Variable-sweep wing assembly of water-air cross-medium flapping-wing aircraft and flapping-wing aircraft

Abstract

The present invention discloses a variable-sweep wing assembly of a water-to-air medium-spanning flapping-wing aircraft, comprising: a fuselage; a rotating frame, which is arranged on one side of the front end of the fuselage, and the front end of the rotating frame is rotatably connected to the fuselage; a first swing arm, which is rotatably arranged on the rotating frame, and the first swing arm can swing up and down relative to the rotating frame; a wing surface, which is fixedly arranged on the first swing arm; a flapping-wing driving mechanism, which is arranged on the fuselage, and the flapping-wing driving mechanism is used to drive the first swing arm to swing up and down relative to the rotating frame; a wing adjustment mechanism, which is arranged on the fuselage, and the wing adjustment mechanism is used to drive the rotating frame to rotate left and right relative to the fuselage; the variable-sweep wing assembly of the water-to-air medium-spanning flapping-wing aircraft can improve the flight performance of the aircraft under different working conditions; the present invention also provides a flapping-wing aircraft.

Description

Technical Field

[0001] The invention relates to the field of aircraft, and in particular to a variable-sweep wing assembly of a water-to-air medium-spanning flapping-wing aircraft and the flapping-wing aircraft. Background Art

[0002] With the development of science and technology, flapping-wing aircraft have a wide range of application scenarios both in the military and civilian fields; in the military field, flapping-wing aircraft can perform camouflage reconnaissance, target tracking, close-range electronic interference, etc. in special environments; in the civilian field, flapping-wing aircraft can be used for rescue in confined spaces, forest wildlife detection, aerial video shooting, etc.; currently many countries and scientific research institutions are carrying out special research, trying to develop flapping-wing aircraft that can be used in special environments.

[0003] Existing flapping-wing aircraft generally use a driving mechanism such as a motor to drive the fixed-shape wings to flap up and down to drive the flight of the entire aircraft; however, for water-air cross-medium flapping-wing aircraft, the wing shape requirements for flying in different media are inconsistent, so the fixed-shape wings cannot fully take into account different working conditions and can only show good aerodynamic performance within a smaller operating adjustment range. Summary of the invention

[0004] The present invention aims to solve at least one of the technical problems existing in the prior art. To this end, the present invention proposes a variable-sweep wing assembly for a water-to-air medium-spanning flapping-wing aircraft, which can improve the flight performance of the aircraft under different working conditions.

[0005] The variable-sweep wing assembly of the water-to-air medium-spanning flapping-wing aircraft of the present invention comprises: a fuselage; a rotating frame, which is arranged on one side of the front end of the fuselage, and the front end of the rotating frame is rotatably connected to the fuselage; a first swing arm, which is rotatably arranged on the rotating frame, and the first swing arm can swing up and down relative to the rotating frame; a wing surface, which is fixedly arranged on the first swing arm; a flapping-wing driving mechanism, which is arranged on the fuselage, and the flapping-wing driving mechanism is used to drive the first swing arm to swing up and down relative to the rotating frame; and a wing adjustment mechanism, which is arranged on the fuselage, and the wing adjustment mechanism is used to drive the rotating frame to rotate left and right relative to the fuselage.

[0006] According to some embodiments of the present invention, the wing adjustment mechanism includes: a slider, which is slidably arranged on the fuselage, and the slider can slide forward and backward relative to the fuselage; a first connecting rod, whose two ends are respectively rotatably connected to the rotating frame and the slider; and a driving mechanism, which is arranged on the fuselage, and the driving mechanism is used to drive the slider to move forward and backward.

[0007] According to some embodiments of the present invention, the driving mechanism includes: a bracket, which is arranged on the body; a driving screw, which is rotatably arranged on the bracket, the driving screw extends in the front and rear directions, and the driving screw is threadedly matched with the slider; and a driving motor, which is arranged on the bracket, and the driving motor is used to drive the driving screw to rotate.

[0008] According to some embodiments of the present invention, the driving mechanism further comprises a slide rail disposed on the bracket, the slide rail extending in the front-rear direction, and the slide rail slidably cooperates with the slider.

