CN220721416U - Unmanned aerial vehicle wing girder and quick detach structure thereof - Google Patents

Abstract

The utility model discloses an unmanned aerial vehicle wing girder and a quick-dismantling structure thereof, which relate to the technical field of unmanned aerial vehicles and have the technical scheme that: including right wing assembly, left wing assembly and fuselage assembly. The two main beams are connected with the frame in a penetrating way by adopting the pin shafts when being staggered, and are locked by using the safety pins, so that the whole dismounting process is visible, the wings can be quickly dismounted without auxiliary tools, the mounting structure is safe and reliable, and the mounting and dismounting are convenient; the hollow rectangular pipe wing main beam adopts an integrated forming mode, so that the problem of strength defect caused by possible virtual adhesion in the original secondary die assembly technology is solved; the material is matched with the stress, so that the characteristics of the material are fully utilized; according to the utility model, the metal bushing structure with wear-resistant property is arranged at the opening part of the mounting pin shaft, so that the hole edge stress caused by stress concentration is reduced, and meanwhile, the abrasion of the composite material caused by direct contact between the pin shaft and the composite material structure is prevented.

Description

Unmanned aerial vehicle wing girder and quick detach structure thereof

Technical Field

The utility model relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle wing girder and a quick-dismantling structure thereof.

Background

The wing of the fixed wing unmanned aerial vehicle is a very key and important structure in the structural design of an airplane, and the connection design of the wing and the fuselage is more, including the arrangement of joint positions, the construction form of joints, the analysis of structural strength and rigidity, the process forming method, the tolerance of fit clearances of the joints and the like.

At present, compared with the conventional wing, the wing is designed in a bilateral symmetry manner and is processed into two independent parts so as to be convenient to disassemble during transition transportation and assemble with a machine body during task use; it is therefore very necessary, and also very critical, to have a secure and reliable wing-to-fuselage connection locking. With the high-speed development of unmanned aerial vehicle technology, the user also has higher and higher requirements on the use experience when the wing and the fuselage are connected, such as disassembly efficiency, disassembly difficulty and the like.

The wing of the large-sized unmanned aerial vehicle in the prior art is connected with the fuselage by mainly adopting a wing spar and the fuselage end to be connected in the form of lug plates, the defect of the wing spar is that the structure is relatively complex, the vertical distance between the lug plates is small, the capability of bearing bending moment is limited, the required structural weight is large in order to enhance the strength of parts, the difficulty of the aircraft in the wing body butt joint is increased, the disassembly and assembly are inconvenient, and the disassembly and assembly capability of a user is also required to be high.

At present, the conventional forming process of the rectangular composite material beam generally comprises the steps of buckling two C-shaped beams after preforming, and performing secondary glue joint riveting, wherein the phenomenon of weak gluing or weak gluing possibly exists, and the hidden danger of strength exists.

Patent CN209795802U provides a wing body connection structure of light-weight light-duty sport aircraft, and the wing passes through the linking bridge with the fuselage to be connected, and wing leading edge root department is provided with the enhancement sleeve pipe, is provided with the enhancement sleeve pipe in the fuselage cooperation department equally, and two sleeve pipes are mutually supported and are connected. The wing root diagonal draw bars are connected with the lower part of the machine body to form a triangular stable structure, and the connection is firm. However, the diagonal draw bar with the structure is exposed to air flow, so that the resistance of the whole aircraft is increased, the energy consumption of the aircraft is increased, and the long-endurance flight is not facilitated.

Patent CN203793614U discloses a connection mode of unmanned aerial vehicle wing fuselage, and this structure is the three hole connection mode of single ear formula. The frame and the frame joint are machined into a whole, the wing spar and the beam joint are machined into a whole, the frame joint and the beam joint are single lugs, three bolt connecting holes are respectively formed, the bushing is embedded in the holes, and interference fit is achieved between the frame joint and the beam joint. During connection, the front beam and the rear beam are respectively and fixedly connected to the frame insulator by bolts. The structure is difficult to disassemble and assemble, and the unmanned aerial vehicle system cannot be assembled and disassembled quickly. The structural member is complex and the processing cost is high.

