CN113353243B - Self-wing-changing multifunctional unmanned aerial vehicle logistics vehicle - Google Patents
Self-wing-changing multifunctional unmanned aerial vehicle logistics vehicle Download PDFInfo
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/54—Varying in area
- B64C3/546—Varying in area by foldable elements
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60F—VEHICLES FOR USE BOTH ON RAIL AND ON ROAD; AMPHIBIOUS OR LIKE VEHICLES; CONVERTIBLE VEHICLES
- B60F5/00—Other convertible vehicles, i.e. vehicles capable of travelling in or on different media
- B60F5/02—Other convertible vehicles, i.e. vehicles capable of travelling in or on different media convertible into aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
- B64C25/62—Spring shock-absorbers; Springs
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C37/00—Convertible aircraft
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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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/10—Wings
- B64U30/12—Variable or detachable wings, e.g. wings with adjustable sweep
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
- B64U2101/60—UAVs specially adapted for particular uses or applications for transporting passengers; for transporting goods other than weapons
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The application discloses a self-wing-changing multifunctional unmanned aerial vehicle logistics vehicle, and belongs to the technical field of unmanned aerial vehicle transportation. The folding wing comprises a body, a folding main wing body, a telescopic winglet, an aileron, a landing gear, a rear body frame, a horizontal tail and a vertical tail, wherein the folding main wing is arranged on two sides of the body, the telescopic winglet is arranged in the folding main wing, the aileron is arranged on the downside of the telescopic winglet, the landing gear is arranged on the bottom of the body, the rear body frame is arranged on the rear body frame, the horizontal tail is connected on the rear body frame, and the vertical tail is arranged on two sides of the horizontal tail. The application has the functions of folding and extending the wing, has quick transportation and large bearing capacity, and can adapt to various transportation working conditions.
Description
Technical Field
The application relates to the technical field of unmanned aerial vehicle transportation, in particular to a self-wing-changing multifunctional unmanned aerial vehicle logistics vehicle.
Background
With the wide-range rise of online shopping, the proportion of people shopping on the internet rises sharply, and the demands on the speed, accuracy and the like of goods transportation are higher in the face of the sharply rising online purchasing power, so that the goods transportation capability faces a great challenge. In order to solve the problem of difficult cargo transportation in remote areas away from urban transportation, a logistics transport vehicle which is rapid, large in bearing capacity and suitable for various transportation conditions is needed.
The patent document with the publication number of CN 110588981A discloses unmanned aerial vehicle with high stability for logistics transportation, which comprises a main body, two support frames and two flying devices, be equipped with elevating system and fixed establishment in the main body, elevating system includes lifter plate, camera and two lifting assembly, lifting assembly includes slide, expansion bracket, guide bar, two racks, two movable blocks, two drive assembly and two sliders, fixed establishment includes connecting box, power component, two sucking discs and two connecting pipes, and this unmanned aerial vehicle with high stability for logistics transportation can carry out identity verification to getting the person, has reduced the probability of goods transportation error, has improved unmanned aerial vehicle's security, through fixed establishment, has realized the function to goods are fixed, avoids taking place to rock the collision and damage during the goods transportation. However, the unmanned aerial vehicle has limited load carrying capacity and a single function.
The patent document with publication number of CN 109625284A discloses a high-efficient unmanned aerial vehicle that flies steadily for logistics distribution, which comprises a main body, a plurality of conveyer and a plurality of flight mechanism, conveyer includes adjustment mechanism, regulating plate and transport mechanism, adjustment mechanism includes the connecting rod, the rotor plate, rotating assembly and translation subassembly, translation subassembly includes first motor, a bearing, lead screw and translation piece, transport mechanism includes the detection subassembly, the pick-up plate, lifting unit, lifting plate, air pump and a plurality of fixed subassembly, fixed subassembly includes the cylinder, a piston, the riser, bottom plate and fixed unit, this high-efficient unmanned aerial vehicle that flies steadily for logistics distribution is convenient for the loading and unloading of goods through transport mechanism, the equipment of being convenient for once only carries the transportation of many goods, improve logistics distribution efficiency, not only, through the weight adjustment mechanism control regulating plate's of detecting goods position, thereby the focus of adjustment equipment is located the central axis of main body, the equipment of being convenient for carries out steady flight, the practicality of equipment has been improved. However, the present application also fails to solve the above-described problems.