[0009] According to some embodiments of the present invention, there are two slide rails, which are respectively located on the left and right sides of the driving screw.

[0010] According to some embodiments of the present invention, the variable-sweep wing assembly of the water-to-air cross-medium flapping wing aircraft also includes a second rocker arm, wherein the first rocker arm is rotatably arranged at the front end of the rotating frame, and the second rocker arm is rotatably arranged at the rear end of the rotating frame, the second rocker arm can swing up and down relative to the rotating frame, and the wing surface is fixedly connected to the second rocker arm.

[0011] According to some embodiments of the present invention, the flapping-wing drive mechanism includes: a flapping-wing crank, which is rotatably arranged on the fuselage; a flapping-wing connecting rod, whose two ends are respectively connected to the flapping-wing crank and the first rocker arm through ball hinges; and a power mechanism, which is used to drive the flapping-wing crank to rotate.

[0012] According to some embodiments of the present invention, the power mechanism includes: a flapping-wing motor, which is arranged on the fuselage; and a transmission gear set, which is arranged on the fuselage, and the flapping-wing motor drives the flapping-wing crank to rotate through the transmission gear set.

[0013] According to some embodiments of the present invention, the fuselage includes: a fuselage main pole; a main mounting plate, which is arranged on the lower side of the fuselage main pole, and the flapping motor and the transmission gear set are both arranged on the main mounting plate, and the main mounting plate is hollowed out.

[0014] The present invention also provides a water-to-air medium-spanning flapping-wing aircraft, characterized in that it comprises the variable-sweep wing assembly of the water-to-air medium-spanning flapping-wing aircraft.

[0015] The wing deformation mechanism used in the water-to-air cross-medium flapping-wing aircraft is applied, and its operating power is generated by the flapping-wing drive mechanism driving the first front swing arm to swing up and down relative to the rotating frame to drive the wing surface to flap up and down, and its power generation principle is similar to the flapping-wing flight of birds; before the aircraft enters the water, the wing adjustment mechanism can drive the rotating frame to rotate, so that the sweep angle of the wing surface is increased, and the water entry area of ​​the aircraft when entering the water is reduced as much as possible, so that the impact force of entering the water is reduced as much as possible, and at the same time, the resistance of the wing that is folded inward in the water is greatly reduced, effectively reducing the resistance received by the aircraft during underwater navigation; when flying in the air, when it is necessary to obtain a larger lift, the deformation drive mechanism can control the driving of the rotating frame to rotate forward, so that the sweep angle of the entire wing is reduced, and the lift obtained by the wing is effectively increased; through the adjustment of the deformation drive mechanism, the aircraft can achieve higher flight performance under different working conditions in water and in the air.

[0016] Additional aspects and advantages of the present invention will be given in part in the following description and in part will be obvious from the following description, or will be learned through practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The above and / or additional aspects and advantages of the present invention will become apparent and easily understood from the description of the embodiments in conjunction with the following drawings, in which:

[0018] Figure 1 is an isometric view of a flapping-wing aircraft in an embodiment of the present invention;

[0019] Figure 2 for Figure 1 Axonometric view of the mid-wing aircraft from another perspective after the wing surface is removed;

[0020] Figure 3 for Figure 2 The enlarged view of point A in the middle;

[0021] Figure 4 for Figure 1 A top view of a mid-wing aircraft with the wing surface removed;

[0022] Figure 5 for Figure 4 The enlarged view of point B in the middle;

[0023] Figure 6 for Figure 4 Enlarged view of point C in the middle.

[0024] The above drawings contain the following reference numerals.

[0025] Label name Label name 100 Main body rod 280 Second swing lever 101 Main mounting plate 421 First steering gear 111 Extension rod 422 Second servo 210 Bracket 431 First rear link 220 Slide rails 432 Second rear link 230 Drive screw 441 Horizontal tail 240 slider 442 Vertical tail 241 First transfer link 510 Flapping wing motor 250 Drive motor 520 Transmission gear set 260 Rotating frame 530 Flapping wing connecting rod 270 First swing lever 540 Flapping Crank DETAILED DESCRIPTION

[0026] Embodiments of the present invention are described in detail below, and examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and cannot be understood as limiting the present invention.

