High-aspect-ratio vertical take-off and landing fixed-wing unmanned aerial vehicle easy to store

Abstract

The utility model provides a high-aspect-ratio vertical take-off and landing fixed-wing unmanned aerial vehicle easy to store, which comprises a vehicle body, canards arranged on the left side and the right side of the front part of the vehicle body respectively, main wings arranged on the two sides of the rear part of the vehicle body respectively, ailerons arranged on the rear sides of the main wings, and vertical wings arranged on the upper side and the lower side of the rear part of the vehicle body respectively. A folding propeller adjacent to the aircraft body is arranged on the front side of the main wing, and the section, away from the aircraft body, of the main wing can be folded and retracted in a swinging mode twice and can be unfolded. The section, away from the aircraft body, of the aileron and the section, corresponding to the main wing, of the aileron can synchronously achieve swing folding and unfolding, and the section, away from the aircraft body, of the vertical wing can be folded in the direction of the main wing and can be unfolded. On the basis that the unmanned aerial vehicle is small in occupied space after being folded and stored, the unfolding length of the main wing can be increased, then the aspect ratio of the unmanned aerial vehicle can be increased, and the cruising ability of the unmanned aerial vehicle can be improved by increasing the aspect ratio of the unmanned aerial vehicle.

Description

Technical Field

[0001] The utility model relates to the technical field of vertical take-off and vertical landing fixed-wing unmanned aerial vehicles, in particular to a large aspect ratio vertical take-off and vertical landing fixed-wing unmanned aerial vehicle which is easy to store. Background Art

[0002] Fixed-wing drones usually have a high flight speed and can reach their destination quickly. They can also carry various sensors, imaging equipment, communication equipment and other payloads to meet the needs of various tasks. Therefore, fixed-wing drones are widely used in terrain surveying and mapping, oil exploration, agricultural and forestry plant protection, firefighting and rescue, news interviews, and photography and videography.

[0003] At present, the battery-powered fixed-wing UAV has a low endurance due to the design limitation of the battery weight. According to the existing aircraft aerodynamic theory, under certain conditions, by increasing the aspect ratio of the aircraft, the induced drag during flight can be reduced, and then the endurance of the aircraft can be improved to a certain extent. For fixed-wing UAVs, if the aspect ratio is increased, the lateral span of the UAV will be larger, resulting in a large space occupied by the UAV. The large space occupied by the UAV is not convenient for transporting and carrying the UAV. The applicant previously applied for a Chinese utility model patent entitled: An innovative vertical vertical take-off and landing fixed-wing UAV (authorization announcement number: CN215155592U), which discloses the foldable wing related technology. Although the storage space occupied by the UAV can be reduced by using the disclosed foldable wing related technology, it is not possible to further improve the aspect ratio of the UAV on the basis of a small storage space, and then it is not possible to further improve the endurance of the UAV. Utility Model Content

[0004] The purpose of the utility model is to provide a large aspect ratio vertical take-off and landing fixed-wing UAV that is easy to store. On the basis of realizing the folding and storage of the UAV with a small occupied space, the unfolded length of the main wing can be increased, thereby improving the aspect ratio of the UAV. The improvement of the aspect ratio of the UAV is conducive to improving its endurance.

[0005] The technical solution adopted by the present utility model to solve its technical problems is as follows: An easy-to-store high aspect ratio vertical takeoff and landing fixed-wing unmanned aerial vehicle, comprising a fuselage. On the left and right sides of the front part of the fuselage, a canard wing is provided respectively. On the two sides of the rear part of the fuselage, a main wing is provided respectively. Ailerons are arranged on the rear sides of the main wings. On the upper and lower sides of the rear part of the fuselage, a vertical wing is provided respectively. A folding propeller adjacent to the fuselage is arranged on the front side of the main wing. One section of the main wing far from the fuselage can swing and fold twice to be retracted and can be unfolded; one section of the aileron far from the fuselage and the corresponding section of the main wing can synchronously swing and fold to be retracted and unfolded. One section of the vertical wing far from the fuselage can be folded towards the main wing to be retracted and can be unfolded.

