Variable-structure wing and cross-medium unmanned aerial vehicle

Abstract

The utility model discloses a variable-structure wing and a cross-medium unmanned aerial vehicle, the variable-structure wing comprises a folding wing and a folding control mechanism, the folding wing comprises a first wing plate, a second wing plate, a third wing plate, a sweepback wing and a fixed seat, the two opposite sides of the second wing plate are connected with the first side of the first wing plate and the first side of the third wing plate through a folding mechanism in a foldable and lockable mode, the second side of the third wing plate is fixedly connected with the first side of the sweepback wing, and a propeller thruster is arranged on the surface, away from the second wing plate, of the third wing plate. The second side of the first wing plate is rotatably connected to the fixing base, the folding control mechanism comprises a power piece, folding gears and translation racks, the folding gears are fixedly arranged at the two ends of the second side of the first wing plate respectively, the output end of the power piece is fixedly connected with the translation racks, and the translation racks are in meshed connection with the folding gears respectively. The conventional fixed wings are designed into the folding wings, so that the maneuverability and efficiency of the aircraft entering a water body from the air can be improved.

Description

TECHNICAL FIELD

[0001] The utility model relates to the technical field of cross -media unmanned aerial vehicle, concretely relates to a variable -configuration wing and cross -media unmanned aerial vehicle. BACKGROUND

[0002] The cross -media unmanned aerial vehicle is a kind of unmanned aerial vehicle with the ability of operating in multiple different media. It can switch freely among air, water surface and underwater and other multiple media, show extremely high mobility and flexibility, can quickly respond to various situations and perform tasks, and can also adapt to complex geographical environment and climate conditions, and can be widely applied to many fields such as sea monitoring, disaster rescue, environmental monitoring and the like.

[0003] A Chinese invention patent discloses a foldable and unfolded wing for aircraft (CN201811008161X), which comprises a first sub-wing, a second sub-wing, a screw nut transmission assembly and a driving unit, one end of the first sub-wing is fixedly arranged on the fuselage of the aircraft, the second sub-wing is rotatably arranged on the first sub-wing in the direction of the chord line of the aircraft wing, the screw nut transmission assembly is arranged on the first sub-wing in the direction of the chord line of the aircraft wing, one end of the screw nut transmission assembly is connected with the driving unit, the other end is connected with the second sub-wing, and the screw nut transmission assembly drives the second sub-wing to fold or unfold relative to the first sub-wing in the direction of the chord line of the aircraft wing under the driving of the driving unit. It can be seen that the foldable and unfolded wing can only realize the folding and unfolding of the second sub-wing, and cannot realize the folding and unfolding of multiple wings. UTILITY MODEL CONTENTS

[0004] Therefore, the utility model provides a variable -configuration wing and cross -media unmanned aerial vehicle, which designs the existing fixed wing into folding wing to improve the mobility and efficiency of the aircraft entering the water body from the air.

[0005] To achieve the above purpose, the utility model adopts the following technical scheme:

[0006] A variable -configuration wing, comprising a folding wing and a folding control mechanism, the folding wing comprises a first wing plate, a second wing plate, a third wing plate, a swept wing and a fixed seat, the opposite sides of the second wing plate are connected with the first side of the first wing plate and the first side of the third wing plate through folding mechanism in a foldable and lockable manner respectively, the second side of the third wing plate is fixedly connected with the first side of the swept wing, the surface of the third wing plate away from the second wing plate is provided with a propeller propeller, and the second side of the first wing plate is rotatably connected on the fixed seat.

[0007] The folding control mechanism comprises a power element, folding gears and a translation gear rack, the two ends of the second side of the first wing plate are respectively fixed with folding gears, and the output end of the power element is fixedly connected with one end of the translation gear rack.