Disclosure of Invention
In view of the above, the application provides the self-changing wing multifunctional unmanned aerial vehicle logistics vehicle which is rapid, has large bearing capacity and can adapt to various transportation working conditions.
In order to solve the technical problems, the application adopts the following technical scheme: the utility model provides a from multi-functional unmanned aerial vehicle commodity circulation car of variable wing, includes fuselage, folding main wing, flexible winglet, aileron, undercarriage, back fuselage frame, horizontal tail and vertical tail, the fuselage both sides all set up folding main wing, set up in the folding main wing flexible winglet, flexible winglet downside sets up the aileron, the fuselage bottom sets up the undercarriage, the fuselage rear portion sets up back fuselage frame, connect on the back fuselage frame the horizontal tail, horizontal tail both sides all set up the vertical tail.
Further, folding main wing includes main wing and folding actuating mechanism, folding actuating mechanism includes first steering wheel, first drive gear, gear shaft, carbon tube, first gear, second gear, wing connecting piece and fuselage connection fastener, set up on the output shaft of first steering wheel first drive gear, first drive gear with gear shaft connection transmission, the gear shaft both ends all set up first gear, the carbon tube passes through the fuselage connection fastener with the fuselage is connected, the carbon tube both ends all set up the second gear, first gear and second gear connection transmission, the carbon tube pass through the wing connecting piece with the main wing is connected.
Further, the telescopic winglet comprises a telescopic actuating mechanism, a connecting rod mechanism and a plurality of wing plates, wherein the telescopic actuating mechanism is of a gear rack structure or a three-section rocker structure, the connecting rod mechanism comprises a plurality of X-shaped connecting rods, two adjacent X-shaped connecting rods are mutually hinged, the wing plates are uniformly distributed in the X-shaped connecting rods which are mutually hinged, strip-shaped holes are formed in the wing plates, upper hinge points of the two adjacent X-shaped connecting rods penetrate through the strip-shaped holes, the lower ends of the two adjacent X-shaped connecting rods are respectively hinged to two sides of the wing plates, and rollers and positioning blocks are respectively arranged on the two X-shaped connecting rods at two ends; the X-shaped connecting rod comprises a first connecting rod and a second connecting rod, wherein the middle parts of the first connecting rod and the second connecting rod are mutually hinged.
Further, the rack and pinion structure comprises a second steering engine, a second transmission gear and a rack, wherein the second transmission gear is arranged on an output shaft of the second steering engine, the rack is arranged on the upper portion of one roller, and the rack is connected with the second transmission gear for transmission.
Further, the three-section rocker structure comprises a second steering engine, a rocker, a straight rod, a limiting block and a connecting piece, wherein the rocker comprises a first rod body and a second rod body, the end parts of the first rod body are hinged, the first rod body is fixedly connected with a rotating shaft of the second steering engine, the second rod body is hinged with the straight rod, the limiting block is arranged on the wing plate, a through hole is formed in the limiting block, the straight rod penetrates through the through hole, and the end part of the straight rod is connected with one of the idler wheels through the connecting piece.
Further, the number of the machine body connecting fasteners is two, the two machine body connecting fasteners are respectively arranged on two sides of the wing connecting piece, the two ends of the gear shaft are respectively provided with a coupler, the couplers are positioned on the outer side of the first gear, one side of the lower portion of the machine body connecting fastener is connected with the couplers, and the other side of the lower portion of the machine body connecting fastener is connected with the machine body through bolts.
Further, the horizontal tail comprises a horizontal stabilizer and an elevator, and the elevator is arranged at the rear side of the horizontal stabilizer; the vertical fin comprises a vertical stabilizer and a rudder, and the rudder is arranged at the rear side of the vertical stabilizer.
Further, a supporting reinforcing structure is arranged inside the main wing, the supporting reinforcing structure comprises a plurality of supporting plates and a plurality of diamond-shaped connecting rods, and two adjacent supporting plates are connected through one diamond-shaped connecting rod.
