Quick disassembly and assembly structure for main wing and fuselage of model airplane
By plugging in the latch and the return spring, combined with the positioning column and mortise and tenon connection, the problems of low efficiency in disassembly and assembly of the model aircraft and easy falling off of screws are solved, achieving efficient and stable assembly and flight performance of the model aircraft.
Patent Information
- Application Number
- CN202422262906.2
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-09-14
- Publication Date
- 2025-10-03
- Estimated Expiration
- 2034-09-14
AI Technical Summary
The existing aircraft model disassembly and assembly technology is inefficient, and screws are prone to slipping and loss, affecting the flight stability of the aircraft model.
It uses a plug-in method with a pin and a return spring. Insert the wing plug into the fixing hole, rotate the pin to align the pin with the pin hole, press the pin through the hole and rotate it ninety degrees to complete the installation. When disassembling, the operation is reversed. It replaces the traditional screw fixation and combines the positioning column and mortise and tenon connection to improve stability.
It improves the efficiency of disassembly and assembly, avoids the problem of screw falling off, ensures the stability and bearing capacity of each structure after the model aircraft is assembled, and enhances the flight stability and service life of the model aircraft.
Smart Images
Figure CN223404401U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of disassembly and assembly of a main wing and a fuselage of a model aircraft, in particular to a structure for quickly disassembling and assembling a main wing and a fuselage of a model aircraft. Background Art
[0002] With the vigorous development of China's aerospace industry, more and more people have begun to participate in the learning and experience of model aircraft and drones. However, due to the large size of medium and large model aircraft, the fuselage and main wings are generally not made into a whole and need to be assembled before flight. The existing model aircraft disassembly and assembly technology on the market generally uses screw fixing. This method requires matching corresponding disassembly and assembly tools. The disassembly and assembly process is slow due to the large number of parts. In addition, the screws are prone to stripping after a large number of disassembly and assembly times. Once the screws are lost, it will affect the assembly of the model aircraft, resulting in reduced stability during flight. Utility Model Content
[0003] The purpose of the utility model is to provide a structure for quickly disassembling and assembling the main wing and fuselage of a model aircraft, so as to solve the problems raised in the above-mentioned background technology.
[0004] To achieve the above-mentioned objectives, the present invention provides the following technical solutions: a quick disassembly and assembly structure of a model aircraft main wing and fuselage, comprising a fuselage structural member, a fixing hole being provided on one side of the fuselage structural member, a first latch hole being provided on the upper surface of the fuselage structural member, a disassembly and assembly structure being installed on the upper surface of the fuselage structural member, the disassembly and assembly structure comprising a base pressed on the upper surface of the fuselage structural member, a screw threadedly connected to the base and the fuselage structural member, a latch inserted in the center of the base, a return spring inserted on the outer wall of the latch, and a pin inserted at one end of the latch, the main wing structure being inserted into the interior of the fixing hole, the main wing structure comprising a wing plug inserted into the interior of the fixing hole and a second latch hole provided on the upper surface of the wing plug, the latch body passing through the first latch hole and the second latch hole.
[0005] By adopting the above technical solution, the wing plug is inserted into the fixing hole, the pin is rotated so that the pin is in the same direction as the first pin hole, and the pin is pressed through the first pin hole and the second pin hole. After pressing into place, the pin is rotated 90 degrees to make the pin resist and complete the installation. The above steps are reversed and the device can be disassembled. This device replaces the traditional screw fixing method, does not require tool-assisted installation, is easy to carry, and improves efficiency in assembly and disassembly. The plug-in method avoids the problem of screw falling off caused by multiple disassembly and assembly in the existing technology, thereby improving the stability of the model aircraft during flight.
[0006] Preferably, a positioning hole is opened on one side of the fuselage structural member, one end of the wing plug is fixedly connected to the wing structural member, one side of the wing structural member is fixedly connected to a positioning column, and the positioning column is inserted into the positioning hole.
[0007] By adopting the above technical solution, by using the positioning columns on the wing structural parts to be inserted into the positioning holes, precise positioning can be provided between the wing structural parts and the fuselage structural parts to ensure the stable flight attitude of the assembled model aircraft.
[0008] Preferably, two positioning columns are fixedly connected to one side of the wing structure, the wing plug is located in the middle of the two positioning columns, and one end of the positioning column is provided with a mortise that can be fitted and connected with the tenon in the positioning hole.