[0008] To better realize the above technical scheme, the folding mechanism comprises a first driven gear, a second driven gear, a third driven gear, a first connecting seat, a second connecting seat, a first connecting rod and a second connecting rod, the first side of the second wing plate is fixedly provided with a first connecting shaft, the two ends of the first connecting shaft are respectively fixed with the first driven gears, the first side of the first wing plate is fixedly provided with a second connecting shaft, the two ends of the second connecting shaft are respectively fixed with the second driven gears, the second driven gears are in one-to-one meshing connection with the first driven gears, the second side of the second wing plate is fixedly provided with a third connecting shaft, the two ends of the third connecting shaft are respectively fixed with the third driven gears, the first side of the third wing plate is fixedly provided with a fourth connecting shaft, the two ends of the fourth connecting shaft are respectively fixed with fourth driven gears, and the fourth driven gears are in meshing cooperation with the third driven gears.

[0009] The ends of the first connecting shaft and the second connecting shaft are respectively in rotary cooperation with the two ends of the first connecting seat, the ends of the third connecting shaft and the fourth connecting shaft are respectively in rotary cooperation with the two ends of the second connecting seat, one end of the first connecting rod is rotatably connected to the end of the first connecting seat close to the second wing plate, the other end of the second connecting rod is rotatably connected to the end of the second connecting seat close to the second wing plate, one end of the second connecting rod is rotatably connected to the end of the first connecting seat close to the first wing plate, and the other end of the second connecting rod is rotatably arranged on the fixed seat.

[0010] Optionally, the first wing plate, the second wing plate and the third wing plate are all half-elliptic arc structures, and when the first wing plate, the second wing plate and the third wing plate are folded, the first wing plate, the second wing plate and the third wing plate form a folded half-elliptic arc structure.

[0011] Optionally, the mutually adhering surfaces of the second wing plate and the third wing plate are respectively embedded with solar panels.

[0012] Optionally, the left and right sides of the cross-medium unmanned aerial vehicle body are symmetrically provided with mounting cavities, each mounting cavity is mounted with the variable-structure wing as claimed in any one of claims 1 to 10, when the variable-structure wing is folded, the first wing plate, the second wing plate and the third wing plate are located in the mounting cavities, and the propeller propeller is located outside the mounting cavities, and when the variable-structure wing is unfolded, the first wing plate, the second wing plate, the third wing plate and the propeller propeller are all located outside the mounting cavities.

[0013] The utility model discloses the beneficial effect of:

[0014] The variable-structure wing of the utility model, when the variable-structure wing is folded and put into the internal space of the aircraft, the propeller propeller will not affect the overall fluency of the aircraft, and can be used as an acceleration device of the variable-structure submarine configuration aircraft, can rotate in all directions, and can meet the ascending or diving requirements of the aircraft, and can control the running track of the aircraft.

[0015] The variable-structure wing of the utility model, when the variable-structure wing is folded and put into the internal space of the aircraft, the propeller propeller will not affect the overall fluency of the aircraft, and can be used as an acceleration device of the variable-structure submarine configuration aircraft, can rotate in all directions, and can meet the ascending or diving requirements of the aircraft, and can control the running track of the aircraft. BRIEF DESCRIPTION OF DRAWINGS

[0016] Figure 1 is a three-dimensional schematic view of a variable-structure wing of the utility model embodiment 1;

[0017] Figure 2 is Figure 1 is a partial schematic view of A in the figure;

[0018] Figure 3 is Figure 1 is a partial schematic view of B in the figure;

[0019] Figure 4 is a three-dimensional schematic view of a variable-structure wing of the utility model embodiment 1;

[0020] Figure 5 is a three-dimensional schematic view of a variable-structure wing of the utility model embodiment 1;

[0021] The first wing plate 10, the second connecting shaft 101, the second driven gear 102, the second wing plate 11, the first connecting shaft 111, the first driven gear 112, the third connecting shaft 113, the third driven gear 114, the third wing plate 12, the fourth connecting shaft 121, the fourth driven gear 122, the backswept wing 13, the first connecting seat 14, the second connecting seat 15, the first connecting rod 16, the second connecting rod 17, the solar panel 18, the power piece 21, the folding gear 22, the translation rack 23, the propeller propeller 30, the cross-media unmanned aerial vehicle body 40. DETAILED DESCRIPTION

[0022] The technical scheme of the utility model will be described in detail below in combination with the drawings and specific embodiments.

