Anti-drag foldable flapping-wing micro-aircraft

Abstract

The invention discloses an anti-drag foldable flapping-wing micro-aircraft, and relates to the technical field of aircrafts. Comprising a fuselage with an oval head, and an empennage is mounted at one end of the fuselage; the power structure is arranged in the fuselage, and the power structure is used for adjusting the folding wings; the folding mechanisms are arranged on the two sides of the power structure, and the folding mechanisms are used for folding the folding wings; a plurality of mounting holes are formed in the top end of the body, solar panels are mounted in the mounting holes, a mobile power supply is mounted on one side of the inner wall of the body, and a notch is formed in the inner wall of the bottom end of the body. According to the aircraft, the head of the aircraft body is arranged to be oval, air resistance can be reduced, the flight efficiency can be improved, airflow can be effectively smoothed, the air resistance encountered by the aircraft in the flight process is reduced, the stability of the aircraft in the air is better, airflow interference is reduced, and the flight stability is improved; the heat of the power structure can be effectively dissipated when the aircraft flies.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and specifically relates to a drag-reducing and foldable flapping-wing micro-aircraft. Background Art

[0002] Flying at extremely low altitudes like insects and flexibly completing multiple reconnaissance and search tasks is the development direction of current and future micro-aircraft. Among the currently studied flapping-wing aircraft, most wings cannot be folded and closed to the fuselage. During the carrying and transportation process after flight, the exposed wings become cantilever beam structures, which are extremely easy to contact with other objects and cause bending deformation, seriously affecting the assembly performance of the whole machine, thus greatly reducing its flight attitude in the air.

[0003] Existing micro-aircraft mostly adopt a power-driven method, and ensure the stability and controllability of the aircraft through the design of the tail wing and wing. However, the existing designs usually lack an effective power adjustment mechanism, which limits the flexibility and flight performance of the aircraft. In addition, it is difficult to effectively solve the heat dissipation problem of the power system of most micro-aircraft. Especially during long-term flight, it is easy to cause the motor to overheat, reducing the reliability and service life of the aircraft.

[0004] Therefore, a drag-reducing and foldable flapping-wing micro-aircraft is proposed. Summary of the Invention

[0005] The purpose of the present invention is to provide a drag-reducing and foldable flapping-wing micro-aircraft to solve the problems raised in the above background art.

[0006] To achieve the above purpose, the present invention provides the following technical solution: A drag-reducing and foldable flapping-wing micro-aircraft, including a fuselage with an oval head, and a tail wing is installed at one end of the fuselage;

[0007] A power structure, which is arranged inside the fuselage, and the power structure is used to adjust the folding wings;

[0008] A folding mechanism, which is arranged on both sides of the power structure, and the folding mechanism is used to fold the folding wings;

[0009] A plurality of mounting holes are opened at the top of the fuselage, solar panels are installed in the mounting holes, a mobile power source is installed on one side of the inner wall of the fuselage, and a notch is opened at the inner wall of the bottom end of the fuselage.

[0010] As a specific solution of the technical solution of the present application, the power structure includes a protective cover, the protective cover is connected to the inner wall of the bottom end of the fuselage, a motor is arranged on the inner wall of the protective cover, and a support frame is installed on the outer side of one end of the protective cover. The output end of the motor sequentially penetrates the outer wall of the protective cover and the outer wall of the support frame and is fixedly connected to a driving gear.

[0011] As a specific embodiment of the technical solution of the present application, a support rod, a fixed rod and two support plates are arranged between the top end and the bottom end of the fuselage. The support plates are located between the support rod and the fixed rod, and the other support plate is adapted to the notch. Fixed shafts are symmetrically arranged between the inner side of one end of the fuselage and the support plates. Moving sleeves are movably arranged on the outer walls of the support rod and the fixed rod, and rotating sleeves are installed on the outer walls of the fixed shafts.

