CN215663968U

CN215663968U - Detachable wing structure

Info

Publication number: CN215663968U
Application number: CN202120913581.3U
Authority: CN
Inventors: 张洪雷; 林景
Original assignee: Shanghai Ganshi Xingjing Intelligent Technology Co ltd
Current assignee: Shanghai Ganshi Xingjing Intelligent Technology Co ltd
Priority date: 2021-04-29
Filing date: 2021-04-29
Publication date: 2022-01-28
Anticipated expiration: 2031-04-29

Abstract

The utility model discloses a detachable wing structure, which relates to the field of unmanned aerial vehicles and comprises an unmanned aerial vehicle body, wherein the center of the unmanned aerial vehicle body is fixedly provided with the middle part of a wing, the upper side of the middle part of the wing is provided with a maintenance cover opening, the upper side of the unmanned aerial vehicle body is fixedly provided with an upper skin, the lower side of the unmanned aerial vehicle body is fixedly provided with a lower skin, two sides of the middle part of the wing are fixedly provided with inner wings, the interiors of the two inner wings are reinforced and penetrated by a reinforcing carbon beam, one side of one inner wing is provided with a left outer wing, the other side of the other inner wing is provided with a right outer wing, the detachable wing structure is provided, the wing is detached into the left outer wing and the right outer wing, so that the packaging and transportation volume can be reduced, the packaging and transportation cost can be reduced, the area of the left outer wing and the right outer wing is small, the pneumatic load bearing is also small, so that most of the wing and the main body structure have higher strength and rigidity, the achievement of the flight performance index of the unmanned aerial vehicle is completely met.

Description

Detachable wing structure

Technical Field

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a detachable wing structure.

Background

With the increasing maturity of the related technologies of unmanned aerial vehicles, the unmanned aerial vehicles are well applied to the activities of actual combat military training, exercise and the like in China, and are applied and popularized in the fields of electric power, communication, weather, agriculture and forestry, oceans, disaster prevention and reduction and the like. The fixed-wing unmanned aerial vehicle can be designed into an unmanned aerial vehicle with high maneuverability, medium and long endurance, high speed and other performances, is used for simulating targets such as fighters and the like, and meets various military activity requirements of the prior troops.

The light and small unmanned aerial vehicle adopts a plurality of carbon fiber tubes to penetrate through the wings and the body and connect the wings and the body into a whole; the middle-sized unmanned aerial vehicle is characterized in that lugs are designed between a wing beam and a fuselage frame at the root of a wing (at the butt joint of the wing and the fuselage) and are connected, the lugs are fastened and connected through bolts, the connecting structure is formed by machining a high-performance metal material, and the connecting structure is high in machining precision requirement and large in structural weight.

SUMMERY OF THE UTILITY MODEL

The utility model provides a detachable wing structure, which solves the technical problems of high precision requirement and larger structural weight of a light small unmanned aerial vehicle and a medium unmanned aerial vehicle.

In order to solve the technical problem, the utility model provides a detachable wing structure which comprises an unmanned aerial vehicle body, wherein the center of the unmanned aerial vehicle body is fixedly provided with a wing middle part, a maintenance cover opening is arranged in the upper side of the wing middle part, the upper side of the unmanned aerial vehicle body is fixedly provided with an upper covering, the lower side of the unmanned aerial vehicle body is fixedly provided with a lower covering, inner wings are fixedly arranged on two sides of the wing middle part, the interiors of the two inner wings are reinforced by a reinforcing carbon beam and penetrate through the reinforcing carbon beam, one of the inner wings is provided with a left outer wing, the other inner wing is provided with a right outer wing, the centers of one sides of the left outer wing and the right outer wing are respectively provided with a connecting hole, two sides of the left outer wing and the right outer wing are respectively provided with a first fixing hole, one side of the unmanned aerial vehicle body is fixedly provided with a wing root part, and the wing root part comprises a front carbon fiber beam, a rear beam and a lower covering, Fixed orifices two, three and the connecting block of fixed orifices, preceding carbon roof beam fixed mounting is in unmanned aerial vehicle organism one side, preceding carbon roof beam both sides cementitious connection has the connecting block, two the carbon roof beam of back of connecting block downside cementitious connection, fixed orifices two has been seted up at preceding carbon roof beam both ends, fixed orifices three, two have been seted up at back carbon roof beam both ends connecting block center fixed mounting has a reinforced carbon roof beam and reinforced carbon roof beam both ends to pass two connecting blocks.