[0023] Please refer to Figures 1 to 3 The utility model embodiment discloses a variable-structure wing, which comprises a folding wing and a folding control mechanism.

[0024] As Figure 1As shown, the folding wing comprises a first wing plate 10, a second wing plate 11, a third wing plate 12, a swept wing 13 and a fixed seat, the opposite sides of the second wing plate 11 are connected with the first side of the first wing plate 10 and the first side of the third wing plate 12 through folding mechanisms in a foldable and lockable manner, the second side of the third wing plate 12 is fixedly connected with the first side of the swept wing 13, the surface of the third wing plate 12 away from the second wing plate 11 is provided with a propeller 30, the propeller 30 operates by relying on the electric energy of a battery, and the second side of the first wing plate 10 is rotatably connected to the fixed seat (not shown in the figure), so that the first wing plate 10, the second wing plate 11 and the third wing plate 12 are folded with each other.

[0025] Specifically, the first wing plate 10, the second wing plate 11 and the third wing plate 12 are all semi-elliptical arc structures, when the first wing plate 10, the second wing plate 11 and the third wing plate 12 are folded, the first wing plate 10, the second wing plate 11 and the third wing plate 12 form a folded semi-elliptical arc structure, and the swept wing 13 can change the sweep angle of the wing, so as to facilitate the control of the inclination of the aircraft, meet the needs of low-speed flight and high-speed flight, and meet the variable-structure requirements of the trans-medium aircraft.

[0026] As shown in the figure, Figure 1 The folding control mechanism comprises a power member 21, folding gears 22 and a translation gear rack 23, the two ends of the second side of the first wing plate 10 are respectively provided with the folding gears 22, the output end of the power member 21 is fixedly connected with one end of the translation gear rack 23, and the translation gear rack 23 is meshed with each group of folding gears 22.

[0027] When the variable-structure wing needs to be unfolded, the power member 21 pushes the translation gear rack 23 to move away from the power member 21, the movement of the translation gear rack 23 drives the folding gears 22 to rotate forward, in the process of forward rotation of the folding gears 22, the second wing plate 11 and the third wing plate 12 are driven by the folding mechanism to unfold away from the first wing plate 10, until the first wing plate 10, the second wing plate 11 and the third wing plate 12 are all unfolded to form a flat structure, and vice versa, when the power member 21 pushes the translation gear rack 23 to move close to the power member 21, the movement of the translation gear rack 23 drives the folding gears 22 to rotate reversely, in the process of reverse rotation of the folding gears 22, the second wing plate 11 and the third wing plate 12 are driven by the folding mechanism to fold towards the first wing plate 10, until the first wing plate 10, the second wing plate 11 and the third wing plate 12 form a folded structure.

[0028] When the variable-structure wing is folded and stored in the internal space of the aircraft, the propeller 30 does not affect the overall smoothness of the aircraft, and can also be used as an acceleration device of the variable-structure submarine configuration aircraft, can rotate in all directions, meets the needs of the aircraft to ascend or dive, and can control the running track of the aircraft.

[0029] In the transformable wing of this embodiment, when the aircraft is in flight, the first wing panel 10, the second wing panel 11, and the third wing panel 12 are fully deployed, the horizontal tail increases its angle of expansion, and the main thruster (the thruster within the aircraft) and the propeller 30 are fully deployed. When the aircraft enters water from mid-air, the first wing panel 10, the second wing panel 11, and the third wing panel 12 are fully retracted into the aircraft, the horizontal tail reduces its angle of expansion, and the main thruster (the thruster within the aircraft) and the propeller 30 are deflected upward, increasing the initial power value upon entry into the water. When the aircraft is submerged underwater, the first wing panel 10, the second wing panel 11, and the third wing panel 12 are fully retracted into the aircraft body, the horizontal tail reduces its angle of expansion, and the main thruster (the thruster within the aircraft) and the propeller 30 are fully deployed.

