CN108031129B - Butt joint grafting structure of fuselage and wing convenient to dismouting - Google Patents
Butt joint grafting structure of fuselage and wing convenient to dismouting Download PDFInfo
- Publication number
- CN108031129B CN108031129B CN201711366452.1A CN201711366452A CN108031129B CN 108031129 B CN108031129 B CN 108031129B CN 201711366452 A CN201711366452 A CN 201711366452A CN 108031129 B CN108031129 B CN 108031129B
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- wing
- clamping
- fuselage
- butt
- docking
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- 210000001503 joint Anatomy 0.000 title claims description 38
- 238000003032 molecular docking Methods 0.000 claims abstract description 43
- 238000005452 bending Methods 0.000 claims description 7
- 238000009434 installation Methods 0.000 claims description 7
- 239000011324 bead Substances 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 1
- 238000004026 adhesive bonding Methods 0.000 description 1
- 238000012258 culturing Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
Classifications
-
- A—HUMAN NECESSITIES
- A63—SPORTS; GAMES; AMUSEMENTS
- A63H—TOYS, e.g. TOPS, DOLLS, HOOPS OR BUILDING BLOCKS
- A63H27/00—Toy aircraft; Other flying toys
- A63H27/02—Model aircraft
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- Seats For Vehicles (AREA)
- Toys (AREA)
Abstract
The invention relates to the technical field of aeromodels, and discloses a docking and plugging structure of a fuselage and a wing, which is convenient to disassemble and assemble. The wing-mounted type wing-mounted device is simple in structural arrangement, easy to mount and dismount, convenient to carry and convenient to maintain after the wings are damaged.
Description
Technical Field
The invention relates to the technical field of aeromodels, in particular to a butt joint splicing structure of a fuselage and a wing, which is convenient to disassemble and assemble.
Background
The aeromodel is used for popularizing aeroknowledge and culturing aeronautical science and technology talents, and with the development of science and technology, the aeromodel can be used as a practical aerial photographing tool or an aeromodel capable of flying gradually, so that the fixation of wings and a fuselage becomes extremely important.
In the existing fixing mode of the fuselage and the wing, the corresponding butt joint structure is installed on the connecting component to be fastened by screws or buckles so as to realize butt joint, or the butt joint is directly bonded by glue, and the butt joint mode is simple and easy to operate.
However, in the existing butt joint modes, the screw locked by the screw is easy to loosen in vibration, the fastening performance of the buckle is not firm, more parts are involved in the two modes, the butt joint is complex, and the fuselage and the wing are fixed by a glue bonding connection mode, so that the disassembly is inconvenient, and inconvenience is caused to carrying and maintenance of the aeromodel.
Disclosure of Invention
The invention provides a butt joint splicing structure of a fuselage and a wing, which is convenient to disassemble and assemble, and aims to solve the problems that the connection between the fuselage and the wing of an aeromodel is unstable and is not easy to carry and maintain in the prior art.
The invention is realized in such a way that the docking and grafting structure of the fuselage and the wing which are convenient to disassemble and assemble comprises a fuselage fixing seat and a wing connecting seat which is docked with the fuselage fixing seat, wherein the fuselage fixing seat is provided with a fuselage docking surface which is docked with the wing connecting seat, and the wing connecting seat is provided with a wing docking surface which is docked with the fuselage; the wing butt joint surface is convexly provided with a clamping column embedded in the clamping groove, the clamping column extends towards the body butt joint surface, and the front end of the clamping column is provided with a clamping hook extending towards the side; a butt-joint sliding block for clamping the clamping hook is arranged in the machine body fixing seat, and the butt-joint sliding block is movably arranged in the clamping groove; and the butt-joint sliding block is enabled to clamp the clamping hook or be separated from the clamping hook by moving the butt-joint sliding block.
Further, the top of the body fixing seat is provided with a mounting groove, the bottom of the mounting groove is provided with a mounting opening communicated with the clamping groove, and the butt-joint sliding block penetrates through the mounting opening and is arranged in the clamping groove.