Preferably, the unmanned aerial vehicle body designs fuselage, wing middle part and wing root into an organic whole.

Preferably, the connecting block, the left outer wing and the right outer wing are all of PMI foam sandwich carbon fiber structures.

Preferably, the maintenance cover is formed by die pressing of carbon fiber composite materials.

Preferably, the aluminum alloy metal piece with the hole is embedded in the middle of the connecting block, and the high-performance aluminum alloy connectors are embedded in the two ends of the reinforced carbon beam.

Preferably, the left outer wing and the right outer wing are connected with the inner wing in a sleeved mode.

Compared with the related art, the detachable wing structure provided by the utility model has the following beneficial effects:

(1) the utility model provides a detachable wing structure, which is characterized in that a left outer wing and a right outer wing are detached from a wing, so that the packaging and transportation volume can be reduced, and the packaging and transportation cost can be reduced.

(2) The utility model provides a detachable wing structure, which has small left and right outer wing areas and smaller aerodynamic load bearing capacity, so that most of the load of the wing is still borne by the wing and a main body structure of a fuselage, and the main body structure has higher strength and rigidity and completely meets the achievement of the flight performance index of an unmanned aerial vehicle.

(3) The utility model provides a detachable wing structure, wherein the left outer wing body and the right outer wing body are simple in structure, low in cost, simple and reliable in structure of connection with a machine body, and convenient to maintain and use.

Drawings

FIG. 1 is a top view of a detachable wing structure according to the present invention;

FIG. 2 is a schematic view of a wing root structure of a detachable wing structure according to the present invention;

FIG. 3 is a schematic view of a removable upper skin and lower skin of a removable wing structure of the present invention;

reference numbers in the figures: 1. an unmanned aerial vehicle body; 2. maintaining the cover opening; 3. a left outer wing; 4. a right outer wing; 5. reinforcing the carbon beam; 6. connecting holes; 7. a first fixing hole; 8. the middle part of the wing; 9. covering the skin; 10. a wing root; 101. a front carbon fiber beam; 102. a rear carbon fiber beam; 103. a second fixing hole; 104. a third fixing hole; 105. connecting blocks; 11. a lower skin; 12. an inner wing.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments; all other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

As shown in figures 1-3, the detachable wing structure comprises an unmanned aerial vehicle body 1, a wing middle part 8 is fixedly installed in the center of the unmanned aerial vehicle body 1, a maintenance cover opening 2 is installed in the upper side of the wing middle part 8, an upper covering 9 is fixedly installed on the upper side of the unmanned aerial vehicle body 1, a lower covering 11 is fixedly installed on the lower side of the unmanned aerial vehicle body 1, inner wings 12 are fixedly installed on two sides of the wing middle part 8, the interiors of the two inner wings 12 are reinforced and penetrate through by reinforcing carbon beams 5, a left outer wing 3 is installed on one side of one of the inner wings 12, a right outer wing 4 is installed on the other side of the other one of the inner wings 12, connecting holes 6 are formed in the centers of one sides of the left outer wing 3 and the right outer wing 4, fixing holes 7 are formed in two sides of the left outer wing 3 and the right outer wing 4, an organic wing root part 10 is fixedly installed on one side of the unmanned aerial vehicle body 1, and the wing root 10 comprises a front beam 101 and a rear carbon fiber beam 102, Fixed orifices two 103, three 104 of fixed orifices and connecting block 105, preceding carbon fibre roof beam 101 fixed mounting is in 1 one side of unmanned aerial vehicle organism, preceding carbon fibre roof beam 101 both sides cementitious joint has connecting block 105, the carbon fibre roof beam 102 in back of two connecting block 105 downside cementitious joints, two 103 fixed orifices have been seted up at preceding carbon fibre roof beam 101 both ends, three 104 fixed orifices have been seted up at back carbon fibre roof beam 102 both ends, two connecting block 105 center fixed mounting have one strengthen carbon roof beam 5 and strengthen carbon roof beam 5 both ends and pass two connecting blocks 105.

Wherein, unmanned aerial vehicle organism 1 designs fuselage, wing middle part 8 and wing root 10 into one whole, makes unmanned aerial vehicle whole more firm and safety.

The connecting block 105, the left outer wing 3 and the right outer wing 4 are all of PMI foam sandwich carbon fiber structures, so that the connecting block 105, the left outer wing 3 and the right outer wing 4 are lighter in weight and have higher pressure resistance.