[0030] The variable-configuration wing of the embodiment of the present invention can realize the expansion or storage of the first wing panel 10, the second wing panel 11, and the third wing panel 12 according to the power requirements in different media, thereby completing the variable configuration.

[0031] like Figure 2 and Figure 3 As shown, the folding mechanism includes a first driven gear 112, a second driven gear 102, a third driven gear 114, a fourth driven gear 122, a first connecting seat 14, a second connecting seat 15, a first connecting rod 16 and a second connecting rod 17. A first connecting shaft 111 is fixedly penetrated on the first side of the second wing plate 11, and the first driven gear 112 is fixedly provided at both ends of the first connecting shaft 111. A second connecting shaft 101 is fixedly penetrated on the first side of the first wing plate 10, and the second driven gear 102 is fixedly provided at both ends of the second connecting shaft 101. The second driven gear 102 is meshed with the first driven gear 112 one by one. A third connecting shaft 113 is fixedly penetrated on the second side of the second wing plate 11, and the third driven gear 114 is fixedly provided at both ends of the third connecting shaft 113. A fourth connecting shaft 121 is fixedly penetrated on the first side of the third wing plate 12, and the fourth driven gear 122 is fixedly provided at both ends of the fourth connecting shaft 121, and the fourth driven gear 122 is meshed with the third driven gear 114.

[0032] like Figure 2 As shown, the ends of the first connecting shaft 111 and the second connecting shaft 101 are respectively rotatably matched with the two ends of the first connecting seat 14, as shown in FIG. Figure 3As shown, the ends of the third connecting shaft 113 and the fourth connecting shaft 121 are rotatably connected with the two ends of the second connecting seat 15 respectively, one end of the first connecting rod 16 is rotatably connected with the end of the first connecting seat 14 close to the second wing plate 11, the other end of the first connecting rod 16 is rotatably connected with the end of the second connecting seat 15 close to the second wing plate 11, one end of the second connecting rod 17 is rotatably connected with the end of the first connecting seat 14 close to the first wing plate 10, the other end of the second connecting rod 17 is rotatably arranged on the fixed seat, the folding gear 22 rotates to drive the first wing plate 10 to rotate, the first wing plate 10 rotates to drive the second connecting rod 17 and the second connecting shaft 101 to rotate synchronously, the second connecting shaft 101 rotates to drive the second driven gear 102 to rotate, the second driven gear 102 rotates to drive the first driven gear 112 to rotate, and then drives the second wing plate 11 to rotate, the second wing plate 11 rotates to drive the third driven gear 114 to rotate, and then drives the fourth driven gear 122 and the third wing plate 12 to rotate, the folding mechanism is simple in structure and high in stability.

[0033] In the embodiment of the utility model, the mutually adhering surfaces of the second wing plate 11 and the third wing plate 12 are respectively embedded with solar panels 18, when the second wing plate 11 and the third wing plate 12 are unfolded, the solar panels 18 can store energy by using solar energy.

[0034] Embodiment 2

[0035] As Figure 4 And Figure 5 As shown, the embodiment discloses a cross-medium unmanned aerial vehicle, which comprises a cross-medium unmanned aerial vehicle body 40, and mounting cavities are symmetrically arranged on the left side and the right side of the cross-medium unmanned aerial vehicle body 40, each mounting cavity is provided with the variable-structure wing of embodiment 1, when the variable-structure wing is folded, the first wing plate 10, the second wing plate 11 and the third wing plate 12 are located in the mounting cavity, and the propeller thruster 30 is located outside the mounting cavity, when the variable-structure wing is unfolded, the first wing plate 10, the second wing plate 11, the third wing plate 12 and the propeller thruster 30 are all located outside the mounting cavity.

[0036] The cross-medium unmanned aerial vehicle of the embodiment can select the variable-structure wing to be folded or unfolded under different media based on the variable-structure wing, so that the functions of the aircraft, the ship and the submarine are integrated.

[0037] The technical scheme of the utility model is described in detail in combination with specific embodiments, and the specific embodiments are used to help understand the idea of the utility model. The deduction and deformation of the specific embodiments of the utility model by the person skilled in the art also belong to the protection scope of the utility model.

