CN112623182A - Wing body connection structure and contain wing body connection structure's unmanned aerial vehicle - Google Patents
Wing body connection structure and contain wing body connection structure's unmanned aerial vehicle Download PDFInfo
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- CN112623182A CN112623182A CN202011586114.0A CN202011586114A CN112623182A CN 112623182 A CN112623182 A CN 112623182A CN 202011586114 A CN202011586114 A CN 202011586114A CN 112623182 A CN112623182 A CN 112623182A
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- wing
- unit
- fuselage
- wing body
- fixing part
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/26—Attaching the wing or tail units or stabilising surfaces
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
Abstract
The invention relates to the technical field of unmanned aerial vehicles, and discloses a wing body connecting structure and an unmanned aerial vehicle comprising the same. Wing body connection structure includes: the wing body connecting unit is used for preliminarily fixing the fuselage and the wings and transmitting the acting force between the fuselage and the wings; the inserting locking unit is used for realizing the quick connection of the fuselage and the wings and limiting the freedom degree of the wings in the unfolding direction; and the clearance eliminating unit is used for providing a pre-tightening load and eliminating the clearance effect of the mechanism, so that the vibration caused by the periodic rotation of the engine and the change of the pneumatic load is avoided. The invention can realize quick assembly and disassembly or tool-free assembly and disassembly, reduces the preparation time for unfolding and folding, and can better deal with emergency tasks; the requirement for high strength of connection of the unmanned aerial vehicle body in certain specific recycling scenes also meets the design and use requirements. The problem of conventional unmanned aerial vehicle installation loaded down with trivial details, the reliability is poor is solved, the problem that unmanned aerial vehicle connection structure is complicated when retrieving to and the no standard connection problem of organism.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to a wing body connecting structure suitable for connecting wings and a fuselage of a fixed-wing unmanned aerial vehicle and an unmanned aerial vehicle comprising the wing body connecting structure.
Background
The wings of the fixed-wing unmanned aerial vehicle are generally designed into independent sub-components which are symmetrical left and right relative to the body, can be disassembled during transition and transportation, and can be assembled with the body during battle or use; therefore, a safe and reliable connection and locking mode of the wing and the fuselage is very necessary. With the rapid development of the unmanned aerial vehicle technology, the user experience requirements on the unmanned aerial vehicle are higher and higher, for example, the efficiency of dismounting and mounting wings and a fuselage of the unmanned aerial vehicle.
In the prior art, the separation of the wing and the fuselage is realized by separating the lock pin and the mounting seat, the mounting seat is mounted on a rib at the root end of the wing, the lock pin is provided with a pressure spring, the upper part of the lock pin penetrates through the mounting seat, the pressure spring is arranged in a cavity formed by the mounting seat and the lock pin, the pin shaft is arranged in a threaded hole formed in the lock pin, and the pull ring is mounted in a through hole formed in the upper part of the lock pin, so that the connection locking and the disassembly of the wing and the fuselage can be carried out outside. Or, the structure includes fuselage fixing base and wing connecting seat, the fuselage fixing base has the fuselage butt joint face with the butt joint of wing connecting seat, the wing connecting seat has the wing butt joint face with the fuselage butt joint, the fuselage butt joint face has the locking knob, the wing butt joint face has the card post, when the card post embedding locking knob, fuselage butt joint face and wing butt joint face butt, the front end of card post has the pothook of buckling the extension towards the side, the butt joint slider that prevents the pothook outwards to remove has in the locking knob, realize being connected between fuselage and the wing, the butt joint slider removes, the card post breaks away from the locking knob, realize the dismantlement between wing and the fuselage.
However, in some specific conditions, such as the recovery process of the skyhook of the unmanned aerial vehicle, the wing-body connecting structure needs to bear the impact load from the rope system to the spanwise direction of the wing-body connecting structure, namely the axial tensile load and the torsional load of the wing-body connecting structure. The above-described joining techniques may not be able to withstand such transient high overloads, with immeasurable consequences such as recovery failure.