Disclosure of Invention

The utility model aims to solve the problems and provide the unmanned aerial vehicle wing girder and the quick-dismantling structure thereof, wherein the overlooking outline of the root part of the wing girder is wedge-shaped and is in a front-back staggered form, the material is matched with the stress characteristic, and the material performance characteristic is fully exerted; the pin shaft or the quick-release pin is in through connection with the bulkhead of the machine body, the tail end of the pin shaft is locked by the safety pin, visual installation and maintenance can be realized, the installation structure is safe and reliable, and the installation and the disassembly are convenient; the wing girder adopts an integrated forming process, so that the possible strength risk in secondary glue joint riveting is reduced.

The technical aim of the utility model is realized by the following technical scheme: the unmanned aerial vehicle wing girder and the quick-dismantling structure thereof comprise a right wing component, a left wing component and a fuselage component, wherein the right wing component comprises a right root rib front edge, a right wing girder, a right wing root rib and a right wing rear wall; the left wing assembly comprises a left root rib front edge, a left wing main beam, a left wing root rib and a left wing rear wall; the machine body assembly comprises a machine body front bulkhead, a machine body rear bulkhead, a left wing table rib, a right wing table rib and a machine body tail frame;

the left wing root rib and the front edge of the left root rib are respectively detachably connected to two sides of the left wing main beam, and the left wing rear wall is detachably connected to the left wing root rib; the right wing root rib and the front edge of the right root rib are respectively detachably connected to two sides of the right wing main beam, and the right wing rear wall is detachably connected to the right wing root rib;

the left wing girder and the right wing girder are detachably connected between the front bulkhead and the rear bulkhead of the fuselage, the left wing root rib and the right wing root rib are detachably connected with a left wing platform rib and a right wing platform rib respectively, and two ends of the left wing platform rib and two ends of the right wing platform rib are detachably fixed on the rear bulkhead and the rear bulkhead of the fuselage respectively.

The utility model is further provided with: the left wing main beam is fixedly connected with the left wing root rib, the left wing rear wall is fixedly connected with the left wing root rib through high-strength bolts, and the left wing front edge is fixedly connected with the left wing main beam, the left wing platform rib is fixedly connected with the rear bulkhead and the tail frame of the fuselage, and the right wing platform rib is fixedly connected with the rear bulkhead and the tail frame of the fuselage through adhesive.

The utility model is further provided with: the left wing girder and the right wing girder are integrally formed by integrally curing carbon fiber composite materials, and the roots of the left wing girder and the right wing girder are of wedge-shaped structures and are rectangular hollow sections.

The utility model is further provided with: the left wing assembly further comprises a left wing long bushing, a left wing short bushing and two left bushing anti-drop nuts, wherein long perforations for the left wing long bushing to pass through and short perforations for the left wing short bushing to pass through are respectively formed in the thick end and the thin end of the root of the left wing girder.

The utility model is further provided with: and after the long left wing bushing and the short left wing bushing are smeared with structural adhesive on the outer wall and are respectively inserted into the long through hole and the short through hole, the left bushing anti-drop nut is fixed on the ends of the long left wing bushing and the short left wing bushing in a threaded manner.

The utility model is further provided with: the right wing assembly further comprises a right wing long bushing, a right wing short bushing, a right bushing anti-drop nut, a long perforation for the right wing long bushing to pass through and a short perforation for the right wing short bushing to pass through, and the fixing mode of the right wing long bushing (107) and the right wing short bushing (108) is the same as the fixing mode of the left wing long bushing (207) and the left wing short bushing (208).

The utility model is further provided with: the fuselage subassembly still includes two bulkhead bush anticreep nuts and two fuselage bulkhead bushes that the symmetry set up, the preceding bulkhead of fuselage with the bulkhead behind the fuselage all is equipped with supplies two bulkhead perforation of fuselage bulkhead bush cross-under.

The utility model is further provided with: after the outer wall of the frame spacer bush is smeared by using structural adhesive and inserted into the frame spacer perforation, the frame spacer bush anti-drop nut is fixed at the end part of the frame spacer bush in a threaded manner.

The utility model is further provided with: the fuselage subassembly still includes two locking round pins, two safety pins, and two locking round pins all are equipped with the confession the tip hole that the safety pin pegged graft, left side wing girder with the wedge root dislocation of right side wing girder is fixed, two locking round pin axle passes in proper order behind the preceding bulkhead of fuselage left side wing girder right side wing girder reaches behind the fuselage bulkhead, two the safety pin passes two respectively the tip hole.