Further, the butt joint sliding block is provided with a convex edge which is abutted with the clamping hook, the convex edge is provided with a convex edge inner end face which is away from the wing, the clamping hook is provided with a bending face which faces the wing, and the convex edge inner end face is abutted with the bending face to limit outward movement of the clamping column.
Further, the butt joint sliding block comprises a movable block body, the side wall of the movable block body is extended to form the convex rib, a reset spring is arranged between the side walls of the convex rib and the clamping groove, and the reset spring drives the butt joint sliding block to move towards the extending direction of the convex rib.
Further, the other side wall of the moving block has a slider spring groove in which the return spring is embedded.
Further, the rib has an outer end surface facing away from the moving block, and the outer end surface of the rib is obliquely arranged.
Further, a limiting block is convexly arranged on the upper portion of the butt joint sliding block, and the limiting block upwards extends out of the top of the machine body fixing seat.
Further, a sliding block fixing plate is arranged in the mounting groove, a limiting opening for limiting the movement of the limiting block is formed in the sliding block fixing plate, the limiting block penetrates through the limiting opening of the sliding fixing plate, and when the limiting block abuts against the side end of the limiting opening, the abutting sliding block limits the outward movement of the clamping hook
Further, the inner side and the outer side of the clamping groove are provided with clamping groove walls for limiting the moving direction of the butt joint sliding block.
Compared with the prior art, the butt joint grafting structure of the fuselage and the wing convenient to disassemble and assemble provided by the invention has the advantages that through the structural arrangement, when the clamping columns are embedded into the clamping grooves, the butt joint surface of the fuselage is abutted against the butt joint surface of the wing, the butt joint sliding blocks of the fuselage fixing seat prevent the hooks of the wing connecting seat from moving outwards, so that stable connection between the fuselage and the wing is realized, when the butt joint sliding blocks are moved, the hooks are separated from the butt joint sliding blocks, the clamping columns are separated from the clamping grooves, and therefore, the disassembly between the wing and the fuselage is realized. The problems that the connection between a fuselage and a wing of an aeromodel in the prior art is unstable and the aeromodel is not easy to carry and maintain are solved.
Drawings
FIG. 1 is a schematic perspective view of a docking structure between a fuselage and a wing for easy assembly and disassembly;
FIG. 2 is a schematic diagram of a second perspective structure of a docking structure between a fuselage and a wing for easy assembly and disassembly according to an embodiment of the present invention;
FIG. 3 is a schematic perspective view of a fuselage fixing seat of a docking structure for a fuselage and a wing, which is convenient to disassemble and assemble according to an embodiment of the present invention;
FIG. 4 is a schematic view of an installation perspective structure of a docking slider of a docking structure for docking a fuselage and a wing, which is convenient for disassembly and assembly according to an embodiment of the present invention;
fig. 5 is a schematic perspective view of a docking slider of a docking structure for a fuselage and a wing, which is convenient to disassemble and assemble according to an embodiment of the present invention.
Detailed Description
The present invention will be described in further detail with reference to the drawings and examples, in order to make the objects, technical solutions and advantages of the present invention more apparent. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the invention.
The implementation of the present invention will be described in detail below with reference to specific embodiments.
The same or similar reference numerals in the drawings of the present embodiment correspond to the same or similar components; in the description of the present invention, it should be understood that, if there is an azimuth or positional relationship indicated by terms such as "upper", "lower", "left", "right", etc., based on the azimuth or positional relationship shown in the drawings, it is only for convenience of describing the present invention and simplifying the description, but it is not indicated or implied that the apparatus or element referred to must have a specific azimuth, be constructed and operated in a specific azimuth, and thus terms describing the positional relationship in the drawings are merely illustrative and should not be construed as limitations of the present patent, and specific meanings of the terms described above may be understood by those skilled in the art according to specific circumstances.
Referring to fig. 1-5, a preferred embodiment of the present invention is provided.
The butt joint grafting structure of fuselage and wing convenient to dismouting that this embodiment provided for fixed mounting forms butt joint grafting structure on fuselage and wing respectively, thereby makes things convenient for dismantlement and fixed connection between wing and the fuselage, in order to carry and maintain of model of aviation.