[0006] Preferably, the main wing comprises a fixed main wing, a proximally foldable main wing, and a distally foldable main wing. The fixed main wing is fixedly connected to the fuselage. The folding propeller is arranged on the front side of the end of the fixed main wing far from the fuselage. The docking part between the fixed main wing and the proximally foldable main wing is hinged through a first hinge mechanism, and the docking part between the fixed main wing and the proximally foldable main wing is stably clamped through the cooperation of a first clamping mechanism and the first hinge mechanism; the docking part between the proximally foldable main wing and the distally foldable main wing is hinged through a second hinge mechanism, and the docking part between the proximally foldable main wing and the distally foldable main wing is stably clamped through the cooperation of a second clamping mechanism and the second hinge mechanism.

[0007] Further, the aileron comprises a fixed aileron and a foldable aileron. The fixed aileron is arranged on the rear side of the fixed main wing. The foldable aileron is arranged on the rear side of the proximally foldable main wing. The docking part between the fixed aileron and the foldable aileron is hinged through a third hinge mechanism.

[0008] Further, the vertical wing comprises a fixed vertical wing and a foldable vertical wing. The fixed vertical wing is fixedly connected to the fuselage. The docking part between the fixed vertical wing and the foldable vertical wing is hinged through a fourth hinge mechanism, and the docking part between the fixed vertical wing and the foldable vertical wing is stably clamped through the cooperation of a third clamping mechanism and the fourth hinge mechanism.

[0009] Further, the first hinge mechanism, the second hinge mechanism, and the fourth hinge mechanism each comprise at least two damping hinges, and the third hinge mechanism comprises at least one damping hinge.

[0010] Further, the first clamping mechanism, the second clamping mechanism, and the third clamping mechanism each comprise at least one buckle.

[0011] The beneficial effects of the present utility model are as follows: The structure of the present utility model is simple and convenient for processing and manufacturing. On the basis that the present unmanned aerial vehicle can be folded and stored with a relatively small occupied space, it can increase the extended length of the main wing, and then improve the aspect ratio of the unmanned aerial vehicle. When the aspect ratio of the unmanned aerial vehicle is increased, it is beneficial to improve its endurance. The main wing adopts a three-section design, and the two outer sections can be folded and stored. Thus, on the basis of not increasing the occupied space after the main wing is folded, the design of increasing the length of the main wing can be realized, and then the aspect ratio of the unmanned aerial vehicle can be improved. When both main wings are folded and retracted, the lateral span occupied by the two main wings can be greatly reduced. The two blades of the folding propeller can achieve an up-and-down balanced folding state. After the two folding propellers are folded and retracted, the lateral span occupied by the two folding propellers can be greatly reduced. After the main wing and the folding propellers of the unmanned aerial vehicle are both folded and contracted, the lateral span of the unmanned aerial vehicle can be greatly reduced. After both vertical wings are folded, the vertical span of the unmanned aerial vehicle can be greatly reduced. When both the vertical span and the lateral span of the unmanned aerial vehicle are reduced, the occupied space of the unmanned aerial vehicle is reduced, which is convenient for realizing the folding, storage, transportation and carrying of the unmanned aerial vehicle. By using damping hinges and buckles, it is convenient to quickly realize the deployment and folding of the main wing, the auxiliary wing and the vertical wing, which is beneficial to improving the deployment and folding storage efficiency of the unmanned aerial vehicle. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] In order to more clearly illustrate the technical solutions in the embodiments of the present utility model or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the following described drawings are some preferred embodiments of the present utility model. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0013] Figure 1 It is a schematic structural view of the first perspective of the first specific embodiment of the present utility model;

[0014] Figure 2 It is a schematic structural view of the second perspective of the first specific embodiment of the present utility model;

[0015] Figure 3 It is a schematic structural view of the third perspective of the first specific embodiment of the present utility model;

[0016] Figure 4 It is the front view of the folding and storage state of the present utility model;