Further, the landing gear comprises a front landing gear and a rear landing gear, the front landing gear comprises a third steering engine, a third transmission gear, steering connecting rods, transmission racks, gear fixing seats, a first landing frame seat, first wheels and first damping mechanisms, the first wheels are arranged on two sides of the first landing frame seat, the gear fixing seats are arranged in the middle of the first landing frame seat, the third steering engine is arranged on the gear fixing seats, the third transmission gear is arranged on an output shaft of the third steering engine, the third transmission gear is connected with the transmission racks for transmission, the two ends of the transmission racks are connected with the steering connecting rods, the two steering connecting rods are respectively connected with the two first wheels, and the two first damping mechanisms are arranged on the first landing frame seat; the rear landing gear comprises a second landing frame seat, second wheels and second damping mechanisms, wherein the second wheels are arranged on two sides of the second landing frame seat, and the second landing frame seat is provided with the two second damping mechanisms; the first damping mechanism and the second damping mechanism which are positioned on the same side are connected through a carbon fiber tube.
Further, the first damping mechanism and the second damping mechanism are identical in structure and comprise a connecting block, a damping spring, a damping connecting rod, a damping fixing buckle and a damping fixing shaft, the damping fixing shaft is arranged below the connecting block, the lower end of the damping fixing shaft is fixed on a lifting frame seat, the damping spring is sleeved on the damping fixing shaft, the upper end and the lower end of the damping spring are respectively provided with the damping fixing buckle, the side faces of the damping fixing buckle are hinged to one damping connecting rod, and the two damping connecting rods are hinged to each other.
Along with unmanned aerial vehicle technique's rapid development, also receive extensive attention with its unmanned logistics car of being applied to logistics transportation field, this industry technician is when researching and developing unmanned logistics car, and the stability that improves logistics car is usually considered in order to protect article safety, and an unmanned aerial vehicle that is used for the reliability of commodity circulation is high as disclosed in publication No. CN 109795695A China patent document, including main part, carrying thing case and four rotors, the rotor sets up the top at the main part, be equipped with drive arrangement in the main part, drive arrangement is connected with the rotor transmission, the vertical cross-section shape of carrying the thing case is the U-shaped, the opening of carrying the U-shaped cross-section of thing case sets up, the shape of carrying the thing case is cylindrical, carry thing case vertical setting, carry the thing case setting in the bottom of main part, carry the incasement to be equipped with buffer gear, carry and be equipped with two coupling mechanism on the thing case, two coupling mechanism set up respectively in the both sides of carrying the thing case, this unmanned aerial vehicle that the reliability is high passes through buffer gear and realizes the buffering effect of article to the main part, has avoided if the reliability is not to improve the connection with the stability and has improved. As another example, the patent document in publication CN 109677617A discloses a stable unmanned flying transport device for logistics distribution, including main part and two at least flight mechanisms, still include and prevent splashing mechanism and strengthening mechanism, prevent splashing mechanism includes go-between, storage tank, two backup pads, two head bars, two first bearing frames, two second connecting bars and two second bearing frames, strengthening mechanism includes two guide rails and two clamping assemblies, clamping assemblies includes grip block, drive unit, slide bar, two sliders, two sliding sleeve pipes, two transfer lines and two springs, in this stable unmanned flying transport device for logistics distribution, through preventing splashing mechanism, make unmanned aerial vehicle be in vertical state all the time at the in-process storage tank that rocks, thereby reduced the probability that liquid cargo splashes to take place, through the removal of strengthening mechanism drive two grip blocks, thereby improved the stability of cargo under the centre gripping effect of two grip blocks, reduced the probability that the cargo damaged takes place. Therefore, the unmanned aerial vehicle logistics vehicle designed by the application can adapt to different transportation conditions by folding or stretching, walking or flying while ensuring transportation stability, and improves logistics flexibility and rapidness, which is not easy to think of a person skilled in the art.
Compared with the prior art, the application has the following beneficial effects:
the self-wing-changing multifunctional unmanned aerial vehicle logistics vehicle disclosed by the application adopts land and air dual-purpose, can complete transportation under more complex working conditions, has functions of folding and stretching wings, and has the advantages of quick execution, small placing area of an aircraft, large cargo carrying capacity, good stability, light weight and the like. The application has two postures, wherein the first posture is that when the wings are retracted, the wing can be used as a cargo trolley, has flexible steering function when on the ground, and has shock absorption effect when facing to a complex road landing gear. The second type gesture is when the wing is expanded, can regard as unmanned aerial vehicle to use this moment, and unmanned aerial vehicle adopts fixed wing aircraft, and transport speed is fast, and the traffic is big, and the vertical tail is two tail that stand, and stability is better. The application has three modes of expansion, telescopic and telescopic folding, and can freely switch different modes to solve different kinds of transportation problems in the face of multiple conditions such as large transportation capacity, complex road conditions and the like.