The docking structure of a fuselage and a wing convenient to disassemble and assemble provided by the embodiment comprises a fuselage fixing seat 11 fixedly connected to the fuselage and a wing connecting seat 12 fixedly connected to the wing, wherein the fuselage fixing seat 11 is detachably connected with the wing connecting seat 12, the fuselage fixing seat 11 is provided with a fuselage docking surface 111 facing the wing and docking with the wing connecting seat 12, the wing connecting seat 12 is provided with a wing docking surface 121 facing the fuselage and docking with the fuselage fixing seat 11, a clamping groove 112 is recessed in the fuselage docking surface 111, an opening of the clamping groove 112 faces the wing, a clamping column 13 is formed in the wing docking surface 121, the clamping column 13 is embedded into the clamping groove 112, the fuselage docking surface 111 is abutted to the wing docking surface 121, a clamping hook 131 extending in a super-lateral bending manner is arranged at the front end of the clamping column 13, a docking sliding block 14 is arranged in the clamping groove 112, the docking sliding block 14 is prevented from moving outwards, and the clamping column 13 is clamped or separated from the clamping groove 112 when the docking sliding block 14 is moved.
Through the above-mentioned structural arrangement, when draw-in column 13 imbeds in draw-in groove 112, fuselage butt joint face 111 and wing butt joint face 121 butt, the butt joint slider 14 of fuselage fixing base 11 prevents the pothook 131 of wing connecting seat 12 to outwards remove, thereby realize the stable connection between fuselage and the wing, when the butt joint slider 14 of both sides removes, pothook 131 breaks away from butt joint slider 14, draw-in column 13 breaks away from with draw-in groove 112, thereby realize dismantling between wing and the fuselage, such structural arrangement is simple, installation and dismantlement are easy, dismantle two back with the wing of both sides, thereby portable, and after the wing damaged, change the wing also be convenient for maintain.
In this embodiment, the two sides of the body fixing seat 11 are provided with the clamping grooves 112, the two sides of the wing connecting seat 12 corresponding to the two sides are provided with the clamping columns 13, and the hooks 131 extending from the clamping columns 13 are bent and extended in opposite directions, so that the connection between the body fixing seat 11 and the wing connecting seat 12 is more stable; and the butting slide blocks 14 are respectively arranged in the clamping grooves 112, and the butting slide blocks 14 are arranged between the clamping hooks 131, so that the clamping hooks 131 at two sides are limited or the clamping hooks 131 at two sides are separated.
In order to install the docking slide block 14 in the clamping groove 112, the mounting groove 113 is formed in the upper portion of the body fixing seat 11, the mounting opening communicated to the clamping groove 112 is formed in the bottom of the mounting groove 113, and the docking slide block 14 passes through the mounting opening in the mounting groove 113 and is arranged in the clamping groove 112, so that the docking slide block 14 installed from above cannot pass out of the clamping groove 112, and when the docking slide block 14 in the clamping groove 112 limits the clamping hook 131 to move outwards, the clamping hook 131 cannot drive the docking slide block 14 to pass through the clamping groove 112, and structural connection between the wing and the body is firmer.
In this embodiment, the butt-joint sliding block 14 is disposed between the hooks 131 on two sides, the rib 141 extends from one surface of the butt-joint sliding block 14 facing the hooks 131, the rib 141 has an inner end surface of the rib 141 facing away from the wing, the hooks 131 have a bending surface facing the wing direction, and when the bending surface of the hooks 131 abuts against the inner end surface of the rib 141, the butt-joint sliding block 14 restricts the outward movement of the clamping column 13, thereby realizing stable fixation between the wing and the fuselage.
In this way, the convex edges 141 on the butting sliding blocks 14 on the two sides are respectively abutted with the hooks 131 on the two sides of the wing connecting seat 12 to clamp the wing connecting seat 12, so that the wing is prevented from being separated from the fuselage, and the wing is prevented from being translated in the directions of the two sides to be separated.