Wherein, maintain 2 covers of flap and adopt carbon-fibre composite mould pressing to form, make to maintain flap 2 and laminate the fuselage more and compressive capacity promotes greatly.

Wherein, the foraminiferous aluminum alloy metalwork of connecting block 105 middle part pre-buried, strengthen carbon roof beam 5 and connect at the pre-buried high performance aluminum alloy in both ends, make connecting block 105 can be connected more firmly and help the conduction of load with strengthening carbon roof beam 5.

Wherein, the left outer wing 3 and the right outer wing 4 are connected with the inner wing 12 in a sleeving manner, so that the left outer wing 3 and the right outer wing 4 are more conveniently and more firmly connected with the inner wing 12.

The working principle is as follows: firstly, the connecting hole 6 at the center of the left outer wing 3 and the right outer wing 4 can be connected with one end of a reinforced carbon beam 5, the first fixing hole 7 on the left outer wing 3 and the right outer wing 4 corresponds to the second fixing hole 103 and the third fixing hole 104 on a connecting block 105, so that the left outer wing 3 and the right outer wing 4 can be fixed on the two connecting blocks 105, the left outer wing 3 and the right outer wing 4 are subjected to load and are transmitted to the reinforced carbon beam 5, then the load is transmitted to the connecting block 105 through the reinforced carbon beam 5, the connecting block 105 is transmitted to a front carbon fiber beam 101 and a rear carbon fiber beam 102, so that the load can not affect the wings, the unmanned aerial vehicle can fly in the air more stably, the phenomenon of a flap can not occur, meanwhile, the reinforced carbon beam 5 has a positioning function, the integrity of the whole wing surface of the wing is ensured, good aerodynamic characteristics can be obtained in the flying process of the unmanned aerial vehicle, if maintenance is needed, the left outer wing 3 and the right outer wing 4 can be dismantled, the maintenance is more convenient.

It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the utility model, the scope of which is defined in the appended claims and their equivalents.

Claims

1. The detachable wing structure is characterized by comprising an unmanned aerial vehicle body (1), wherein the center of the unmanned aerial vehicle body (1) is fixedly provided with a wing middle part (8), a maintenance cover opening (2) is installed in the upside of the wing middle part (8), an upper covering (9) is fixedly installed on the upside of the unmanned aerial vehicle body (1), a lower covering (11) is fixedly installed on the downside of the unmanned aerial vehicle body (1), inner wings (12) are fixedly installed on two sides of the wing middle part (8), two inner wings (12) are internally reinforced and penetrated through by a reinforced carbon beam (5), one of the inner wings (12) is provided with a left outer wing (3) on one side, the other inner wing (12) is provided with a right outer wing (4) on the other side, connecting holes (6) are respectively formed in the centers of one side of the left outer wing (3) and one side of the right outer wing (4), fixing holes (7) are respectively formed in two sides of the left outer wing (3) and the right outer wing (4), unmanned aerial vehicle organism (1) one side fixed mounting has wing root portion (10), wing root portion (10) are including preceding carbon roof beam (101), the fine roof beam (102) of back carbon, fixed orifices two (103), three (104) of fixed orifices and connecting block (105), preceding carbon roof beam (101) fixed mounting is in unmanned aerial vehicle organism (1) one side, preceding carbon roof beam (101) both sides cementitious joint has connecting block (105), two carbon roof beam (102) of back carbon of connecting block (105) downside cementitious joint, fixed orifices two (103) have been seted up at preceding carbon roof beam (101) both ends, three (104) of fixed orifices have been seted up at back carbon roof beam (102) both ends, two connecting block (105) center fixed mounting has a reinforced carbon roof beam (5) and reinforced carbon roof beam (5) both ends to pass two connecting blocks (105).

2. A detachable wing structure according to claim 1, characterized in that the unmanned aerial vehicle body (1) is designed as a whole with fuselage, wing middle (8) and wing root (10).

3. A detachable wing structure according to claim 1, characterised in that the connection blocks (105), the left outer wing (3) and the right outer wing (4) are all PMI foam sandwich carbon fibre structures.

4. A detachable wing structure according to claim 1, characterised in that the maintenance flap (2) cover is moulded from a carbon fibre composite material.

5. A detachable wing structure according to claim 1, wherein the aluminum alloy metal part with holes is embedded in the middle of the connecting block (105), and the high-performance aluminum alloy joints are embedded in the two ends of the reinforced carbon beam (5).

6. A detachable wing structure according to claim 1, characterised in that the left outer wing (3) and the right outer wing (4) are in a telescoping connection with the inner wing (12).