In addition, the folding main wing is connected with the folding executing mechanism by adopting gear transmission, and the gear transmission has the advantages of high reliability, large bearing capacity, accurate transmission ratio, long service life and the like, and the carbon tube is driven to axially rotate by two-stage transmission, so that the wing folding function is realized.
In addition, the telescopic winglet disclosed by the application has the advantages that the telescopic actuating mechanism drives the wing plates to move through the connecting rod mechanism, so that the telescopic actuating mechanism is telescopic, the telescopic actuating mechanism adopts two mechanism designs, the first design is in a gear-rack structure, and the second type is in a rocker structure; the gear rack structure is connected with the gear rack, the steering engine is axially and rotationally controlled through the aircraft controller, so that the transverse motion of the rack along the X axis is realized, and the pulley is pushed to transversely move to enable the connecting rod in the telescopic winglet to perform telescopic motion along the Y axis; the three-section rocker structure adopts steering engine control, and the steering engine rotates clockwise along the XZ plane to drive the rocker and the straight rod to move forward along the X-axis direction and drive the roller to move cooperatively, so that the X-shaped connecting rod contracts, otherwise, the X-shaped connecting rod can expand, and the mechanism is simple to execute and easy to manufacture. The telescopic winglet disclosed by the application has the advantages that the wing load is carried in a distributed manner after being unfolded, and the bearing performance is good; a plurality of X-shaped connecting rods are adopted, so that the telescopic distance is long; the roller wheels are arranged at two ends of the connecting rod structure, the telescopic execution resistance is small, the rapid execution of telescopic movement can be guaranteed, the clamping phenomenon can not happen, the rapid execution and the continuity of the telescopic movement have great influence on the vibration of the winglet deformation wing, the excellent performance of the rapid execution and the continuity of the telescopic movement can reduce the vibration of the winglet deformation wing to the minimum, and therefore the stability of the winglet in the flying process is enhanced.
Drawings
FIG. 1 is a schematic diagram of the structure of the present application;
FIG. 2 is a schematic view of the connection structure of the folding main wing, the telescopic winglet and the aileron of the present application;
FIG. 3 is a schematic structural view of a folding main wing of the present application;
FIG. 4 is a schematic view of the structure of the telescopic airfoil of the present application;
FIG. 5 is a partial schematic view of the connection of the folding main wing to the fuselage of the present application;
FIG. 6 is a schematic view of the structure of the linkage mechanism of the present application;
FIG. 7 is a schematic view of the rack and pinion construction of the present application;
FIG. 8 is a schematic view of the structure of the horizontal tail of the present application;
FIG. 9 is a schematic view of the structure of the vertical fin of the present application;
FIG. 10 is a schematic illustration of the connection of the linkage mechanism to a three-section rocker structure of the present application;
FIG. 11 is a schematic illustration of a three-section rocker structure of the present application;
FIG. 12 is a schematic view of the structure of the support reinforcing structure of the present application;
FIG. 13 is a schematic view of the internal structure of a main wing of the present application;
FIG. 14 is a schematic view of the structure of the nose landing gear of the present application;
FIG. 15 is a schematic view of the construction of the landing gear of the present application;
fig. 16 is an enlarged view of a portion a in fig. 14.
Detailed Description
For a better understanding of the present application, the following examples are set forth to further illustrate the application, but are not to be construed as limiting the application. In the following description, numerous specific details are set forth in order to provide a more thorough understanding of the present application. It will be apparent, however, to one skilled in the art that the application may be practiced without one or more of these details.
Example 1
As shown in fig. 1-9, a self-variable wing multifunctional unmanned aerial vehicle logistics vehicle comprises a body 1, a folding main wing 2, a telescopic winglet 3, an aileron 4, landing gears 5, a rear fuselage frame 6, a horizontal tail 7 and a vertical tail 8, wherein the folding main wing 2 is arranged on two sides of the body 1, the telescopic winglet 3 is arranged on the lower side of the telescopic winglet 3, the aileron 4 is arranged on the bottom of the body 1, the landing gears 5 are arranged on the rear portion of the body 1, the rear fuselage frame 6 is connected with the horizontal tail 7, and the vertical tail 8 is arranged on two sides of the horizontal tail 7.