In addition, the butt-joint sliding blocks 14 comprise a movable connecting body, the side walls of the movable blocks 144 are extended with the convex edges 141, a return spring 16 is arranged between the convex edges 141 and the clamping groove 112, one end of the return spring 16 is abutted against the inner end 143, and the other end is abutted against the side walls of the clamping groove 112, so that the convex edges 141 on the butt-joint sliding blocks 14 on two sides are abutted with the clamping hooks 131 more tightly through the return springs 16 on two sides respectively, and the connection between the fuselage and the wing is more stable.
In this embodiment, the inner end portion 143 of the docking slide 14 has a slide spring groove for fixing the return spring 16, and a clamping spring groove is also formed on the inner wall of the clamping groove 112, so that two ends of the return spring 16 are respectively embedded in the slide spring groove and the clamping spring groove, thereby preventing the offset of the return spring 16 and firmly connecting the fuselage with the wing.
And, the one side that the bead 141 deviates from the movable block 144 is the outer terminal surface of bead, and the outer terminal surface of bead 141 is arranged towards the direction slope that deviates from the wing, and the same pothook 131 inclines towards the direction that deviates from the fuselage towards the fuselage, like this when card post 13 imbeds in draw-in groove 112, makes pothook 131 imbeds draw-in groove 112 more easily to with bead 141 looks butt, thereby the installation between fuselage and the wing of being convenient for.
In addition, the mounting opening 118 is identical to the longitudinal joint surface of the docking slide 14, and the mounting opening 118 extends in a transverse direction, so that the docking slide 14 can move transversely along the mounting opening 118, and thus when the fuselage is stably connected with the wing, the docking slide 14 abuts against the side wall of the mounting opening 118, and the docking slide 14 on two sides is transversely moved towards the hooks 131 far away from two sides respectively, so that the hooks 131 are separated from the ribs 141, and the wing and the fuselage are detached.
Meanwhile, a limiting block 142 is arranged at the upper part of the butting slide block 14, the limiting block 142 extends out of the top of the machine body fixing seat 11, the limiting block 142 is pulled to enable the butting slide block 14 to move in a direction away from the clamping hooks 131, so that disassembly is realized, at the moment, the reset spring 16 is compressed, after the limiting block 142 is loosened, the butting slide block 14 is reset, when the wing connecting seat 12 needs to be installed again, the clamping columns 13 on the wing connecting seat 12 are aligned with the clamping grooves 112 on the machine body fixing seat 11, the limiting block 142 is pulled, the clamping columns 13 are embedded into the clamping grooves 112, the limiting block 142 is loosened, the butting slide block 14 is reset, and the convex edges 141 on two sides are abutted against the clamping hooks 131 on two sides to realize clamping positions; or directly press the clamping post 13 into the clamping groove 112, the inclined surface on the clamping hook 131 is abutted against the inclined surface on the convex rib 141, the butt joint sliding block 14 is transversely moved through extrusion, the clamping post 13 is embedded into the clamping groove 112, the butt joint sliding block 14 is reset, and the convex rib 141 is abutted against the clamping hook 131, so that the clamping post 13 is prevented from moving outwards.
And, the installation groove 113 is internally provided with the slider fixing piece 15, the slider fixing piece 15 is abutted against the upper end face of the butt-joint slider 14, the slider fixing piece 15 is provided with a limit opening 151 with a longitudinal through hole, a limit block 142 at the upper part of the butt-joint slider 14 is arranged in the limit opening 151 and penetrates through the limit opening 151, and when the reset spring 16 abuts against the butt-joint slider 14 and the clamping hook 131, the limit block 142 abuts against one end of the limit opening 151, so that the movement of the butt-joint slider 14 is limited, the abrasion of the butt-joint slider 14 to the installation opening 118 is prevented, and meanwhile, the installation of the butt-joint slider 14 is more stable.
In addition, the slot wall 117 is formed on the inner and outer sides of the slot 112, the slot wall 117 abuts against two sides of the butt-joint sliding block 14, so that the butt-joint sliding block 14 is prevented from penetrating out of the slot 112, the wing is more firmly connected with the fuselage, and meanwhile, the moving direction of the butt-joint sliding block 14 in the slot 112 is limited, namely, only the lateral movement can be performed, so that the convex edge 141 abuts against the clamping hook 131 or the test convex edge 141 is far away from the clamping hook 131, the butt-joint sliding block 14 is more firmly installed, and the connection between the wing and the fuselage is more stable.