[0012] As a specific embodiment of the technical solution of the present application, second fixed rods are symmetrically arranged on the outer wall of the rotating sleeve. Moving holes are formed in the outer walls of the second fixed rods. The two connecting blocks are connected by a fixing pin and are adapted to the moving grooves. A connecting rod is arranged on the outer wall of the fixing pin. The other end of the connecting rod is installed with a rotating disc. The rotating disc is in a shape of. A rotating shaft is installed on the outer side of one end of the rotating disc. The other end of the rotating shaft sequentially penetrates through the outer walls of the two support plates and is fixedly connected with a connecting disc. Another connecting rod is installed on the outer side of one end of the connecting disc.

[0013] As a specific embodiment of the technical solution of the present application, a driven gear is installed on the outer wall of the center of the rotating shaft. The driven gear is meshed and connected with the active gear.

[0014] As a specific embodiment of the technical solution of the present application, the folding mechanism includes a fixed wing. The fixed wing is connected to the outer wall of the rotating sleeve and is in a U-shaped structure. Fixed seats are symmetrically installed on the inner wall of the bottom end of the fixed wing. Second support blocks are symmetrically arranged between the top end and the bottom end of one end of the fixed wing. An articulated block is arranged between the second support blocks. Articulated rods are articulated on the outer walls of both sides of the articulated block.

[0015] As a specific embodiment of the technical solution of the present application, an installation shaft is arranged between the articulated rods. A connecting seat is installed on the outer wall of the center of the installation shaft. An articulated seat is articulated between the fixed seats. An electric telescopic rod is arranged between the articulated seat and the connecting seat. A second articulated rod is articulated on the outer side of the articulated rod. A second connecting block is arranged between the inner sides of the top ends of the second support blocks. The other end of the second connecting block is connected to the second articulated rod.

[0016] As a specific embodiment of the technical solution of the present application, a second connecting rod is articulated between the second connecting blocks. The other end of the second connecting rod is articulated with a second fixed seat. A folding wing is installed on the top end of the second fixed seat.

[0017] As a specific embodiment of the technical solution of the present application, installation holes are formed at the top ends of both the fixed wing and the folding wing. A connecting block and a fixing block are installed in the installation holes. The connecting block and the fixing block are articulated.

[0018] Compared with the prior art, the beneficial effects of the present invention are:

[0019] The drag-reducing foldable flapping-wing micro air vehicle can reduce air resistance and improve flight efficiency by setting the head of the fuselage to be oval. It can effectively smooth the air flow, reduce the air resistance encountered by the vehicle during flight, make the vehicle more stable in the air, reduce air flow interference, and improve flight smoothness. In addition, the side of the fuselage is in the shape of through holes, which can enable the effective heat dissipation of the power structure during flight.

[0020] At the same time, the set power structure can adjust the angle of the wings, and can adjust the lift, drag and flight attitude of the vehicle according to the flight environment and requirements, so as to optimize flight performance. By adjusting the wings through the power structure, the vehicle can obtain the best aerodynamic performance under different flight conditions, effectively reduce unnecessary energy consumption, and improve the energy use efficiency of the vehicle.

[0021] Secondly, through the set folding mechanism, the folding wings can be folded when not in flight, saving storage space, enhancing the portability of the vehicle, protecting the wings at the same time, improving the flexibility of the vehicle, and reducing the external impact and pressure on the wings. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 Schematic diagram of the overall structure of the vehicle of the present invention;

[0023] Figure 2 Schematic side view of the vehicle of the present invention;

[0024] Figure 3 Schematic diagram of the power structure of the present invention;

[0025] Figure 4 Schematic left view of the present invention;

[0026] Figure 5 Schematic top view of the present invention;

[0027] Figure 6 Schematic diagram of the rotating sleeve structure of the present invention;

[0028] Figure 7 Schematic top view of the folding wings of the present invention;

[0029] Figure 8 Schematic diagram of the folding mechanism of the present invention.