Disclosure of Invention
The invention discloses a wing body connecting structure and an unmanned aerial vehicle comprising the same, and aims to solve any problem in the above problems or other potential problems in the prior art.
In order to solve the problems, the technical scheme of the invention is as follows: a wing body attachment structure, the wing body attachment structure comprising: the wing body connecting unit, the inserting locking unit and the gap eliminating unit are arranged on the wing body;
the wing body connecting unit is used for preliminarily fixing the fuselage and the wings and transmitting the acting force between the fuselage and the wings;
the inserting and locking unit is used for realizing the quick connection between the fuselage and the wings and limiting the freedom degree of the wings in the unfolding direction;
and the clearance eliminating unit is used for providing a pre-tightening load and eliminating the clearance effect of the mechanism, so that the vibration caused by the periodic rotation of the engine and the change of the pneumatic load is avoided.
The wing body connecting unit is respectively inserted into a bearing structure in the fuselage and a bearing structure in the wing, the inserting locking unit 4 is arranged between the fuselage and the wing, and the gap eliminating unit is arranged on the inserting locking unit 4.
Further, the plugging locking unit 4 comprises a first mounting seat, a plug pin, a locking knob and a second mounting seat,
wherein the first mounting seat is screwed on the bearing structure of the fuselage, the second mounting seat is symmetrically screwed on the bearing structure of the wing,
a locking knob mounting hole, a first bolt hole and an anti-backlash unit mounting hole are formed in the first mounting seat, one end of the bolt hole is communicated with the locking knob mounting hole, and the anti-backlash unit mounting hole is communicated with the locking knob mounting hole;
the locking knob is movably arranged in the locking knob mounting hole, and a bolt locking port is formed in the locking knob;
a second bolt hole is formed in the second mounting seat;
one end of the bolt is inserted into the second bolt hole and is connected with the side wall of the second bolt hole, the other end of the bolt is inserted into the first bolt hole, and the end part of the bolt is locked by a locking knob;
the anti-backlash unit is arranged in the anti-backlash unit mounting hole.
Further, the anti-backlash mechanism comprises a pressure spring and a ball, the ball is arranged in the anti-backlash unit mounting hole, and the ball is pressed by the pressure spring.
Further, the first mounting seat comprises a first fixing part, a first extending part, a first reinforcing part and a first main body,
the extension part is arranged at one end of the first fixing part, the first main body is arranged on the first fixing part, the first reinforcing part is arranged on the first extension part, one end of the reinforcing part is fixedly connected with the first main body, and the first main body is provided with the locking knob mounting hole, the first plug pin hole and the anti-backlash unit mounting hole.
Further, the second mounting seat comprises a second fixing part, a second extending part and a second main body;
the first main body is cylindrical and horizontally arranged on the second fixing part, and one end of the second extending part is fixedly connected with the fixing part;
the first main body is cylindrical, a second bolt hole is formed in the first main body, and connecting threads are arranged on the inner wall of the second bolt hole.
Further, the bolt comprises a spherical fixing part, a pretightening force part and a connecting fixing part,
wherein one end of the spherical fixing part is fixedly connected with one end of the pretightening force part through a transition section, the other end of the pretightening force part is fixedly connected with the connecting fixing part,
and the side wall of the connecting and fixing part is provided with connecting threads.
Further, the second extension part comprises a second extension main body, a second extension reinforcing rib and an extension fixing part,
wherein, one end of the second extension main body is fixedly connected with the first main body, the other end is fixedly connected with the extension fixing part, the extension fixing part is provided with a fixing hole,
at least one second elongated bead is disposed on an end face of the second elongated body.
Further, the angle between the second elongate body and the spar of the wing is no more than 5 °.
Further, the wing body connecting unit comprises a rectangular guide part, a conical surface bearing part and a rectangular fixing part;
wherein 2 conical surface bearing parts are arranged at two ends of the rectangular fixing part and are fixedly connected with the rectangular fixing part,
the 2 rectangular guide parts are respectively fixedly connected with the other ends of the 2 conical surface bearing parts,
the cross section of the rectangular fixing part is the same as that of the end parts of the 2 conical surface bearing parts.