The folding main wing 2 comprises a main wing 21 and a folding executing mechanism, the folding executing mechanism comprises a first steering engine 22, a first transmission gear 23, a gear shaft 24, a carbon tube 25, a first gear 26, a second gear 27, a wing connecting piece 28 and a body connecting fastener 29, the first transmission gear 23 is arranged on an output shaft of the first steering engine 22, the first transmission gear 23 is in connection transmission with the gear shaft 24, the first gears 26 are arranged at two ends of the gear shaft 24, the carbon tube 25 is connected with the body 1 through the body connecting fastener 29, the second gears 27 are arranged at two ends of the carbon tube 25, the first gears 26 are in connection transmission with the second gears 27, and the carbon tube 25 is connected with the main wing 21 through the wing connecting piece 28.
The number of the body connecting fasteners 29 is two, the two body connecting fasteners are respectively arranged on two sides of the wing connecting piece 28, the two ends of the gear shaft 24 are respectively provided with a coupler 241, the couplers 241 are positioned on the outer side of the first gear 26, one side of the bottom of the body connecting fasteners 29 is connected with the couplers 241, and the other side of the bottom of the body connecting fasteners 29 is connected with the body 1 through bolts.
The telescopic winglet 3 comprises a telescopic actuating mechanism, a connecting rod mechanism and a plurality of wing plates 31, wherein a skin is arranged on the plurality of wing plates 31, the telescopic actuating mechanism is of a gear-rack structure, the connecting rod mechanism comprises a plurality of X-shaped connecting rods 32, two adjacent X-shaped connecting rods 32 are mutually hinged, the plurality of wing plates 31 are uniformly distributed in the plurality of X-shaped connecting rods 32 which are mutually hinged, strip-shaped holes 33 are arranged on the wing plates 31, upper hinge points of the two adjacent X-shaped connecting rods 32 penetrate through the strip-shaped holes 33, the lower ends of the two adjacent X-shaped connecting rods 32 are respectively hinged to two sides of the wing plates 31, and rollers 34 and positioning blocks 35 are arranged on the two X-shaped connecting rods 32 positioned at two ends; the X-shaped link 32 includes a first link and a second link hinged to each other at the middle.
The gear rack structure comprises a second steering engine 36, a second transmission gear 37 and a rack 38, wherein the second transmission gear 37 is arranged on an output shaft of the second steering engine 36, the rack 38 is arranged on the upper portion of one roller 34, and the rack 38 is connected with the second transmission gear 37 for transmission.
The horizontal tail 7 comprises a horizontal stabilizer 71 and an elevator 72, and the elevator 72 is arranged at the rear side of the horizontal stabilizer 71; the vertical fin 8 comprises a vertical stabilizer 81 and a rudder 82, and the rudder 82 is arranged at the rear side of the vertical stabilizer 81.
And establishing a local coordinate system according to the unmanned aerial vehicle logistics vehicle, and assuming a Y axis along the transverse direction of the wing, an X axis perpendicular to the Y axis and parallel to the cross section of the wing, and a Z axis perpendicular to the XY plane. The telescopic actuating mechanism carries out axial rotation control on the second steering engine through the aircraft controller, so that transverse movement of the rack along the X axis is realized, and then the pulley is pushed to transversely move, so that the connecting rod in the telescopic winglet carries out telescopic movement along the Y axis.
Example two
As shown in fig. 10 to 11, the self-wing-changing multifunctional unmanned aerial vehicle logistics vehicle in the embodiment of the application is different from the first embodiment in that:
the three-section rocker structure comprises a second steering engine 41, a rocker 42, a straight rod 43, a limiting block 44 and a connecting piece 45, wherein the rocker 42 comprises a first rod body 421 and a second rod body 422, the end parts of the first rod body 421 are hinged, the first rod body 421 is fixedly connected with a rotating-out shaft of the second steering engine 41, the second rod body 422 is hinged with the straight rod 43, the limiting block 44 is arranged on the wing plate 31, a through hole is formed in the limiting block 44, the straight rod 43 penetrates through the through hole, and the end part of the straight rod 43 is connected with one of the rollers 34 through the connecting piece 45.
The telescopic actuating mechanism is controlled by a second steering engine, the second steering engine rotates clockwise along the XZ plane to drive the rocker and the straight rod to move forward along the X-axis direction, and the roller is driven to move forward in a coordinated manner, so that the X-shaped connecting rod is contracted, and the X-shaped connecting rod can be expanded otherwise. The mechanism is simple to execute and easy to manufacture.