[0009] By adopting the above technical solution, by setting a symmetrical positioning column with the wing plug as the center on one side of the wing structure, the position can be positioned from both ends after plugging and fixing, and the mortise and tenon connection between the plug-in wing plug and the positioning hole can improve the plug-in stability, so that the two ends of the wing structure are evenly stressed after being fixed, so as to ensure that the various structures have good bearing capacity after the model aircraft is assembled.
[0010] Preferably, the direction of the insertion hole on the base is perpendicular to the directions of the first insertion hole and the second insertion hole, and after the wing plug is plugged in, the second insertion hole and the first insertion hole overlap with each other.
[0011] By adopting the above technical solution, by setting the direction of the socket on the base, after the base, the pin and the return spring are assembled, it can be perpendicular to the direction of the first pin hole. When the wing structure is disassembled, the rotating pin needs to make the pin coincide with the first pin hole and the second pin hole. From then on, under the elastic force of the return spring, the pin body can be lifted out of the wing plug, and the pin will be blocked by the socket of the base to avoid being ejected by the elastic force of the return spring.
[0012] Preferably, the fuselage structural parts and the wing structural parts are plastic parts, and the base, screws, latches, return springs and pins are metal parts.
[0013] By adopting the above technical solution, plastic parts are used to form the fuselage structural parts and wing structural parts. The plastic parts are designed to be lightweight and have certain elasticity and wear resistance to ensure that good connection performance can be maintained after multiple disassembly and assembly. Metal parts constitute the disassembly and assembly structure. The metal parts have the characteristics of high strength and wear resistance, which can achieve a stable connection between the wing body and the fuselage body of the model aircraft.
[0014] Preferably, the return spring is located between the upper surface of the base and the top of the latch, and the return spring is in a compressed state.
[0015] By adopting the above technical solution, a certain upward thrust can be applied to the pin by utilizing the compressed return spring. After the wing plug is installed, the pin can be pressed against the bottom of the fuselage structure to prevent it from slipping. When it is removed, it can be quickly bounced onto the base, making it convenient to quickly remove the wing structure.
[0016] Preferably, one side of the wing structural component is fixedly connected to the wing main body, and the outside of the fuselage structural component is fixedly connected to the fuselage main body.
[0017] By adopting the above technical solution, by separately connecting the wing structural parts to the wing main body and separately connecting the fuselage structural parts to the fuselage main body, the wing main body and the fuselage main body can be replaced after being damaged, thereby increasing the service life of the wing structural parts and the fuselage structural parts for the model aircraft.
[0018] Compared with the prior art, the beneficial effects of the present invention are:
[0019] (1) Insert the wing plug into the fixing hole, rotate the pin so that the pin is in the same direction as the first pin hole, press the pin through the first pin hole and the second pin hole, and rotate the pin 90 degrees after pressing it into place so that the pin is against the installation to complete the installation. The above steps can be reversed to complete the disassembly. This device replaces the traditional screw fixing method, does not require tool-assisted installation, is easy to carry, and improves the efficiency of assembly and disassembly. The plug-in method avoids the problem of screw falling off caused by multiple disassembly and assembly in the existing technology, thereby improving the stability of the aircraft model during flight.
[0020] (2) By setting a symmetrical positioning column with the wing plug as the center on one side of the wing structure, the position can be positioned from both ends after plugging and fixing, and the mortise and tenon connection between the plug-in wing plug and the positioning hole can improve the plug-in stability, so that the two ends of the wing structure are evenly stressed after the wing structure is fixed, so as to ensure that the various structures have good bearing capacity after the model aircraft is assembled. BRIEF DESCRIPTION OF THE DRAWINGS
[0021] Figure 1 This is an exploded view of the overall structure of the device of the present utility model;
[0022] Figure 2 This is a schematic diagram of the connection between the aircraft body and the wings of the present invention;
[0023] Figure 3 It is a schematic diagram of the fuselage structural parts of the present utility model;
[0024] Figure 4 This is a schematic diagram of the main wing structure of the present utility model;
[0025] Figure 5 This is an exploded view of the disassembly and assembly structure of the utility model;
[0026] Figure 6 This is a bottom view of the connection between the disassembly and assembly structure of the utility model and the fuselage structure;
[0027] Figure 7 This is a front view of the connection between the disassembly and assembly structure of the utility model and the fuselage structural parts.
[0028] In the figure: 1. Fuselage structure; 2. Fixing hole; 3. First latch hole; 4. Disassembly and assembly structure; 401. Base; 402. Screw; 403. Latch; 404. Return spring; 405. Pin; 5. Positioning hole; 6. Main wing structure; 601. Wing structure; 602. Wing plug; 603. Second latch hole; 604. Positioning column; 7. Fuselage body; 8. Wing body. DETAILED DESCRIPTION
[0029] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.