The utility model provides an unmanned aerial vehicle, unmanned aerial vehicle includes fuselage and wing, adopt foretell wing body connection structure to connect between fuselage and the wing.
The invention has the beneficial effects that: by adopting the technical scheme, the invention has simple structure, can realize quick assembly and disassembly or tool-free assembly and disassembly, reduces the preparation time for unfolding and folding, and can better cope with emergency tasks; the requirement of connecting high strength to the unmanned aerial vehicle organism equally satisfies design and operation requirement in some specific recovery scenes, has solved conventional unmanned aerial vehicle installation loaded down with trivial details simultaneously, the poor problem of reliability, has solved the fixed point and has retrieved the problem that unmanned aerial vehicle connection structure is complicated such as sky hook recovery, has solved the nonstandard piece connection problem of organism.
Drawings
Fig. 1 is a schematic layout of a wing body connection structure in a fixed-wing aircraft according to the present invention.
Fig. 2 is a schematic structural diagram of a wing body connection structure according to the present invention.
Fig. 3 is an enlarged schematic view of the symbol I in fig. 1.
Fig. 4 is a state diagram of fig. 3 after disassembly, namely separation of the wing and the fuselage.
Fig. 5 is an exploded view of fig. 3.
Fig. 6 is an enlarged view of fig. 1, item ii.
Fig. 7 is a schematic structural view of a plug of a wing body connection structure according to the present invention.
In the figure:
1. the airplane comprises an airplane body, 2 wings, 3 wing body connecting units, 4 splicing locking units, 4-1 first installation seats, 4-2 locking knobs, 4-3 bolts, 4-31 spherical fixing parts, 4-32 pretightening force parts, 4-33 connecting fixing parts, 4-44 connecting threads, 4-4 second installation seats, 4-5 locking knob installation holes, 4-6 first bolt holes, 4-7 gap eliminating unit installation holes and 5 gap eliminating units.
Detailed Description
The technical solution of the present invention is further explained below with reference to the specific embodiments and the accompanying drawings.
As shown in fig. 2, the wing body connection structure of the present invention includes: the wing body connecting unit 3, the inserting locking unit 4 and the gap eliminating unit 5;
the wing body connecting unit 3 is used for primarily fixing the fuselage and the wings and transmitting the acting force between the fuselage and the wings;
the inserting locking unit 4 is used for realizing the quick connection between the fuselage and the wings and limiting the freedom degree of the wings in the unfolding direction;
and the anti-backlash unit 5 is used for providing pre-tightening load and eliminating mechanism backlash, and avoiding vibration caused by periodic rotation of the engine and change of pneumatic load.
The wing body connecting unit 3 is respectively inserted into a bearing structure in the fuselage 1 and a bearing structure in the wing 2, the inserting and locking unit 4 is arranged between the fuselage 1 and the wing 2, and the gap eliminating unit 5 is arranged on the inserting and locking unit 4.
The inserting and locking unit 4 comprises a first mounting seat 4-1, a bolt 4-3, a locking knob 4-2 and a second mounting seat 4-4,
wherein, the first mounting seat 4-1 is screwed on the bearing structure of the fuselage 1, the second mounting seat 4-4 is symmetrically screwed on the bearing structure of the wing 2,
a locking knob mounting hole 4-5, a first bolt hole 4-6 and an anti-backlash unit mounting hole 4-7 are formed in the first mounting seat 4-1, one end of the first bolt hole 4-6 is communicated with the locking knob mounting hole 4-5, and the anti-backlash unit mounting hole 4-6 is communicated with the locking knob mounting hole 4-5;
the locking knob 4-2 is movably arranged in the locking knob mounting hole 4-5, and a bolt locking opening 4-7 is formed in the locking knob 4-2;
a second bolt hole 4-8 is formed in the second mounting seat 4-4;
one end of the bolt 4-3 is inserted into the second bolt hole 4-8 and is connected with the side wall of the second bolt hole 4-8, the other end of the bolt is inserted into the first bolt hole 4-6, and the end part of the bolt 4-3 is locked by the locking knob 4-2;
the anti-backlash unit 5 is arranged in the anti-backlash unit mounting hole 4-7.