[0030] In the figure: 1, fuselage; 11, tail wing; 12, solar panel; 13, notch; 2, power structure; 20, protective cover; 21, support frame; 211, driving gear; 212, movable sleeve; 22, support rod; 23, support plate; 24, support block; 25, fixed rod; 26, connecting rod; 261, rotating disc; 262, rotating shaft; 263, driven gear; 264, connecting disc; 27, motor; 28, fixed shaft; 281, rotating sleeve; 282, second fixed rod; 3, folding mechanism; 30, fixed wing; 31, fixed seat; 32, hinge seat; 33, second support block; 34, hinge block; 35, hinge rod; 36, electric telescopic rod; 37, second hinge rod; 38, second connecting rod; 39, folding wing; 391, connecting block; 392, fixed block; 393, second connecting block. Detailed implementation manners

[0031] In order to make the objectives, technical solutions and advantages of the present invention clearer and more understandable, the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0032] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. is based on the orientation or positional relationship shown in the accompanying drawings. It is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as a limitation to the present invention.

[0033] In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include at least one of such features. In the description of the present invention, "a plurality" means at least two, such as two, three, etc., unless otherwise specifically defined.

[0034] In the present invention, unless otherwise clearly specified or defined, terms such as "installed", "connected", "joined", "fixed", etc. shall be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or integrated; it may be a mechanical connection or an electrical connection; it may be directly connected or indirectly connected through an intermediate medium, and it may be the internal communication of two components or the interaction relationship between two components, unless otherwise clearly defined. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0035] In the present invention, unless otherwise clearly specified or defined, the first feature being "on" or "under" the second feature may be that the first and second features are in direct contact, or the first and second features are indirectly in contact through an intermediate medium. Moreover, the first feature being "above", "over" and "on top of" the second feature may be that the first feature is directly above or obliquely above the second feature, or merely means that the first feature has a higher horizontal height than the second feature. The first feature being "under", "beneath" and "underneath" the second feature may be that the first feature is directly below or obliquely below the second feature, or merely means that the first feature has a lower horizontal height than the second feature.

[0036] In the description of this specification, the description with reference to terms such as "one embodiment", "some embodiments", "example", "specific example", or "some examples", etc. means that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described can be combined in a suitable manner in any one or more embodiments or examples. In addition, without contradiction, those skilled in the art can combine and combine the different embodiments or examples described in this specification and the features of different embodiments or examples.

[0037] As Figures 1 to 8As shown in the figure, the present invention provides a technical solution: a drag-reducing foldable flapping-wing micro air vehicle, which includes a fuselage 1 with an oval head. A tail wing 11 is installed at one end of the fuselage 1; a power structure 2 is arranged inside the fuselage 1, and the power structure 2 is used to adjust the folding wings 39; a folding mechanism 3 is arranged on both sides of the power structure 2, and the folding mechanism 3 is used to fold the folding wings 39; a plurality of mounting holes are opened at the top of the fuselage 1, and solar panels 12 are installed in the mounting holes. A mobile power source is installed on one side of the inner wall of the fuselage 1, and a notch 13 is opened at the inner wall of the bottom end of the fuselage 1. It should be clear that in the embodiment of the present application, as can be seen from the foregoing, solar panels 12 are installed on the top of the fuselage 1, and the solar panels 12 can continuously supply power to the mobile power source. Since the conversion of thermal energy into electrical energy by the solar panels 12 is a prior art, no further description will be given here.

[0038] The power structure 2 includes a protective cover 20, which is connected to the inner wall of the bottom end of the fuselage 1. A motor 27 is arranged on the inner wall of the protective cover 20, and a support frame 21 is installed on the outer side of one end of the protective cover 20. The output end of the motor 27 sequentially penetrates the outer wall of the protective cover 20 and the outer wall of the support frame 21 and is fixedly connected to a driving gear 211.

[0039] A support rod 22, a fixed rod 25 and two support plates 23 are arranged between the top end and the bottom end of the fuselage 1. The support plates 23 are located between the support rod 22 and the fixed rod 25, and the other support plate 23 is adapted to the notch 13. Fixed shafts 28 are symmetrically arranged between the inner side of one end of the fuselage 1 and the support plates 23. Moving sleeves 212 are movably arranged on the outer walls of the support rod 22 and the fixed rod 25, and a rotating sleeve 281 is installed on the outer wall of the fixed shaft 28.