[0030] The following is combined with Figure 1-7 The utility model is described in further detail.
[0031] Example 1
[0032] See also Figures 1 to 7 The utility model provides an embodiment: a rapid disassembly structure of the main wing and fuselage of a model aircraft, comprising a fuselage structure 1, a fixing hole 2 is opened on one side of the fuselage structure 1, a first latch hole 3 is opened on the upper surface of the fuselage structure 1, a disassembly structure 4 is installed on the upper surface of the fuselage structure 1, the disassembly structure 4 includes a base 401 pressed on the upper surface of the fuselage structure 1, a screw 402 threadedly connected to the base 401 and the fuselage structure 1, a latch 403 inserted in the center of the base 401, a return spring 404 inserted on the outer wall of the latch 403 and a pin 405 inserted at one end of the latch 403, the fixing hole 2 is plugged into the main wing structure 6, the main wing structure 6 includes a wing plug 602 plugged into the fixing hole 2 and an opening A second latch hole 603 is provided on the upper surface of the wing plug 602, and the main body of the latch 403 passes through the first latch hole 3 and the second latch hole 603. By inserting the wing plug 602 into the fixing hole 2, the latch 403 is rotated so that the pin 405 is in the same direction as the first latch hole 3. After pressing the latch 403 through the first latch hole 3 and the second latch hole 603, after pressing into place, the latch 403 is rotated ninety degrees so that the pin 405 is against the installation to complete. The above steps can be reversed to complete the disassembly. This device replaces the traditional screw fixing method, does not require tool-assisted installation, is easy to carry, and improves the efficiency of disassembly and assembly. The use of plug-in method avoids the problem of screw falling off caused by multiple disassembly and assembly in the existing technology, thereby improving the stability of the model aircraft during flight.
[0033] Example 2
[0034] See also Figures 1 to 7, the direction of the insertion hole on the base 401 is perpendicular to the directions of the first latch hole 3 and the second latch hole 603. After the wing plug 602 is plugged in, the second latch hole 603 coincides with the first latch hole 3. By setting the direction of the insertion hole on the base 401, after the base 401, the latch 403, and the return spring 404 are assembled, it can be perpendicular to the direction of the first latch hole 3. When the wing structure 601 is disassembled, the latch 403 needs to be rotated so that the pin 405 coincides with the first latch hole 3 and the second latch hole 603. When the latch 403 is opened, under the elastic force of the return spring 404, the main body of the latch 403 can be lifted out of the wing plug 602, and the pin 405 will be blocked by the insertion hole of the base 401 to prevent the latch 403 from being ejected by the elastic force of the return spring 404;
[0035] A positioning hole 5 is provided on one side of the fuselage structure 1, one end of the wing plug 602 is fixedly connected to the wing structure 601, and a positioning post 604 is fixedly connected to one side of the wing structure 601. The positioning post 604 is plugged into the positioning hole 5. By plugging the positioning post 604 on the wing structure 601 into the positioning hole 5, the wing structure 601 and the fuselage structure 1 can be accurately positioned to ensure the stability of the flight attitude of the assembled aircraft model. One side of the wing structure 601 is fixedly connected to two positioning posts 604. The wing plug 602 is located in the middle of the two positioning columns 604. A mortise is provided at one end of the positioning column 604, which can be fitted with the tenon in the positioning hole 5. By setting a symmetrical positioning column 604 with the wing plug 602 as the center on one side of the wing structure 601, the position can be positioned from both ends after plugging and fixing. The mortise and tenon connection between the wing plug 602 and the positioning hole 5 can improve the plug-in stability, so that the two ends of the wing structure 601 are evenly stressed after being fixed, so as to ensure that the various structures have good bearing capacity after the model aircraft is assembled.