The anti-backlash mechanism 5 comprises a pressure spring 5-1 and a ball 5-2, the ball 5-2 is arranged in the anti-backlash unit mounting hole 4-7, and the ball 5-2 is pressed by the pressure spring 5-1.
The first mounting seat 4-1 comprises a first fixing part 4-11, a first extending part 4-12, a first reinforcing part 4-13 and a first main body 4-14,
the extension part 4-12 is arranged at one end of the first fixing part 4-11, the main body 4-14 is arranged on the first fixing part 4-11, the first reinforcing part 4-13 is arranged on the first extension part 4-12, one end of the first reinforcing part 4-13 is fixedly connected with the first main body 4-14, and the first main body 4-13 is provided with a locking knob 4-2 mounting hole, a first bolt hole 4-6 and a gap eliminating unit 5 mounting hole.
The second mounting seat 4-4 comprises a second fixing part 4-41, a second extending part 4-42 and a second main body 4-45;
the second main body 4-45 is cylindrical and horizontally arranged on the second fixing part 4-41, and one end of the second extending part 4-42 is fixedly connected with the second fixing part 4-41;
the second cylindrical body 4-45 is provided with a second pin hole 4-6, and the inner wall of the second pin hole 4-6 is provided with a connecting thread (not shown in the figures), as shown in fig. 2-5.
The bolt 4-3 comprises a spherical fixing part 4-31, a pretightening force part 4-32 and a connecting fixing part 4-33,
wherein, one end of the spherical fixed part 4-31 is fixedly connected with one end of the pretightening force part 4-32 through a transition section, the other end of the pretightening force part 4-32 is fixedly connected with the connecting fixed part 4-33,
the side wall of the connection fixing part 4-33 is provided with a connection thread 4-34, as shown in fig. 7.
The second extension 4-42 includes a second extension body 4-21, a second extension bead 4-43, and an extension fixture 4-44,
wherein one end of the second extension main body 4-21 is fixedly connected with the second main body 4-41, the other end is fixedly connected with the extension fixing part 4-44, the extension fixing part 4-44 is provided with a fixing hole,
at least one second elongated reinforcing bead 4-43 is provided on an end face of the second elongated body 4-42.
The angle between the second extension 4-42 and the spar of the wing 2 is not more than 5 deg., and the position of intersection of the second extension 4-42 and the wing spar is used as a length reference for determining the second extension 4-42.
The wing body connecting unit 3 comprises a rectangular guide part 3-3, a conical surface bearing part 3-2 and a rectangular fixing part 3-1;
wherein 2 conical surface bearing parts 3-2 are arranged at two ends of the rectangular fixing part 3-1 and are fixedly connected with the rectangular fixing part 3-1,
the 2 rectangular guide parts 3-2 are respectively fixedly connected with the other ends of the 2 conical surface bearing parts 3-2,
the rectangular fixing portion 3-2 has the same cross-section as the 2 cone carrying portion ends 3-2, as shown in FIG. 5.
The utility model provides an unmanned aerial vehicle, unmanned aerial vehicle includes fuselage and wing, adopt foretell wing body connection structure to connect between fuselage and the wing.
Example (b):
a wing body connecting structure comprises a first mounting seat, a bolt, a locking knob, a gap eliminating unit, a second mounting seat and a wing body connecting unit. The first mounting seat is screwed on a bearing structure in the fuselage, and the second mounting seat is screwed on a bearing structure in the wing; the bolt is fixed on the second mounting seat, the bolt and the second mounting seat are designed into a split structure in consideration of production and assembly process reasons, and the wing body connecting unit can be independently taken down. The locking knob can rotate in the first mounting seat, and the rotation action of the locking knob can be manually controlled outside the machine body. When the wing is rotated to a fixed position, the gap eliminating unit can block the locking knob, so that the bolt is locked with the clamping groove, and the wing is connected with the body.