Example III
As shown in fig. 12 to 13, the self-wing-changing multifunctional unmanned aerial vehicle logistics vehicle in the embodiment of the application is different from the first embodiment in that:
the main wing is internally provided with a supporting reinforcing structure, the supporting reinforcing structure comprises a plurality of supporting plates 61 and a plurality of diamond-shaped connecting rods 62, and two adjacent supporting plates 61 are connected through one diamond-shaped connecting rod 62.
A carbon fiber pipe 63 is provided to penetrate the plurality of support plates 61.
When the telescopic winglet is considered to be unfolded, the telescopic winglet can extend out of the main wing, so that the hollow phenomenon is generated in the middle of the main wing, the stability design requirement of the unmanned aerial vehicle freight car is not met, the structural design is carried out on the inside of the main wing, the wing load uniform distribution is considered, the service life of the wing is longer, and the support reinforcing structure is adopted, so that the main wing load uniform distribution is realized.
Example IV
As shown in fig. 14 to 16, the self-wing-changing multifunctional unmanned aerial vehicle logistics vehicle in the embodiment of the present application is different from the first embodiment in that:
the landing gear 5 comprises a front landing gear and a rear landing gear, the front landing gear comprises a third steering engine 511, a third transmission gear 512, a steering connecting rod 513, a transmission rack 514, a gear fixing base 515, a first landing frame base 516, first wheels 517 and first damping mechanisms 518, first wheels 517 are arranged on two sides of the first landing frame base 516, the middle part of the first landing frame base 516 is provided with the gear fixing base 515, the gear fixing base 515 is provided with the third steering engine 511, the output shaft of the third steering engine 511 is provided with the third transmission gear 512, the third transmission gear 512 is connected with the transmission rack 514 for transmission, two ends of the transmission rack 514 are connected with the steering connecting rod 513, the two steering connecting rods 513 are respectively connected with the two first wheels 517, and the first landing frame base 516 is provided with the two first damping mechanisms 518; the rear landing gear comprises a second landing gear seat 521, a second wheel 522 and a second damping mechanism 523, wherein the second wheel 522 is arranged on two sides of the second landing gear seat 521, and the two second damping mechanisms 523 are arranged on the second landing gear seat 521; the first damper 518 and the second damper 523 located on the same side are connected by a carbon fiber pipe 524.
The first damping mechanism 518 and the second damping mechanism 523 have the same structure and comprise a connecting block 531, a damping spring 532, a damping connecting rod 533, a damping fixing buckle 534 and a damping fixing shaft 535, the damping fixing shaft 535 is arranged below the connecting block 531, the lower end of the damping fixing shaft 535 is fixed on a lifting frame seat, the damping spring 532 is sleeved on the damping fixing shaft 535, the upper end and the lower end of the damping spring 532 are respectively provided with the damping fixing buckle 534, the side surfaces of the damping fixing buckle 534 are respectively hinged with one damping connecting rod 533, and the two damping connecting rods 533 are mutually hinged.
At least one of the two shock-absorbing fixing buckles 535 can slide on the shock-absorbing fixing shaft 536, and in the embodiment of the present application, the shock-absorbing fixing buckle at the upper part is fixedly connected with the connecting block, and the shock-absorbing fixing buckle at the lower part can move up and down.
Finally, it is noted that the above-mentioned embodiments are merely for illustrating the technical solution of the present application, and that other modifications and equivalents thereof by those skilled in the art should be included in the scope of the claims of the present application without departing from the spirit and scope of the technical solution of the present application.