[0040] Second connecting blocks 391 are symmetrically arranged on the outer wall of the rotating sleeve 281. A moving groove is opened on the outer wall of the second connecting blocks 391. The two connecting blocks 391 are connected by a fixing pin and are adapted to the moving groove. A connecting rod 26 is arranged on the outer wall of the fixing pin. The other end of the connecting rod 26 is installed with a rotating disc 261. The rotating disc 261 is in an 8-shaped structure. A rotating shaft 262 is installed on the outer side of one end of the rotating disc 261. The other end of the rotating shaft 262 sequentially penetrates the outer walls of the two support plates 23 and is fixedly connected to a connecting disc 264. Another connecting rod 26 is installed on the outer side of one end of the connecting disc 264.

[0041] A driven gear 263 is installed on the outer wall of the center of the rotating shaft 262, and the driven gear 263 is meshed and connected with the driving gear 211. It should be clear that in the present application, the mobile power source can supply power to the motor 27 and the electric telescopic rod 36, and the rotating sleeves 281 are distributed on both sides of the fuselage 1, and the rotating sleeves 281 are driven by the motor 27 to drive the driving gear 211 to rotate. By Figure 3It can be seen that the driving gear 211 is meshed and connected with the driven gear 263. Therefore, the driving gear 211 can drive the rotation of the driven gear 263. The driven gear 263 is installed on the outer wall of the rotating shaft 262. Therefore, the rotating shaft 262 can rotate with the driven gear 263. While the rotating shaft 262 is rotating, it can drive the rotating disks 261 connected at both ends to rotate, and the rotating disks 261 can drive the connecting rod 26 to move. From Figure 6 It can be seen that second fixing rods 282 are symmetrically arranged on the outer wall of the rotating sleeve 281. A moving hole is formed in the outer wall of the second fixing rod 282. An installation shaft is arranged in the moving hole. The installation shaft connects the second fixing rod 282 and the connecting rod 26, and the installation shaft is also connected with the movable sleeve 212. Therefore, the fixed wing 30 installed on the outer wall of the rotating sleeve 281 can be adjusted.

[0042] The folding mechanism 3 includes a fixed wing 30. The fixed wing 30 is connected to the outer wall of the rotating sleeve 281. The fixed wing 30 is of a U-shaped structure. Fixed seats 31 are symmetrically installed on the inner wall of the bottom end of the fixed wing 30. Second support blocks 33 are symmetrically arranged between the top end and the bottom end inner wall of one end of the fixed wing 30. An articulated block 34 is arranged between the second support blocks 33. Articulated rods 35 are articulated on the outer walls on both sides of the articulated block 34.

[0043] An installation shaft is arranged between the articulated rods 35. A connecting seat is installed on the outer wall of the center of the installation shaft. An articulated seat 32 is articulated between the fixed seats 31. An electric telescopic rod 36 is arranged between the articulated seat 32 and the connecting seat. A second articulated rod 37 is articulated on the outer side of the articulated rod 35. A second connecting block 393 is arranged between the inner sides of the top ends of the second support blocks 33. The other end of the second connecting block 393 is connected with the second articulated rod 37.

[0044] A second connecting rod 38 is articulated between the second connecting blocks 393. The other end of the second connecting rod 38 is articulated with a second fixed seat. A folding wing 39 is installed on the top end of the second fixed seat.

[0045] Installation holes are formed at the top ends of the fixed wing 30 and the folding wing 39. A connecting block 391 and a fixing block 392 are installed in the installation holes. The connecting block 391 and the fixing block 392 are articulated.