The utility model is further provided with: the left wing assembly further comprises a left rear wall pin, the right wing assembly further comprises a right rear wall pin, the left rear wall pin and the right rear wall pin are respectively fixed on the left wing root rib and the right wing root rib in a threaded mode, and the left wing platform rib and the right wing platform rib are respectively provided with insertion holes for inserting the left rear wall pin and the right rear wall pin.

In summary, the utility model has the following beneficial effects:

the utility model provides a novel reliable main girder arrangement form and a wing body connection mode for a medium-sized and large-sized unmanned aerial vehicle, two main girders are connected with a frame in a penetrating way by adopting pin shafts when being staggered, and are locked by using safety pins, so that the whole process of disassembly and assembly is visible, the wings can be disassembled and assembled quickly without auxiliary tools, the installation structure is safe and reliable, and the installation and the disassembly are convenient;

the hollow rectangular pipe wing girder adopts an integrated molding mode, and solves the problem of strength defect which is possibly caused by virtual adhesion in the original secondary mold closing technology.

The bending moment born by the wing single-side girder is maximum when the wing single-side girder passes through the first pin shaft, the bending moment is gradually reduced to zero in the process of passing through the second pin shaft, the compression/tensile stress born by the upper and lower edge strips of the girder is reduced along with the bending moment, the upper and lower edge strips of the girder are specially cut according to the stress characteristics, the occupation space of the girder in front and back is reduced, the cross section area of the rectangular girder is reduced, and the material is matched with the stress born by the rectangular girder, so that the characteristics of the material are fully utilized;

according to the utility model, the metal bushing structure with wear-resistant property is arranged at the opening part of the mounting pin shaft, the pin shaft is directly contacted and extruded with the bushing, and the bushing is in transition fit with the bulkhead and the beam web, so that the diameter of a hole on the composite web is increased, the hole edge stress caused by stress concentration is reduced, and meanwhile, the abrasion of the composite material caused by the direct contact of the pin shaft and the composite material structure is prevented.

Drawings

FIG. 1 is a block diagram of an integrally formed main beam (gradually shrinking from the root of a rectangular section to the tip of a C-shaped section) in an embodiment of the utility model;

FIG. 2 is a top view of a fuselage connection in an embodiment of the present utility model (this view shows the skin removed from the mask);

FIG. 3 is an exploded view of an airfoil bushing assembly (assembly relationship of the bushing assembly on the airfoil main beam) in accordance with an embodiment of the utility model;

FIG. 4 is an exploded view of a fuselage liner assembly and pin assembly (liner mounting relationship on the fuselage bulkhead and pin assembly relationship, the view omitting the fuselage skin and stringers) in accordance with an embodiment of the present utility model;

FIG. 5 is a schematic view of shear and bending moment experienced by the root of the left wing spar in an embodiment of the present utility model.

In the figure: 1. a right wing assembly; 101. the front edge of the right root rib; 102. a right wing main beam; 103. a right wing root rib; 104. a right wing rear wall; 105. a right rear wall pin; 106. a right bushing anti-drop nut; 107. a right wing long bushing; 108. a right wing short bushing; 109. long perforations; 1010. short perforations; 2. a left wing assembly; 201. the front edge of the left root rib; 202. a left wing main beam; 203. left wing root rib; 204. left wing rear wall; 205. a left rear wall pin; 206. left bushing anti-drop nut; 207. a left wing long bushing; 208. a left wing short bushing; 3. a fuselage assembly; 301. a fuselage front bulkhead; 302. a fuselage rear bulkhead; 303. left wing platform rib; 304. a right wing platform rib; 305. a fuselage tail frame; 306. spacer bush anti-drop nut; 307. a fuselage bulkhead bushing; 308. locking the pin shaft; 309. safety pins; 3010. perforating the partition frame; 3011. an end hole; 3012. a jack; 4. a first rotating shaft; 5. and a second rotating shaft.