Claims (1)
1. The utility model provides a from multi-functional unmanned aerial vehicle commodity circulation car of variable wing which characterized in that: the folding main wing is internally provided with the telescopic winglet, the downside of the telescopic winglet is provided with the aileron, the bottom of the main body is provided with the landing gear, the rear part of the main body is provided with the rear fuselage frame, the rear fuselage frame is connected with the horizontal tail, and both sides of the horizontal tail are provided with the vertical tail;
the folding main wing comprises a main wing body and a folding executing mechanism, the folding executing mechanism comprises a first steering engine, a first transmission gear, a gear shaft, a carbon tube, a first gear, a second gear, a wing connecting piece and a main body connecting fastener, the first transmission gear is arranged on an output shaft of the first steering engine, the first transmission gear is in transmission connection with the gear shaft, the first gears are arranged at two ends of the gear shaft, the carbon tube is connected with the main body through the main body connecting fastener, the second gears are arranged at two ends of the carbon tube, the first gears are in transmission connection with the second gears, and the middle part of the carbon tube is connected with the main wing through the wing connecting piece; the number of the machine body connecting fasteners is two, the two machine body connecting fasteners are respectively arranged on two sides of the wing connecting piece, the two ends of the gear shaft are respectively provided with a shaft coupling, the shaft couplings are positioned on the outer sides of the first gears, one side of the lower part of each machine body connecting fastener is connected with the shaft couplings, and the other side of the lower part of each machine body connecting fastener is connected with the machine body through bolts;
the telescopic winglet comprises a telescopic actuating mechanism, a connecting rod mechanism and a plurality of wing plates, wherein the telescopic actuating mechanism is of a gear rack structure, the connecting rod mechanism comprises a plurality of X-shaped connecting rods, two adjacent X-shaped connecting rods are mutually hinged, the wing plates are uniformly distributed in the X-shaped connecting rods which are mutually hinged, strip-shaped holes are formed in the wing plates, upper hinge points of the two adjacent X-shaped connecting rods penetrate through the strip-shaped holes, the lower ends of the two adjacent X-shaped connecting rods are respectively hinged to two sides of the wing plates, and rollers and positioning blocks are arranged on the two X-shaped connecting rods at two ends; the X-shaped connecting rod comprises a first connecting rod and a second connecting rod, wherein the middle parts of the first connecting rod and the second connecting rod are mutually hinged; the gear rack structure comprises a second steering engine, a second transmission gear and a rack, wherein the second transmission gear is arranged on an output shaft of the second steering engine, the rack is arranged on the upper part of one roller, and the rack is connected with the second transmission gear for transmission;
the main wing is internally provided with a supporting reinforcing structure, the supporting reinforcing structure comprises a plurality of supporting plates and a plurality of diamond-shaped connecting rods, two adjacent supporting plates are connected through one diamond-shaped connecting rod, and carbon fiber tubes are arranged on the plurality of supporting plates in a penetrating manner;
the landing gear comprises a front landing gear and a rear landing gear, the front landing gear comprises a third steering engine, a third transmission gear, steering connecting rods, transmission racks, gear fixing seats, a first landing frame seat, first wheels and first damping mechanisms, the first wheels are arranged on two sides of the first landing frame seat, the gear fixing seats are arranged in the middle of the first landing frame seat, the third steering engine is arranged on the gear fixing seats, the third transmission gear is arranged on an output shaft of the third steering engine, the third transmission gear is connected with the transmission racks for transmission, the two ends of the transmission racks are connected with the steering connecting rods, the two steering connecting rods are respectively connected with the two first wheels, and the two first damping mechanisms are arranged on the first landing frame seat; the rear landing gear comprises a second landing frame seat, second wheels and second damping mechanisms, wherein the second wheels are arranged on two sides of the second landing frame seat, and the second landing frame seat is provided with the two second damping mechanisms; the first damping mechanism and the second damping mechanism which are positioned on the same side are connected through a carbon fiber tube;
the horizontal tail comprises a horizontal stabilizer and an elevator, and the elevator is arranged at the rear side of the horizontal stabilizer; the vertical fin comprises a vertical stabilizer and a rudder, and the rudder is arranged at the rear side of the vertical stabilizer;
the first damping mechanism and the second damping mechanism are identical in structure and comprise a connecting block, a damping spring, a damping connecting rod, a damping fixing buckle and a damping fixing shaft, the damping fixing shaft is arranged below the connecting block, the lower end of the damping fixing shaft is fixed on a lifting frame seat, the damping spring is sleeved on the damping fixing shaft, the upper end and the lower end of the damping spring are respectively provided with the damping fixing buckle, the side faces of the damping fixing buckles are hinged with one damping connecting rod, the two damping connecting rods are hinged with each other, and at least one of the two damping fixing buckles can slide on the damping fixing shaft.
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| CN202110875727.4A CN113353243B (en) | 2021-07-30 | 2021-07-30 | Self-wing-changing multifunctional unmanned aerial vehicle logistics vehicle |
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| CN115147051B (en) * | 2022-09-01 | 2022-12-09 | 菏泽京九特种汽车有限公司 | Special lifting vehicle transportation safety supervision system based on big data |
| CN116215907B (en) * | 2023-04-11 | 2023-08-04 | 南京航空航天大学 | Vertical take-off and landing variant unmanned aerial vehicle with tilting, folding and telescopic wings |
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