[0036] Example 3
[0037] See also Figures 1 to 7 The fuselage structure 1 and the wing structure 601 are plastic parts, and the base 401, screw 402, latch 403, return spring 404 and pin 405 are metal parts. By using plastic parts to form the fuselage structure 1 and the wing structure 601, the plastic parts are designed to be lightweight and have certain elasticity and wear resistance to ensure that they can still maintain good connection performance after multiple disassembly and assembly. The metal parts constitute the disassembly and assembly structure 4. The metal parts have the characteristics of high strength and wear resistance, which can achieve a stable connection between the wing body 8 and the fuselage body 7 of the model aircraft;
[0038] The return spring 404 is located between the upper surface of the base 401 and the top of the pin 403, and the return spring 404 is in a compressed state. By utilizing the compressed return spring 404, a certain upward thrust can be applied to the pin 403. After installing the wing plug 602, the pin 405 can be pressed against the bottom of the fuselage structure 1 to prevent slipping. When removed, it can be quickly bounced onto the base 401, which is convenient for quickly removing the wing structure 601. One side of the wing structure 601 is fixedly connected to the wing body 8, and the outside of the fuselage structure 1 is fixedly connected to the fuselage body 7. By adopting the separate connection between the wing structure 601 and the wing body 8 and the separate connection between the fuselage structure 1 and the fuselage body 7, the wing body 8 and the fuselage body 7 can be replaced after damage, thereby improving the service life of the wing structure 601 and the fuselage structure 1 for the model aircraft.
[0039] Working principle: When in use, the disassembly and assembly structure 4 is pre-installed on the fuselage structure 1. When installing, the wing plug 602 and the positioning column 604 are respectively inserted into the fixing hole 2 and the positioning hole 5. After rotating the latch 403 until the pin 405 coincides with the first latch hole 3, press the latch 403 through the wing plug 602 to the bottom, and then rotate the latch 403 until the pin 405 rests on the bottom of the fuselage structure 1 to complete the installation. When disassembling, rotate the latch 403 until the pin 405 coincides with the first latch hole 3, release the latch 403, and it will be quickly lifted up and separated from the wing plug 602 under the thrust of the return spring 404. At this time, pull out the wing plug 602 to complete the disassembly.
[0040] It is obvious to those skilled in the art that the present invention is not limited to the details of the above exemplary embodiments, and that the present invention can be implemented in other specific forms without departing from the spirit or basic characteristics of the present invention.
Claims
1. A structure for quickly disassembling and assembling a main wing and a fuselage of a model aircraft, comprising a fuselage structural member (1), characterized in that: A fixing hole (2) is provided on one side of the fuselage structural member (1), a first latch hole (3) is provided on the upper surface of the fuselage structural member (1), and a disassembly structure (4) is installed on the upper surface of the fuselage structural member (1), the disassembly structure (4) comprising a base (401) pressed on the upper surface of the fuselage structural member (1), a screw (402) threadedly connected to the base (401) and the fuselage structural member (1), a latch (403) inserted in the center of the base (401), A return spring (404) is inserted on the outer wall of the latch (403) and a pin (405) is inserted at one end of the latch (403). A main wing structure (6) is inserted into the interior of the fixing hole (2). The main wing structure (6) includes a wing plug (602) inserted into the interior of the fixing hole (2) and a second latch hole (603) provided on the upper surface of the wing plug (602). The main body of the latch (403) passes through the first latch hole (3) and the second latch hole (603).
2. The structure for quickly disassembling the main wing and fuselage of a model aircraft according to claim 1, characterized in that: A positioning hole (5) is provided on one side of the fuselage structural member (1); one end of the wing plug (602) is fixedly connected to the wing structural member (601); a positioning column (604) is fixedly connected to one side of the wing structural member (601); and the positioning column (604) is plugged into the positioning hole (5).
3. The structure for quickly disassembling the main wing and fuselage of a model aircraft according to claim 2, characterized in that: Two positioning posts (604) are fixedly connected to one side of the wing structure (601), and the wing plug (602) is located in the middle of the two positioning posts (604). One end of the positioning post (604) is provided with a mortise that can be connected with the tenon in the positioning hole (5).
4. The structure for quickly disassembling the main wing and fuselage of a model aircraft according to claim 1, characterized in that: The direction of the insertion hole on the base (401) is perpendicular to the direction of the first insertion hole (3) and the second insertion hole (603). After the wing plug (602) is plugged in, the second insertion hole (603) and the first insertion hole (3) overlap with each other.
5. The structure for quickly disassembling and assembling the main wing and fuselage of a model aircraft according to claim 1, characterized in that: The fuselage structural component (1) and the wing structural component (601) are plastic components, and the base (401), screw (402), latch (403), return spring (404) and pin (405) are metal components.
6. The structure for quickly disassembling the main wing and fuselage of a model aircraft according to claim 1, characterized in that: The return spring (404) is located between the upper surface of the base (401) and the top of the latch (403), and the return spring (404) is in a compressed state.
7. The structure for quickly disassembling the main wing and fuselage of a model aircraft according to claim 2, characterized in that: One side of the wing structure (601) is fixedly connected to the wing body (8), and the outside of the fuselage structure (1) is fixedly connected to the fuselage body (7).