First mount pad is installed on the load structure of fuselage or interior wing, with first mount pad trompil position towards the outside, the bolt is installed on the load structure of outer wing or wing, with bolt tip towards the outside, bolt tip and first mount pad trompil need not cooperate, the locking knob is a cylinder type structure, open in the cylinder outside has the waist round hole, the locking knob can be installed inside first mount pad, and can be rotary motion around the cylinder center pin, it is spacing to design machinery on first mount pad, the turned angle of restriction locking knob. The waist round hole of the locking knob is matched with the end part of the bolt to a certain degree. The first mounting seat is provided with a spherical or cylindrical groove, the end part of the gap eliminating unit is a spherical top bead, and the spherical top bead are matched with each other.
During operation, the wing body connecting unit is installed to one side of the fuselage 1 or the wing 2, the wing or the outer wing provided with the bolt is butted to the inner wing or the fuselage provided with the first installation seat, meanwhile, the wing body connecting unit 3 is butted, the end part of the bolt is inserted into the waist circular hole of the locking knob through the opening of the first installation seat, the locking knob is rotated, the wing or the outer wing provided with the bolt cannot be separated from the fuselage or the inner wing, and after the locking knob is rotated to a certain angle, the spherical top ball at the end part of the gap eliminating unit 5 is bounced into the spherical or cylindrical groove of the first installation seat 3 to prevent looseness.
The anti-backlash unit 5 is composed of a pressure spring and a ball, wherein the pressure spring is designed according to the installation load, the working load and the rigidity of the anti-backlash mechanism, and the head of the ball has wear resistance. The backlash elimination unit 5 functions to provide a preload load and eliminate a mechanism backlash. In the flight process, unmanned aerial vehicle receives the engine cycle to rotate and the change of pneumatic load etc. produces the vibration, and crack unit 5 that disappears can guarantee that locking knob 5 in this connection structure can not be influenced by the vibration and cause the rotation to make the bolt break away from, cause the trouble that the wing breaks away from.
The wing body connecting unit 3 comprises a rectangular guide part, a conical surface bearing part and a rectangular fixing part;
wherein 2 conical surface bearing parts are arranged at two ends of the rectangular fixing part and are fixedly connected with the rectangular fixing part,
the 2 rectangular guide parts are respectively fixedly connected with the other ends of the 2 conical surface bearing parts,
the cross section of the rectangular fixing part is the same as that of the end parts of the 2 conical surface bearing parts.
The wing body connecting unit 3 is used for being respectively inserted into a bearing structure in the fuselage 1 and a bearing structure in the wing 2; the conical structure can ensure that the assembly gap is eliminated after the fuselage 1 and the wing 2 are installed in place, and ensure reliable force transmission.
Two sets of butt joint separating surfaces with the same structure are arranged, wherein one set is arranged on a force transmission path of a main wing beam (figure 3), and the other set is arranged on a force transmission path of an auxiliary wing beam (figure 4). When the unmanned aerial vehicle flies, the torque at the wing root is borne by two structures on respective force transmission routes; and most of the bending moment of the wing is borne by the wing body connecting unit 4.
When unmanned aerial vehicle day hook retrieves, will follow the exhibition to load pass through wing spar transmission to butt joint structural on, turn into the tensile load of bolt tip and locking knob, bolt tip and locking knob are the spherical surface contact, can greatly reduce stress distribution level, bear day hook retrieval time unmanned aerial vehicle's the recovery load that receives.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto. Any person skilled in the art should be able to substitute or change the technical solution of the present invention and its inventive concept within the scope of the present invention.