Detailed Description

In order that those skilled in the art will better understand the present utility model, a more particular description of the utility model will be rendered by reference to specific embodiments thereof which are illustrated in the appended drawings, wherein it is to be understood that the illustrated embodiments are merely exemplary of some, but not all, of the utility model. All other embodiments, which can be made by those skilled in the art based on the embodiments of the present utility model without making any inventive effort, shall fall within the scope of the present utility model.

It should be noted that, without conflict, the embodiments of the present utility model and features of the embodiments may be combined with each other. The present utility model will be described in detail with reference to examples.

Examples:

as shown in fig. 1 to 5, an unmanned aerial vehicle wing girder and a quick-dismantling structure thereof comprise a right wing assembly 1, a left wing assembly 2 and a fuselage assembly 3;

the right wing assembly 1 comprises a right root rib front edge 101, a right wing main beam 102, a right wing root rib 103, a right wing rear wall 104, a right rear wall pin 105, a right bushing anti-drop nut 106, a right wing long bushing 107 and a right wing short bushing 108;

the left wing assembly 2 comprises a left root rib front edge 201, a left wing main beam 202, a left wing root rib 203, a left wing rear wall 204, a left rear wall pin 205, a left bushing anti-disengaging nut 206, a left wing long bushing 207 and a left wing short bushing 208;

the left wing girder 202 and the right wing girder 102 are integrally formed by integrally curing carbon fiber composite materials, the roots of the left wing girder 202 and the right wing girder 102 are of wedge-shaped structures and are rectangular hollow sections, and the slightly parts are C-shaped sections;

the thick end and the thin end of the wedge-shaped root of the left wing girder 202 and the right wing girder 102 are respectively provided with a long perforation 109 and a short perforation 1010, and after the left wing long bushing 207 and the left wing short bushing 208 are coated on the outer wall by using structural adhesive and respectively inserted into the long perforation 109 and the short perforation 1010, the left bushing anti-falling nut 206 is used for locking, so that the left wing long bushing 207 and the left wing short bushing 208 are prevented from falling off; the right wing assembly 1 is connected with the left wing assembly;

the fuselage assembly 3 comprises a front fuselage bulkhead 301, a rear fuselage bulkhead 302, a left wing rib 303, a right wing rib 304, a tail fuselage frame 305, a bulkhead bushing anti-disengaging nut 306, a fuselage bulkhead bushing 307, a locking pin 308, and a safety pin 309;

high-strength bolts are used for fastening connection between the left wing main beam 202 and the left wing root rib 203, between the left wing rear wall 204 and the left wing root rib 203, and adhesive connection is used for the left root rib front edge 201 and the left wing main beam 202, the left wing platform rib 303 and the rear frame 302 of the fuselage, the left wing platform rib 303 and the tail frame 305 of the fuselage, the right wing platform rib 304 and the rear frame 302 of the fuselage, and the right wing platform rib 304 and the tail frame 305 of the fuselage.

The front bulkhead 301 and the rear bulkhead 302 are respectively provided with two bulkhead perforations 3010 through which the bulkhead bushing 307 of the fuselage is connected, and after the bulkhead bushing 307 of the fuselage is coated with structural adhesive and inserted into the bulkhead perforation 3010, the bulkhead bushing anti-drop nut 306 is screwed on the end of the bulkhead bushing 307 of the fuselage to lock.

The left wing main beam, the right wing main beam 102, the left wing root rib 203, the right wing root rib 103, the left root rib front edge 201 and the right root rib front edge 101 are assembled and then are externally glued with the skin in a die-closing manner, so that a structural closed chamber is formed to transfer loads on the wing to the fuselage spacer.

The fuselage structure at the connection of the wing body is correspondingly designed, fuselage bulkhead bushings 307 are arranged on the fuselage front bulkhead 301 and the fuselage rear bulkhead 302, the bulkhead bushing anti-disengaging nuts 306 are used for locking, the rear ends of the left wing root rib 203 and the right wing root rib 103 are respectively provided with a left rear wall pin 205 and a right rear wall pin 105, the left wing platform rib 303 and the right wing platform rib 304 are respectively provided with an inserting hole 3012 for inserting the left rear wall pin 205 and the right rear wall pin 105, and the fuselage front bulkhead 301, the fuselage rear bulkhead 302, the fuselage tail bulkhead 305, the left wing platform rib 303, the right wing platform rib 304 and the fuselage stringer form a main structural frame of the fuselage, and the exterior and the fuselage skin are assembled to form the whole fuselage structure.

