the pressing end (415) of the locking member (414) extends from the body (310) and can be pressed; The plug-in device (610) includes a locking bar (612); a first latch (416) on the locking member (414) can be engaged with the locking bar (612).

2. The quick-mounting structure of a model airplane wing according to claim 1, characterized in that: The locking device (410) further includes a first mounting base (411); a first mounting groove (312) is provided on the body (310); the rebounder (413) is disposed in the first mounting groove (312); the first mounting base (411) is disposed on the body (310) and covers the first mounting groove (312); a first hole (412) is provided on the first mounting base (411); the locking rod (612) can extend into the first hole (412); the pressing end (415) of the locking member (414) extends out from the first mounting base (411); The locking device (410) further includes a second mounting base (611); a second mounting groove (511) is provided on the wing (510); the locking rod (612) is provided on the base; the base is embedded in the second mounting groove (511); the second mounting base (611) is closely attached to the wing (510) and covers the second mounting groove (511); the locking rod (612) extends out from the second mounting base (611).

3. The quick-mounting structure of a model airplane wing according to claim 2, characterized in that: The fuselage (310) is provided with a third mounting groove (311); the first mounting base (411) is provided with a female head (10), and the female head (10) is embedded in the third mounting groove (311); The wing (510) is provided with a fourth mounting slot (512); the second mounting base (611) is provided with a male head (20), and the male head (20) is embedded in the fourth mounting slot (512).

4. The quick-mounting structure of a model airplane wing according to claim 3, characterized in that: The female connector (10) includes a first outer shell (110) and a first terminal module (120); at least one first channel (112) is provided inside the first outer shell (110), and a first limiting groove (121) is provided on the first terminal module (120); the first terminal module (120) is inserted into the first channel (112), and a first limiting rib (114) on the inner wall of the first channel (112) is embedded in the first limiting groove (121); The male connector (20) includes a second outer shell (210) and a second terminal module (220); at least one second channel (215) is provided inside the second outer shell (210); a first limiting step (221) is provided on the second terminal module (220); a second limiting step (216) is provided on the inner wall of the second channel (215); the second terminal module (220) extends out from the second channel (215), and the second limiting step (216) blocks the first limiting step (221); a spring piece (217) on the second outer shell (210) abuts against the second terminal module (220); The second terminal module (220) is inserted into the first channel (112), and the first terminal module (120) and the second terminal module (220) are connected.

5. The quick-mounting structure of a model airplane wing according to claim 4, characterized in that: The second outer shell (210) includes a main body (212) and a frame (214); the main body (212) and the frame (214) are integrally formed, and at least two connecting parts (213) are provided between the main body (212) and the frame (214); the spring piece (217) extends out from the frame (214) and can press against the back of the second terminal module (220).

6. The quick-mounting structure of a model airplane wing according to claim 4, characterized in that: The first channel (112) is provided with a second limiting rib (115), which can block the front end of the second terminal module (220).

7. The quick-mounting structure of a model aircraft wing according to claim 4 or 6, characterized in that: The first channel (112) is provided with a third limiting rib (117), which can block the front end of the first terminal module (120).

8. The quick-mounting structure of a model airplane wing according to claim 4, characterized in that: The first housing (110) is provided with a first mounting ear (111); a first screw passes through the first mounting ear (111) and fixes the first housing (110) to the body (310); The second housing (210) is provided with a second mounting ear (211); the second screw passes through the second mounting ear (211) and fixes the second housing (210) to the wing (510).

9. The quick-mounting structure of a model airplane wing according to claim 4, characterized in that: There are four first channels (112) and two channels (215); each first channel (112) contains a first terminal module (120); and at least one second channel (215) contains a second terminal module (220).

10. The quick-mounting structure of a model airplane wing according to claim 4, characterized in that: The length of the first channel (112) is greater than the length of the second channel (215), and the length of the second terminal module (220) inserted into the first channel (112) is not less than one-third of the length of the first channel (112).

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