Claims (10)
1. A wing body attachment structure, comprising: the wing body connecting unit, the inserting locking unit and the gap eliminating unit are arranged on the wing body;
the wing body connecting unit is used for preliminarily fixing the fuselage and the wings and transmitting the acting force between the fuselage and the wings;
the inserting and locking unit is used for realizing the quick connection between the fuselage and the wings and limiting the freedom degree of the wings in the unfolding direction;
the clearance eliminating unit is used for providing a pre-tightening load and eliminating the clearance effect of the mechanism, so that the vibration caused by the periodic rotation of the engine and the change of the pneumatic load is avoided;
the wing body connecting unit is respectively inserted into a bearing structure in the fuselage and a bearing structure in the wing, the inserting and locking unit is arranged between the fuselage and the wing, and the gap eliminating unit is arranged on the inserting and locking unit.
2. The wing body connection structure of claim 1, wherein the plug-in locking unit comprises a first mounting seat, a plug pin, a locking knob, and a second mounting seat,
wherein the first mounting seat is screwed on the bearing structure of the fuselage, the second mounting seat is symmetrically screwed on the bearing structure of the wing,
a locking knob mounting hole, a first bolt hole and an anti-backlash unit mounting hole are formed in the first mounting seat, one end of the bolt hole is communicated with the locking knob mounting hole, and the anti-backlash unit mounting hole is communicated with the locking knob mounting hole;
the locking knob is movably arranged in the locking knob mounting hole, and a bolt locking port is formed in the locking knob;
a second bolt hole is formed in the second mounting seat;
one end of the bolt is inserted into the second bolt hole and is connected with the side wall of the second bolt hole, the other end of the bolt is inserted into the first bolt hole, and the end part of the bolt is locked by a locking knob;
the anti-backlash unit is arranged in the anti-backlash unit mounting hole.
3. The wing body connecting structure according to claim 2, wherein the anti-backlash mechanism includes a compression spring and a ball, the ball being disposed in the anti-backlash unit mounting hole, the ball being pressed by the compression spring.
4. The wing body attachment structure according to claim 2, wherein the first mounting seat includes a first fixing portion, a first extending portion, a first reinforcing portion, and a first main body,
the first extending part is arranged at one end of the first fixing part, the first main body is arranged on the first fixing part, the first reinforcing part is arranged on the first extending part, one end of the reinforcing part is fixedly connected with the first main body, and the first main body is provided with the locking knob mounting hole, the first bolt hole and the anti-backlash unit mounting hole.
5. The wing body attachment structure of claim 2, wherein the second mount includes a second fixed portion, a second extension, and a second body;
the second main body is cylindrical and horizontally arranged on the second fixing part, and one end of the second extending part is fixedly connected with the fixing part;
the second main body is cylindrical, a second bolt hole is formed in the second main body, and connecting threads are arranged on the inner wall of the second bolt hole.
6. The wing body connecting structure according to claim 2, wherein the plug includes a spherical fixing portion, a pretightening force portion, and a connecting fixing portion,
wherein one end of the spherical fixing part is fixedly connected with one end of the pretightening force part through a transition section, the other end of the pretightening force part is fixedly connected with the connecting fixing part,
and the side wall of the connecting and fixing part is provided with connecting threads.
7. The wing body attachment structure of claim 5, wherein the second extension includes a second extension body, a second extension bead, and an extension fixing portion,
wherein one end of the second extension main body is fixedly connected with the first main body, the other end is fixedly connected with the extension fixing part, the extension fixing part is provided with a fixing hole,
at least one second elongated bead is disposed on an end face of the second elongated body.
8. The wing body attachment structure of claim 7, wherein the angle between the second extension and the spar of the wing is no greater than 5 °.
9. The wing body connection structure according to claim 1, wherein the wing body connection unit includes a rectangular guide portion, a tapered surface bearing portion, and a rectangular fixing portion;
wherein 2 conical surface bearing parts are arranged at two ends of the rectangular fixing part and are fixedly connected with the rectangular fixing part,
the 2 rectangular guide parts are respectively fixedly connected with the other ends of the 2 conical surface bearing parts,
the cross section of the rectangular fixing part is the same as that of the end parts of the 2 conical surface bearing parts.