[0017] Figure 5 It is the top view of the folding and storage state of the present utility model;

[0018] Figure 6 It is a schematic structural view of the first perspective of the folding and storage state of the present utility model;

[0019] Figure 7 ForFigure 1 Enlarged view of location A in [diagram name];

[0020] Figure 8 is Figure 1 Enlarged view of location B in [diagram name];

[0021] Figure 9 is Figure 1 Enlarged view of location C in [diagram name];

[0022] Figure 10 is Figure 1 Enlarged view of location D in [diagram name];

[0023] Figure 11 is Figure 3 Enlarged view of location E in [diagram name];

[0024] Figure 12 is Figure 3 Enlarged view of location F in [diagram name];

[0025] In the figure: 1 airframe, 2 canard, 3 folding propeller, 41 fixed main wing, 42 proximally foldable main wing, 43 distally foldable main wing, 51 fixed aileron, 52 foldable aileron, 61 fixed vertical wing, 62 foldable vertical wing, 7 buckle, 8 damping hinge. Detailed implementation manners

[0026] The following will combine specific embodiments and the attached Figure 1-12 , and clearly and completely describe the technical solutions in the embodiments of the present utility model. Obviously, the described embodiments are only some preferred embodiments of the present utility model, rather than all embodiments. Those skilled in the art can make similar deformations without violating the connotation of the present utility model. Therefore, the present utility model is not limited by the specific embodiments disclosed below.

[0027] The present utility model provides an easy-to-store high aspect ratio vertical takeoff and landing fixed-wing unmanned aerial vehicle (such as Figure 1As shown in the figure, it includes a fuselage 1. On the left and right sides of the front part of the fuselage 1, a canard 2 is provided respectively. On the two sides of the rear part of the fuselage 1, a main wing is provided respectively. On the rear side of the main wing, an aileron is provided. The specific connection method between the aileron and the main wing is a mature technical means in the field of unmanned aerial vehicle technology. Therefore, the specific connection method between the aileron and the main wing will not be described in detail; on the upper and lower sides of the rear part of the fuselage 1, a vertical wing is provided respectively. The canard 2, main wing, aileron and vertical wing of the unmanned aerial vehicle are all known aircraft components in the field of unmanned aerial vehicle technology. Therefore, the specific structures, functions and working principles of the canard 2, main wing, aileron and vertical wing will not be described in detail; in front of the main wing, a folding propeller 3 adjacent to the fuselage is provided. The folding propeller 3 is also a known and mature technical component in the field of unmanned aerial vehicle technology. Therefore, the specific structure of the folding propeller 3 and the specific implementation method of folding after the flight stops will not be introduced in detail. In this specific embodiment, the folding propeller 3 is selected as a propeller including two blades. When performing a flight mission, the angle between the two blades is 180 degrees. When the unmanned aerial vehicle is in a stopped flight state, the two blades can be folded on one side and distributed in a parallel state; a section of the main wing away from the fuselage 1 can achieve two swings of folding and retraction, and can be unfolded; a section of the aileron away from the fuselage 1 and a corresponding section of the main wing can synchronously achieve swinging folding and retraction and unfolding. A section of the aileron and a section of the main wing can be synchronously folded. When folding the main wing, the folding of the aileron is achieved at the same time, and then the folding and storage operation of the unmanned aerial vehicle is carried out; a section of the vertical wing away from the fuselage 1 can be folded and retracted towards the main wing direction, and can be unfolded. The main wing can be folded and stored twice, so that on the basis of not increasing the occupied space after the main wing of the unmanned aerial vehicle is folded, the total length of the main wing after unfolding is appropriately increased. The increase in the total length of the main wing increases the aspect ratio of the unmanned aerial vehicle. The increase in the aspect ratio is beneficial to reducing the induced drag during the flight of the unmanned aerial vehicle, thereby improving the endurance of the unmanned aerial vehicle; after the two main wings are folded and retracted, the transverse span occupied by the two main wings can be greatly reduced; the two blades of the folding propeller can achieve an upper and lower balanced folding state. After the two folding propellers are folded and retracted, the transverse span occupied by the two folding propellers can be greatly reduced; after the main wing and the folding propeller of the unmanned aerial vehicle are folded and retracted, the transverse span of the unmanned aerial vehicle can be greatly reduced; after the two vertical wings are folded, the vertical span of the unmanned aerial vehicle can be greatly reduced. The vertical span and the transverse span of the unmanned aerial vehicle are both reduced, reducing the occupied space of the unmanned aerial vehicle, which is convenient for realizing the folding, storage, transportation and carrying of the unmanned aerial vehicle. The unmanned aerial vehicle is convenient to carry, so in practical applications, it is convenient to realize the rapid deployment of the unmanned aerial vehicle in the mission execution area.