When the wing bodies are connected, the roots of the left wing girder 202 and the right wing girder 102 are inserted between the front bulkhead 301 and the rear bulkhead 302 of the fuselage, and the wedge-shaped dislocation of the roots of the left wing girder 202 and the right wing girder 102 enables the difference of the station positions of the left wing girder and the right wing girder in the chord direction to be smaller, so that the symmetry of the left wing and the right wing after being subjected to pneumatic load is basically not influenced. When the left back wall pin 205 and the right back wall pin 105 are inserted into the two insertion holes 3012 at the same time, after the left wing and the right wing are installed in place, the locking pin 308 sequentially passes through the front bulkhead 301 of the fuselage, the main beam 202 of the left wing, the main beam 102 of the right wing and the rear bulkhead 302 of the fuselage, and then passes through the end holes 3011 of the pins to be locked by using the safety pin 309, or is connected by using a quick-release pin.

When the left wing girder 202 and the right wing girder 102 are staggered, the bending moment born by the left wing girder 202 gradually increases inwards from the wing tip to reach the first rotating shaft 4, and then gradually decreases until the second rotating shaft 5 is reduced to 0, the change of the compression/tensile stress born by the upper/lower edge strips of the girder caused by the bending moment is the same as the change of the bending moment, the width of the upper/lower edge strips of the girder is also changed along with the change of the bending moment between the first rotating shaft 4 and the second rotating shaft 5, the external dimension of the part is better matched with the born load, and the performance of the material is fully utilized.

In this connection, the left and right wing girders 202 and 102 are mainly subjected to the shearing forces and bending moments transmitted from the entire wing, while the left and right rear wall pins 205 and 105 are mainly subjected to the shearing forces generated by torsion in the pitch direction of the wing surface and the shearing forces generated by a part of the wing. The locking pin 308 limits the wing displacement in the spanwise direction and the left and right rear wall pins 205, 105 limit the wing movement along the fuselage axis.

The wing main beam bearing form is a typical double-pivot external extension beam structure, the distance between two fulcrums is larger, and the supporting reaction force born by the fulcrums and generated by the wing bending moment is greatly reduced.

In addition, in the whole wing body connection process, after the upper part flap of the fuselage is opened, the wing girder mounting hole is visually inspected, so that the adjustment of wing mounting is facilitated, and the difficulty of the mounting process is reduced.

The present embodiment is only for explanation of the present utility model and is not to be construed as limiting the present utility model, and modifications to the present embodiment, which may not creatively contribute to the present utility model as required by those skilled in the art after reading the present specification, are all protected by patent laws within the scope of claims of the present utility model.

Claims (10)

1. An unmanned aerial vehicle wing girder and quick detach structure thereof, characterized by: the wing system comprises a right wing assembly (1), a left wing assembly (2) and a fuselage assembly (3), wherein the right wing assembly (1) comprises a right root rib front edge (101), a right wing main beam (102), a right wing root rib (103) and a right wing rear wall (104); the left wing assembly (2) comprises a left root rib front edge (201), a left wing main beam (202), a left wing root rib (203) and a left wing rear wall (204); the fuselage assembly (3) comprises a fuselage front bulkhead (301), a fuselage rear bulkhead (302), a left wing platform rib (303), a right wing platform rib (304) and a fuselage tail frame (305);

the left wing root rib (203) and the left root rib front edge (201) are respectively and detachably connected to two sides of the left wing main beam (202), and the left wing rear wall (204) is detachably connected to the left wing root rib (203); the right wing root rib (103) and the right root rib front edge (101) are respectively and detachably connected to two sides of the right wing main beam (102), and the right wing rear wall (104) is detachably connected to the right wing root rib (103);

left wing girder (202) with right wing girder (102) can dismantle connect in before the fuselage spacer frame (301) with between spacer frame (302) behind the fuselage, left wing root rib (203) with right wing root rib (103) can be dismantled respectively and be connected with left wing platform rib (303) and right wing platform rib (304), left wing platform rib (303) with right wing platform rib (304) both ends can be dismantled respectively and be fixed in behind the fuselage spacer frame (302) with fuselage tail frame (305).