10. An unmanned aerial vehicle, the unmanned aerial vehicle includes fuselage and wing, characterized in that, adopt the wing body connection structure of any one of claims 1-9 to connect between fuselage and the wing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011586114.0A CN112623182B (en) | 2020-12-28 | 2020-12-28 | Wing body connection structure and contain wing body connection structure's unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011586114.0A CN112623182B (en) | 2020-12-28 | 2020-12-28 | Wing body connection structure and contain wing body connection structure's unmanned aerial vehicle |
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| CN112623182A true CN112623182A (en) | 2021-04-09 |
| CN112623182B CN112623182B (en) | 2022-10-28 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114435583A (en) * | 2022-01-04 | 2022-05-06 | 南京航空航天大学 | Wing locking and separating mechanism of combined unmanned aerial vehicle and working method of wing locking and separating mechanism |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2010228598A (en) * | 2009-03-27 | 2010-10-14 | Japan Aerospace Exploration Agency | Fuselage-wing connection part noise reduction device |
| CN202038449U (en) * | 2010-12-14 | 2011-11-16 | 上海智晟航空科技有限公司 | Plane body-wing connecting mechanism for plane |
| CN202495375U (en) * | 2012-03-27 | 2012-10-17 | 天津祥嘉流体控制系统有限公司 | Operation knob structure used by electric actuating mechanism |
| CN203623960U (en) * | 2013-12-20 | 2014-06-04 | 海鹰航空通用装备有限责任公司 | Device for connecting wings and body of small-and-medium-sized fixed-wing unmanned aerial vehicle |
| CN104343790A (en) * | 2014-10-17 | 2015-02-11 | 无锡同捷汽车设计有限公司 | Quick rotating and fixing structure |
| CN110775248A (en) * | 2019-10-21 | 2020-02-11 | 深圳市道通智能航空技术有限公司 | Unmanned aerial vehicle |
| EP3674204A1 (en) * | 2018-12-26 | 2020-07-01 | Airbus Operations SAS | Aircraft wing unit comprising two wings attached to one another |
-
2020
- 2020-12-28 CN CN202011586114.0A patent/CN112623182B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2010228598A (en) * | 2009-03-27 | 2010-10-14 | Japan Aerospace Exploration Agency | Fuselage-wing connection part noise reduction device |
| CN202038449U (en) * | 2010-12-14 | 2011-11-16 | 上海智晟航空科技有限公司 | Plane body-wing connecting mechanism for plane |
| CN202495375U (en) * | 2012-03-27 | 2012-10-17 | 天津祥嘉流体控制系统有限公司 | Operation knob structure used by electric actuating mechanism |
| CN203623960U (en) * | 2013-12-20 | 2014-06-04 | 海鹰航空通用装备有限责任公司 | Device for connecting wings and body of small-and-medium-sized fixed-wing unmanned aerial vehicle |
| CN104343790A (en) * | 2014-10-17 | 2015-02-11 | 无锡同捷汽车设计有限公司 | Quick rotating and fixing structure |
| EP3674204A1 (en) * | 2018-12-26 | 2020-07-01 | Airbus Operations SAS | Aircraft wing unit comprising two wings attached to one another |
| US20200207455A1 (en) * | 2018-12-26 | 2020-07-02 | Airbus Operations (S.A.S.) | Aircraft wing unit comprising two wings attached to one another |
| CN110775248A (en) * | 2019-10-21 | 2020-02-11 | 深圳市道通智能航空技术有限公司 | Unmanned aerial vehicle |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114435583A (en) * | 2022-01-04 | 2022-05-06 | 南京航空航天大学 | Wing locking and separating mechanism of combined unmanned aerial vehicle and working method of wing locking and separating mechanism |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112623182B (en) | 2022-10-28 |
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