[0028] On the basis of the above embodiments, a specific implementation manner for the main wing to achieve two - stage folding is as follows: The main wing includes a fixed main wing 41, a proximally foldable main wing 42, and a distally foldable main wing 43. The fixed main wing 41 is fixedly connected to the fuselage 1 and cannot be folded relative to the fuselage 1. The folding propeller 3 is arranged on the front side of the end of the fixed main wing 41 away from the fuselage 1. The docking portion between the fixed main wing 41 and the proximally foldable main wing 42 is hingedly connected through a first hinge mechanism. Specifically, the first hinge mechanism includes at least two damping hinges 8. In this specific implementation, the lower side of the docking portion between the fixed main wing 41 and the proximally foldable main wing 42 is hingedly connected through two damping hinges 8, so that the folding operation of the proximally foldable main wing 42 swinging downward can be achieved. The docking portion between the fixed main wing 41 and the proximally foldable main wing 42 is stably clamped and connected through the cooperation of a first clamping mechanism and the first hinge mechanism. Specifically, the first clamping mechanism includes at least one buckle 7. In this specific embodiment, a buckle 7 is arranged on the upper side of the docking portion between the fixed main wing 41 and the proximally foldable main wing 42. The connection of the buckle 7 realizes the stable connection of the upper side of the docking portion between the fixed main wing 41 and the proximally foldable main wing 42, and the connection of the damping hinge 8 realizes the stable connection of the lower side of the docking portion between the fixed main wing 41 and the proximally foldable main wing 42. Then, the stable connection after the unfolding of the fixed main wing 41 and the proximally foldable main wing 42 can be achieved by using the buckle 7 and the damping hinge 8. The docking portion between the proximally foldable main wing 42 and the distally foldable main wing 43 is hingedly connected through a second hinge mechanism. Specifically, the second hinge mechanism includes at least two damping hinges 8. In this specific implementation, the lower side of the docking portion between the proximally foldable main wing 42 and the distally foldable main wing 43 is hingedly connected through two damping hinges 8, so that the folding operation of the distally foldable main wing 43 swinging downward can be achieved. When folding and storing the main wing, the distally foldable main wing 43 can be first folded and retracted downward. After the folding of the distally foldable main wing 43 is completed, the distally foldable main wing 43 and the proximally foldable main wing 42 swing downward synchronously as a whole for folding. Through the above operations, the two - stage folding of the main wing is achieved. By this folding method, the folding and storage of the main wing with a large aspect ratio are realized. After the main wing with a large aspect ratio is folded on both sides, its lateral span is greatly reduced;The docking part of the proximal foldable main wing 42 and the distal foldable main wing 43 is stably clamped and connected through the cooperation of the second clamping mechanism and the second hinge mechanism. Specifically, the second clamping mechanism includes at least one buckle 7. In this specific embodiment, a buckle 7 is provided on the upper side of the docking part of the proximal foldable main wing 42 and the distal foldable main wing 43. The connection of the buckle 7 realizes the stable connection of the upper side of the docking part of the proximal foldable main wing 42 and the distal foldable main wing 43, and the connection of the damping hinge 8 realizes the stable connection of the lower side of the docking part of the proximal foldable main wing 42 and the distal foldable main wing 43. Subsequently, the stable connection of the proximal foldable main wing 42 and the distal foldable main wing 43 after deployment can be realized by using the buckle 7 and the damping hinge 8. The buckle 7 and the damping hinge 8 are both commonly known connecting components in the mechanical field, so the specific structures and corresponding usage operation methods of the buckle 7 and the damping hinge 8 will not be described in detail.;