The body fixing seat 11 is fixedly connected with the body, the body fixing seat 11 is sheet-shaped and provided with a body through groove 114 towards the direction of the body, a clamping groove protrusion 115 is formed at the position of a clamping groove 112 in the body through groove 114, and a clamping groove notch embedded in the clamping groove protrusion 115 is formed on the body, so that the sheet-shaped body fixing seat 11 is stably attached to the body and fixedly connected, and the body fixing seat 11 is convenient to replace; meanwhile, a body boss 116 is formed in the body through groove 114, and the body boss 116 is used for positioning the body fixing seat 11 on the body to prevent deviation.
The wing connecting seat 12 is fixedly connected with the wing, the wing connecting seat 12 is sheet-shaped and is provided with a wing through groove 122 towards the direction of the wing, so that the wing connecting seat 12 in the sheet shape is stably attached to the wing and is fixedly connected, and the wing connecting seat 12 is convenient to replace; meanwhile, a wing boss 123 is formed in the wing through groove 122, and the wing boss 123 is used for positioning the wing connecting seat 12 on the wing to prevent deflection.
Meanwhile, a wing positioning block is arranged on the butt joint surface of the wing facing the fuselage, a fuselage positioning groove is arranged on the butt joint surface of the fuselage facing the wing, and the wing positioning block is embedded in the fuselage positioning groove, so that the wing and the fuselage are positioned conveniently, clamping is further carried out, and the fuselage and the wing are connected stably.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, and alternatives falling within the spirit and principles of the invention.
Claims (5)
1. The docking and plugging structure is characterized by comprising a body fixing seat and a wing connecting seat which is docked with the body fixing seat, wherein the body fixing seat is provided with a body docking surface which is docked with the wing connecting seat, and the wing connecting seat is provided with a wing docking surface which is docked with the body; the wing butt joint surface is convexly provided with a clamping column embedded in the clamping groove, the clamping column extends towards the body butt joint surface, and the front end of the clamping column is provided with a clamping hook extending towards the side; a butt-joint sliding block for clamping the clamping hook is arranged in the machine body fixing seat, and the butt-joint sliding block is movably arranged in the clamping groove; the butt-joint sliding block is enabled to clamp the clamping hook or be separated from the clamping hook by moving the butt-joint sliding block;
the top of the machine body fixing seat is provided with a mounting groove, the bottom of the mounting groove is provided with a mounting opening communicated with the clamping groove, and the butt-joint sliding block penetrates through the mounting opening and is arranged in the clamping groove;
the butt joint sliding block is provided with a convex rib which is abutted with the clamping hook, the convex rib is provided with a convex rib inner end surface which is away from the wing, the clamping hook is provided with a bending surface which faces the wing, and the convex rib inner end surface is abutted with the bending surface to limit outward movement of the clamping column;
the upper part of the butt joint sliding block is provided with a limiting block, and the limiting block extends upwards to the outside of the top of the machine body fixing seat;
the installation groove is internally provided with a sliding block fixing plate, a limiting opening for limiting the movement of the limiting block is arranged in the sliding block fixing plate, the limiting block penetrates through the limiting opening of the sliding fixing plate, and when the limiting block is abutted to the side end of the limiting opening, the abutting sliding block limits the clamping hook to move outwards.
2. The docking structure of a fuselage and a wing which are convenient to disassemble and assemble according to claim 1, wherein the docking slide comprises a movable block body, the side wall of the movable block body is extended with the convex rib, a return spring is arranged between the side walls of the convex rib and the clamping groove, and the return spring drives the docking slide to move towards the extending direction of the convex rib.
3. The fuselage-wing docking structure of claim 2, wherein the other side wall of the movable block has a slider spring slot in which the return spring is embedded.
4. The fuselage-wing butt-joint connection structure of claim 2, wherein the rib has an outer end surface facing away from the movable block, the outer end surface of the rib being disposed obliquely.