[0046] It should be clear that in the embodiments of the present application, the fixed wing 30 and the folding wing 39 are folded through the folding mechanism 3. The folding mechanism 3 can fold and store the folding wing 39 when it is not in use. As can be seen from the foregoing, the mobile power supply can supply power to the electric telescopic rod 36, and the electric telescopic rod 36 can drive the hinge rods 35 at both ends of the mounting shaft to fold. Also, since the hinge rod 35 is hinged to the hinge block 34, and the outer side of the hinge rod 35 is connected to the second connecting rod 38 and the second fixed seat through the second hinge rod 37, and the second fixed seat is connected to the folding wing 39, a structure for folding the folding wing 39 is thus formed. It should also be clear that when folding the folding wing 39, the fixed block 392 is not affected by the fixed wing 30, and the folding wing 39 can be folded normally.

[0047] The working principle of the present invention is as follows: The solar panel 12 continuously supplies power to the mobile power supply to avoid power shortage during flight. The mobile power supply supplies power to the motor 27, and the motor 27 drives the driving gear 211 to rotate. The driving gear 211 is meshed with the driven gear 263, so the rotation of the driven gear 263 can be driven. The driven gear 263 drives the rotating shaft 262 to rotate. While the rotating shaft 262 rotates, it drives the rotating disks 261 and the connecting disks 264 at both ends to rotate. One end of each of the rotating disks 261 and the connecting disks 264 is connected to a connecting rod 26, and the connecting rod 26 is connected to the second fixed rod 282 through a fixing pin. The second fixed rod 282 is connected to the rotating sleeve 281, so the rotating sleeve 281 can be driven to adjust. The adjusted rotating sleeve 281 drives the folding mechanism 3 to adjust. During the movement, since the fixing pin is connected to the movable sleeve 212, the movable sleeve 212 moves up and down on the outer wall of the support rod 22, thus realizing the adjustment of the fixed wing 30 and the folding wing 39. When the flight ends, the electric telescopic rod 36 drives the mounting seat to contract. Since the mounting seat is arranged between the hinge rods 35, the angle of the hinge rods 35 is changed. The hinge rod 35 is hinged to the second hinge rod 37, so the second hinge rod 37 can be driven to contract. The other end of the second hinge rod 37 is connected to the folding wing 39 through the second connecting rod 38 and the second fixed seat, thus realizing the folding of the folding wing 39.

[0048] In summary: A drag-reducing foldable flapping-wing micro air vehicle includes a fuselage 1 with an oval head, and a tail wing 11 is installed at one end of the fuselage 1; a power structure 2 is arranged inside the fuselage 1, and the power structure 2 is used to adjust the folding wing 39; a folding mechanism 3 is arranged on both sides of the power structure 2, and the folding mechanism 3 is used to fold the folding wing 39; a plurality of mounting holes are opened at the top of the fuselage 1, and solar panels 12 are installed in the mounting holes. A mobile power source is installed on one side of the inner wall of the fuselage 1, and a notch 13 is opened at the inner bottom wall of the fuselage 1. By setting the head of the fuselage 1 to be oval, air resistance can be reduced, flight efficiency can be improved, air flow can be effectively smoothed, air resistance encountered by the air vehicle during flight can be reduced, the stability of the air vehicle in the air can be made better, air flow interference can be reduced, and the flight smoothness can be improved. Moreover, the side of the fuselage 1 is in the shape of through holes, which can enable the power structure of the air vehicle to dissipate heat effectively during flight.

[0049] At the same time, the set power structure 2 can adjust the angle of the wing, and the lift, drag and flight attitude of the air vehicle can be adjusted according to the flight environment and requirements, so as to optimize the flight performance. By adjusting the wing through the power structure 2, the air vehicle can obtain the best aerodynamic performance under different flight conditions, effectively reduce unnecessary energy consumption, and improve the energy use efficiency of the air vehicle. Secondly, through the set folding mechanism 3, the folding wing 39 can be folded when not in flight, saving storage space, enhancing the portability of the air vehicle, protecting the wing at the same time, improving the flexibility of the air vehicle, and reducing the external impact and pressure on the wing.

[0050] Although the embodiments of the present invention have been shown and described, for those of ordinary skill in the art, it can be understood that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirit of the present invention. The scope of the present invention is defined by the appended embodiments and their equivalents.