Claims

1. A variable configuration wing, characterized in that: The invention comprises a folding wing and a folding control mechanism, wherein the folding wing comprises a first wing panel (10), a second wing panel (11), a third wing panel (12), a swept wing (13) and a fixing seat, wherein opposite sides of the second wing panel (11) are respectively connected to the first side of the first wing panel (10) and the first side of the third wing panel (12) in a foldable and lockable manner through the folding mechanism, the second side of the third wing panel (12) is fixedly connected to the first side of the swept wing (13), a propeller propeller (30) is provided on the surface of the third wing panel (12) facing away from the second wing panel (11), and the second side of the first wing panel (10) is rotatably connected to the fixing seat; The folding control mechanism comprises a power member (21), a folding gear (22) and a translation rack (23); the folding gears (22) are fixedly provided at both ends of the second side of the first wing plate (10); the output end of the power member (21) is fixedly connected to one end of the translation rack (23); and the translation rack (23) is respectively engaged with each group of folding gears (22).

2. A transformable wing according to claim 1, characterized in that: The folding mechanism comprises a first driven gear (112), a second driven gear (102), a third driven gear (114), a first connecting seat (14), a second connecting seat (15), a first connecting rod (16) and a second connecting rod (17); a first connecting shaft (111) is fixedly provided on the first side of the second wing plate (11); the first driven gear (112) is fixedly provided on the two ends of the first connecting shaft (111); a second connecting shaft (101) is fixedly provided on the first side of the first wing plate (10); the second connecting shaft (101) is fixedly provided on the two ends of the second connecting shaft (101); Two driven gears (102), the second driven gear (102) is meshed with the first driven gear (112) one by one, a third connecting shaft (113) is fixedly provided on the second side of the second wing plate (11), and third driven gears (114) are fixedly provided at both ends of the third connecting shaft (113), a fourth connecting shaft (121) is fixedly provided on the first side of the third wing plate (12), and fourth driven gears (122) are fixedly provided at both ends of the fourth connecting shaft (121), and the fourth driven gear (122) is meshed with the third driven gear (114); The ends of the first connecting shaft (111) and the second connecting shaft (101) are respectively rotatably matched with the two ends of the first connecting seat (14), and the ends of the third connecting shaft (113) and the fourth connecting shaft (121) are respectively rotatably matched with the two ends of the second connecting seat (15). One end of the first connecting rod (16) is rotatably connected to the end of the first connecting seat (14) close to the second wing plate (11), and the other end of the second connecting rod (17) is rotatably connected to the end of the second connecting seat (15) close to the second wing plate (11). One end of the second connecting rod (17) is rotatably connected to the end of the first connecting seat (14) close to the first wing plate (10), and the other end of the second connecting rod (17) is rotatably set on the fixed seat.

3. The variable configuration wing according to claim 2, characterized in that: The first wing panel (10), the second wing panel (11) and the third wing panel (12) are all semi-elliptical arc structures. When the first wing panel (10), the second wing panel (11) and the third wing panel (12) are folded, the first wing panel (10), the second wing panel (11) and the third wing panel (12) form a foldable semi-elliptical arc structure.

4. The variable configuration wing according to claim 1, characterized in that: Solar panels (18) are respectively embedded in the surfaces of the second wing plate (11) and the third wing plate (12) that are in contact with each other.

5. A cross-medium unmanned aerial vehicle, comprising a cross-medium unmanned aerial vehicle body (40), characterized in that: The left and right sides of the cross-medium unmanned aerial vehicle body (40) are symmetrically provided with installation cavities, and each installation cavity is installed with a transformable wing according to any one of claims 1 to 4. When the transformable wing is folded, the first wing panel (10), the second wing panel (11) and the third wing panel (12) are located in the installation cavity, and the propeller propeller (30) is located outside the installation cavity. When the transformable wing is unfolded, the first wing panel (10), the second wing panel (11), the third wing panel (12) and the propeller propeller (30) are all located outside the installation cavity.

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