[0029] On the basis of the above embodiment, a specific implementation manner for the secondary wing to achieve one-time folding is as follows: The secondary wing includes a fixed secondary wing 51 and a foldable secondary wing 52. The fixed secondary wing 51 is arranged at the rear side of the fixed main wing 41, and the foldable secondary wing 52 is arranged at the rear side of the proximal foldable main wing 42. The docking part of the fixed secondary wing 41 and the foldable secondary wing 42 is hingedly connected through a third hinge mechanism. In this specific embodiment, the third hinge mechanism includes at least one damping hinge 8. Specifically, the damping hinge 8 realizes the hinged connection of the lower side of the docking part of the fixed secondary wing 41 and the foldable secondary wing 42; during the swinging and folding process of the proximal foldable main wing 42, the swinging and folding of the foldable secondary wing 52 will be synchronously realized.

[0030] Based on the above embodiments, a specific implementation manner for the vertical wing to achieve a single-fold is as follows: The vertical wing includes a fixed vertical wing 61 and a foldable vertical wing 62. The fixed vertical wing 61 is fixedly connected to the airframe 1 and does not rotate relative to the airframe 1. The docking portion between the fixed vertical wing 61 and the foldable vertical wing 62 is hingedly connected through a fourth hinge mechanism. Specifically, the fourth hinge mechanism includes at least two damping hinges 8. In this specific embodiment, two damping hinges 8 are used to achieve the hinged connection of the corresponding fixed vertical wing 61 and foldable vertical wing 62. Specifically, the left side of the docking portion between the fixed vertical wing 61 and the foldable vertical wing 62 located on the upper side of the tail of the airframe 1 is hingedly connected through two damping hinges 8, and then the foldable vertical wing 62 on the upper side of the tail of the airframe 1 can swing and fold to the left. The right side of the docking portion between the fixed vertical wing 61 and the foldable vertical wing 62 located on the lower side of the tail of the airframe 1 is hingedly connected through two damping hinges 8, and then the foldable vertical wing 62 on the lower side of the tail of the airframe 1 can swing and fold to the right. The docking portion between the fixed vertical wing 61 and the foldable vertical wing 62 is stably clamped and connected through the cooperation of a third clamping mechanism and the fourth hinge mechanism. Specifically, the third clamping mechanism includes at least one buckle 7. In this specific embodiment, a buckle 7 is provided on the right side of the docking portion between the fixed vertical wing 61 and the foldable vertical wing 62 located on the upper part of the airframe 1. By using this buckle 7, the stable connection of the right side of the docking portion between the fixed vertical wing 61 and the foldable vertical wing 62 located on the upper part of the airframe 1 can be achieved, and two damping hinges 8 are used to achieve the stable connection of the left side of the docking portion between the fixed vertical wing 61 and the foldable vertical wing 62 located on the upper part of the airframe 1, so as to realize the stable deployment of the foldable vertical wing 62 on the upper side of the tail of the airframe 1; a buckle 7 is provided on the left side of the docking portion between the fixed vertical wing 61 and the foldable vertical wing 62 located on the lower part of the airframe 1. By using this buckle 7, the stable connection of the left side of the docking portion between the fixed vertical wing 61 and the foldable vertical wing 62 located on the lower part of the airframe 1 can be achieved, and two damping hinges 8 are used to achieve the stable connection of the right side of the docking portion between the fixed vertical wing 61 and the foldable vertical wing 62 located on the lower part of the airframe 1, so as to realize the stable deployment of the foldable vertical wing 62 on the lower side of the tail of the airframe 1.