5. The docking structure of a fuselage and a wing for easy disassembly and assembly according to claim 1, wherein the inner and outer sides of the clamping groove are formed with clamping groove walls for limiting the movement direction of the docking slide block.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711366452.1A CN108031129B (en) | 2017-12-18 | 2017-12-18 | Butt joint grafting structure of fuselage and wing convenient to dismouting |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711366452.1A CN108031129B (en) | 2017-12-18 | 2017-12-18 | Butt joint grafting structure of fuselage and wing convenient to dismouting |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108031129A CN108031129A (en) | 2018-05-15 |
| CN108031129B true CN108031129B (en) | 2024-01-02 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711366452.1A Active CN108031129B (en) | 2017-12-18 | 2017-12-18 | Butt joint grafting structure of fuselage and wing convenient to dismouting |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108031129B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110588951A (en) * | 2018-06-13 | 2019-12-20 | 北京京东尚科信息技术有限公司 | Connecting device and aircraft |
| CN109927878B (en) * | 2019-04-25 | 2024-02-02 | 西安航空学院 | Diamond wing mounting structure and aircraft with same |
| CN112278235B (en) * | 2020-11-05 | 2022-03-11 | 湖南浩天翼航空技术有限公司 | Wing quick locking mechanism of fixed-wing unmanned aerial vehicle and using method thereof |
| CN114851164A (en) * | 2022-05-06 | 2022-08-05 | 湖南固工机器人有限公司 | Wearable shoulder assistance exoskeleton |
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| US5363940A (en) * | 1992-08-11 | 1994-11-15 | Otmar Fahrion | Aircraft work dock |
| DE102011010164A1 (en) * | 2011-02-02 | 2012-08-02 | M. Seebauer Vertrbiebs Gmbh | Model airplane with manual adjustment for switching between straight flight and looping or circular flight |
| CN105109663A (en) * | 2015-09-04 | 2015-12-02 | 西北工业大学 | Motor-driven sealing mechanism for aircraft external hanging point |
| CN205906206U (en) * | 2016-07-23 | 2017-01-25 | 北京耐威智能科技有限公司 | Wing connecting device , wing and aircraft |
| CN107226195A (en) * | 2017-04-28 | 2017-10-03 | 青岛高智高新科技有限公司 | A kind of unmanned plane wing registration locking device |
| CN107472515A (en) * | 2017-07-28 | 2017-12-15 | 河南农业大学 | Six rotors are taken photo by plane unmanned plane and its wing arm Fast detachable unit |
| CN208097396U (en) * | 2017-12-18 | 2018-11-16 | 深圳市中航电科技有限公司 | Easy-to-mount fuselage docks connected structure with wing |
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2017
- 2017-12-18 CN CN201711366452.1A patent/CN108031129B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5363940A (en) * | 1992-08-11 | 1994-11-15 | Otmar Fahrion | Aircraft work dock |
| DE102011010164A1 (en) * | 2011-02-02 | 2012-08-02 | M. Seebauer Vertrbiebs Gmbh | Model airplane with manual adjustment for switching between straight flight and looping or circular flight |
| CN105109663A (en) * | 2015-09-04 | 2015-12-02 | 西北工业大学 | Motor-driven sealing mechanism for aircraft external hanging point |
| CN205906206U (en) * | 2016-07-23 | 2017-01-25 | 北京耐威智能科技有限公司 | Wing connecting device , wing and aircraft |
| CN107226195A (en) * | 2017-04-28 | 2017-10-03 | 青岛高智高新科技有限公司 | A kind of unmanned plane wing registration locking device |
| CN107472515A (en) * | 2017-07-28 | 2017-12-15 | 河南农业大学 | Six rotors are taken photo by plane unmanned plane and its wing arm Fast detachable unit |
| CN208097396U (en) * | 2017-12-18 | 2018-11-16 | 深圳市中航电科技有限公司 | Easy-to-mount fuselage docks connected structure with wing |
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| Publication number | Publication date |
|---|---|
| CN108031129A (en) | 2018-05-15 |
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