Claims

1. A drag-reducing foldable flapping-wing micro air vehicle, characterized in that It includes a fuselage with an oval head, and a tail wing is installed at one end of the fuselage; A power structure, which is arranged inside the fuselage and is used to adjust the folding wings; A folding mechanism, which is arranged on both sides of the power structure and is used to fold the folding wings; A plurality of mounting holes are opened at the top of the fuselage, solar panels are installed in the mounting holes, a mobile power source is installed on one side of the inner wall of the fuselage, and a notch is opened at the inner wall of the bottom end of the fuselage.

2. The drag-reducing foldable flapping-wing micro air vehicle according to claim 1, characterized in that: The power structure includes a protective cover, which is connected to the inner wall of the bottom end of the fuselage. A motor is arranged on the inner wall of the protective cover, and a support frame is installed on the outer side of one end of the protective cover. The output end of the motor sequentially penetrates the outer wall of the protective cover and the outer wall of the support frame and is fixedly connected to a driving gear.

3. The drag-reducing foldable flapping-wing micro air vehicle according to claim 1, wherein: A support rod, a fixed rod and two support plates are arranged between the top and the bottom of the fuselage. The support plates are located between the support rod and the fixed rod, and the other support plate is adapted to the notch. Fixed shafts are symmetrically arranged between the inner side of one end of the fuselage and the support plate. Movable sleeves are movably arranged on the outer walls of the support rod and the fixed rod, and a rotating sleeve is installed on the outer wall of the fixed shaft.

4. The drag-reducing foldable flapping-wing micro air vehicle according to claim 3, characterized in that: Second fixed rods are symmetrically arranged on the outer wall of the rotating sleeve. Moving holes are opened on the outer walls of the second fixed rods. Two connecting blocks are connected by a fixing pin and are adapted to the moving groove. A connecting rod is arranged on the outer wall of the fixing pin. The other end of the connecting rod is installed with a rotating disc. The rotating disc is in an 8-shaped structure. A rotating shaft is installed on the outer side of one end of the rotating disc. The other end of the rotating shaft sequentially penetrates the outer walls of the two support plates and is fixedly connected to a connecting disc. Another connecting rod is installed on the outer side of one end of the connecting disc.

5. A drag-reducing foldable flapping-wing micro air vehicle according to claim 4, characterized in that: A driven gear is installed on the outer wall of the center of the rotating shaft, and the driven gear is meshed with the driving gear.

6. A drag-reducing foldable flapping-wing micro air vehicle according to claim 1, wherein: The folding mechanism includes a fixed wing, which is connected to the outer wall of the rotating sleeve. The fixed wing is in a U-shaped structure. Fixed seats are symmetrically installed on the inner wall of the bottom end of the fixed wing. Second support blocks are symmetrically arranged between the top end and the bottom end of one end of the fixed wing. An articulated block is arranged between the second support blocks. Articulated rods are articulated on the outer walls of both sides of the articulated block.

7. The drag-reducing foldable flapping-wing micro air vehicle according to claim 6, wherein: An installation shaft is arranged between the articulated rods. A connecting seat is installed on the outer wall of the center of the installation shaft. An articulated seat is articulated between the fixed seats. An electric telescopic rod is arranged between the articulated seat and the connecting seat. Second articulated rods are articulated on the outer sides of the articulated rods. A second connecting block is arranged between the inner sides of the top ends of the support blocks. The other end of the second connecting block is connected to the second articulated rod.

8. A drag-reducing foldable flapping-wing micro air vehicle according to claim 7, characterized in that: A second connecting rod is articulated between the second connecting blocks. The other end of the second connecting rod is articulated to a second fixed seat. A folding wing is installed on the top of the second fixed seat.

9. A drag-reducing foldable flapping-wing micro air vehicle according to claim 6, characterized in that: Mounting holes are opened at the tops of both the fixed wing and the folding wing. Connecting blocks and fixing blocks are installed in the mounting holes, and the connecting blocks and the fixing blocks are articulated.

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