2. The unmanned aerial vehicle wing girder and quick release structure thereof according to claim 1, wherein: the left wing main beam (202) and the left wing root rib (203), the left wing rear wall (204) and the left wing root rib (203) are all fastened and connected by using high-strength bolts, the left root rib front edge (201) and the left wing main beam (202), the left wing platform rib (303) and the fuselage rear bulkhead (302), the left wing platform rib (303) and the fuselage tail bulkhead (305), the right wing platform rib (304) and the fuselage rear bulkhead (302), and the right wing platform rib (304) and the fuselage tail bulkhead (305) are all connected by using adhesives.

3. The unmanned aerial vehicle wing girder and quick release structure thereof according to claim 1, wherein: the left wing girder (202) and the right wing girder (102) are integrally formed by integrally curing carbon fiber composite materials, the roots of the left wing girder (202) and the right wing girder (102) are of wedge-shaped structures and are rectangular hollow sections, and the slightly parts of the left wing girder (202) and the right wing girder (102) are C-shaped sections.

4. The unmanned aerial vehicle wing girder and quick release structure thereof according to claim 3, wherein: the left wing assembly (2) further comprises a left wing long bushing (207), a left wing short bushing (208) and two left bushing anti-disengaging nuts (206), and a thick end and a thin end of the root of the left wing main beam (202) are respectively provided with a long perforation (109) for the left wing long bushing (207) to penetrate through and a short perforation (1010) for the left wing short bushing (208) to penetrate through.

5. The unmanned aerial vehicle wing girder and quick release structure thereof according to claim 4, wherein: after the left wing long bushing (207) and the left wing short bushing (208) are coated on the outer wall by using structural adhesive and are respectively inserted into the long perforation (109) and the short perforation (1010), two left bushing anti-drop nuts (206) are respectively fixed at the ends of the left wing long bushing (207) and the left wing short bushing (208) in a threaded mode.

6. The unmanned aerial vehicle wing girder and quick release structure thereof according to claim 5, wherein: the right wing assembly (1) further comprises a right wing long bushing (107), a right wing short bushing (108), a right bushing anti-drop nut (106), long perforations (109) for the right wing long bushing (107) to be connected in a penetrating manner and short perforations (1010) for the right wing short bushing (108) to be connected in a penetrating manner, and the fixing modes of the right wing long bushing (107) and the right wing short bushing (108) are the same as the fixing modes of the left wing long bushing (207) and the left wing short bushing (208).

7. The unmanned aerial vehicle wing girder and quick release structure thereof according to claim 6, wherein: the fuselage subassembly (3) still includes two bulkhead bushing anticreep nuts (306) and two fuselage bulkhead bushings (307) that the symmetry set up, preceding bulkhead (301) of fuselage with bulkhead (302) behind the fuselage all are equipped with supplies two bulkhead perforation (3010) of fuselage bulkhead bushing (307) cross-under.

8. The unmanned aerial vehicle wing girder and quick release structure thereof according to claim 7, wherein: after the outer wall of the bulkhead bushing (307) is smeared by structural adhesive and inserted into the bulkhead perforation (3010), the bulkhead bushing anti-disengaging nut (306) is fixed on the end part of the bulkhead bushing (307) in a threaded manner.

9. The unmanned aerial vehicle wing girder and quick release structure thereof according to claim 8, wherein: the fuselage subassembly (3) still includes two locking round pins (308), two insurance pins (309), and two locking round pins (308) all are equipped with supplies the tip hole (3011) of insurance pin (309) grafting, left wing girder (202) with wedge root dislocation of right wing girder (102) is fixed, two locking round pins (308) pass in proper order before fuselage bulkhead (301) left wing girder (202) right wing girder (102) reaches behind fuselage bulkhead (302), two insurance pins (309) pass two respectively tip hole (3011).

10. The unmanned aerial vehicle wing girder and quick release structure thereof according to claim 1, wherein: left wing subassembly (2) still include left back wall pin (205), right side wing subassembly (1) still include right back wall pin (105), left back wall pin (205) with right back wall pin (105) screw thread respectively fixed in left wing root rib (203) with right wing root rib (103), left wing platform rib (303) with right wing platform rib (304) are equipped with respectively supplies left back wall pin (205) with jack (3012) that right back wall pin (105) pegged graft.