[0031] The connections at the folding parts of the above main wing, auxiliary wing and vertical wing are all achieved by the combination of damping hinges 8 and buckles 7. Because the operation of the buckle 7 is simple, it is convenient to quickly realize the folding operation and deployment operation of the main wing, auxiliary wing and vertical wing.

[0032] In the present utility model, "left", "right", "front", "rear", "upper" and "lower" are all relative positions used for conveniently describing the position relationship, and thus cannot be understood as absolute positions to limit the protection scope.

[0033] Except for the technical features described in the specification, the rest are well-known technologies to those skilled in the art.

[0034] As described above, the preferred embodiments and examples of the present utility model have been described in detail in conjunction with the accompanying drawings. However, the present utility model is not limited to the above-mentioned embodiments and examples. For those of ordinary skill in the art, without departing from the concept of the present utility model, several improvements and modifications can still be made, and these improvements and modifications should also be regarded as the protection scope of the present utility model.

Claims

1. An easy-to-store high aspect ratio vertical takeoff and landing fixed-wing unmanned aerial vehicle, comprising a fuselage, with a canard wing arranged on each of the left and right sides of the front part of the fuselage, a main wing arranged on each of the two sides of the rear part of the fuselage, an aileron arranged behind the main wing, and a vertical wing arranged on each of the upper and lower sides of the rear part of the fuselage. It is characterized in that A folding propeller adjacent to the fuselage is provided on the front side of the main wing. One end of the main wing away from the fuselage can swing and fold twice for retraction and can also be deployed. One end of the aileron away from the fuselage and the corresponding part of the main wing can synchronously swing, fold, retract and deploy. One end of the vertical wing away from the fuselage can fold towards the main wing for retraction and can also be deployed.

2. The large aspect ratio vertical takeoff and landing fixed-wing UAV that is easy to store according to claim 1, wherein The main wing includes a fixed main wing, a proximally foldable main wing, and a distally foldable main wing. The fixed main wing is fixedly connected to the fuselage. The folding propeller is provided on the front side of the end of the fixed main wing away from the fuselage. The docking part between the fixed main wing and the proximally foldable main wing is hingedly connected through a first hinge mechanism, and the docking part between the fixed main wing and the proximally foldable main wing is stably clamped through the cooperation of a first clamping mechanism and the first hinge mechanism. The docking part between the proximally foldable main wing and the distally foldable main wing is hingedly connected through a second hinge mechanism, and the docking part between the proximally foldable main wing and the distally foldable main wing is stably clamped through the cooperation of a second clamping mechanism and the second hinge mechanism.

3. The large aspect ratio vertical takeoff and landing fixed-wing UAV that is easy to store according to claim 2, characterized in that, The aileron includes a fixed aileron and a foldable aileron. The fixed aileron is provided at the rear side of the fixed main wing, and the foldable aileron is provided at the rear side of the proximally foldable main wing. The docking part between the fixed aileron and the foldable aileron is hingedly connected through a third hinge mechanism.

4. The large aspect ratio vertical takeoff and landing fixed-wing UAV that is easy to store according to claim 3, wherein, The vertical wing includes a fixed vertical wing and a foldable vertical wing. The fixed vertical wing is fixedly connected to the fuselage. The docking part between the fixed vertical wing and the foldable vertical wing is hingedly connected through a fourth hinge mechanism, and the docking part between the fixed vertical wing and the foldable vertical wing is stably clamped through the cooperation of a third clamping mechanism and the fourth hinge mechanism.

5. The large aspect ratio vertical takeoff and landing fixed-wing UAV that is easy to store according to claim 4, characterized in that, The first hinge mechanism, the second hinge mechanism, and the fourth hinge mechanism each include at least two damping hinges, and the third hinge mechanism includes at least one damping hinge.

6. The large aspect ratio vertical take-off and landing fixed-wing UAV that is easy to store according to claim 5, characterized in that The first clamping mechanism, the second clamping mechanism, and the third clamping mechanism each include at least one buckle.

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