[0027] In the description of the present invention, it should be understood that descriptions involving orientations, such as up, down, front, back, left, right, etc., and orientations or positional relationships indicated are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present invention.

[0028] In the description of the present invention, "several" means one or more, "more" means two or more, "greater than", "less than", "exceed" etc. are understood as not including the number itself, and "above", "below", "within" etc. are understood as including the number itself. If there is a description of "first" or "second", it is only used for the purpose of distinguishing the technical features, and cannot be understood as indicating or implying the relative importance or implicitly indicating the number of the indicated technical features or implicitly indicating the order of the indicated technical features.

[0029] In the description of the present invention, unless otherwise clearly defined, terms such as setting, installing, connecting, etc. should be understood in a broad sense, and technicians in the relevant technical field can reasonably determine the specific meanings of the above terms in the present invention based on the specific content of the technical solution.

[0030] refer to Figures 1 to 6 The variable-sweep wing assembly of the water-to-air cross-medium flapping-wing aircraft of this embodiment includes: a fuselage; a rotating frame 260, which is arranged on one side of the front end of the fuselage, and the front end of the rotating frame 260 is rotatably connected to the fuselage; a first swing arm 270, which is rotatably arranged on the rotating frame 260, and the first swing arm 270 can swing up and down relative to the rotating frame 260; a wing surface, which is fixedly arranged on the first swing arm 270; a flapping-wing drive mechanism, which is arranged on the fuselage, and the flapping-wing drive mechanism is used to drive the first swing arm 270 to swing up and down relative to the rotating frame 260; a wing adjustment mechanism, which is arranged on the fuselage, and the wing adjustment mechanism is used to drive the rotating frame 260 to rotate left and right relative to the fuselage.

[0031] The wing deformation mechanism used in the water-air cross-medium flapping-wing aircraft is applied. Its operating power relies on the flapping-wing drive mechanism to drive the first front swing arm to swing up and down relative to the rotating frame 260 to drive the wing surface to flap up and down. The principle of its power generation is similar to the flapping flight of birds. Before the aircraft enters the water, the wing adjustment mechanism can drive the rotating frame 260 to rotate, so that the sweep angle of the wing surface is increased, and the water entry area of ​​the aircraft when entering the water is reduced as much as possible, so that the impact force of entering the water is reduced as much as possible. At the same time, the resistance of the wing that is folded inward in the water is greatly reduced, which effectively reduces the resistance received by the aircraft during underwater navigation. When flying in the air, when it is necessary to obtain a larger lift, the deformation drive mechanism can control the rotating frame 260 to rotate forward, so that the sweep angle of the entire wing is reduced, and the lift obtained by the wing is effectively increased. Through the adjustment of the deformation drive mechanism, the aircraft can achieve higher flight performance under different working conditions in water and in the air.

[0032] refer to Figure 1 , Figure 5In this embodiment, the wing surface is a rigid wing surface, the entire wing surface itself cannot be deformed, the wing surface is fixedly connected to the first swing rod 270, and the flapping wing driving mechanism drives the first swing rod 270 to swing up and down relative to the rotating frame 260 to drive the entire wing surface to flap; and when the wing adjustment mechanism drives the rotating frame 260 to rotate, the sweep angle of the wing can be adjusted, such as Figure 5 As shown, when the rear side of the rotating frame 260 rotates toward the direction approaching the fuselage, the sweep angle of the wing increases; when the rear side of the rotating frame 260 rotates toward the direction away from the fuselage, the sweep angle of the wing decreases.

[0033] It can be understood that the wing adjustment mechanism can drive the rotating frame 260 to rotate in a variety of ways, such as directly driving the rotating frame 260 to rotate through a driving source such as a motor, or it can also drive the rotating frame 260 to rotate through a linear mechanism such as a linear motor or a motor gear rack, by pulling one end of the rotating frame 260 to move.

[0034] Among them, Figure 4 , Figure 5 As shown, the wing adjustment mechanism includes: a slider 240, which is slidably arranged on the fuselage, and the slider 240 can slide forward and backward relative to the fuselage; a first transfer link 241, both ends of which are rotatably connected to the rotating frame 260 and the slider 240 respectively; a driving mechanism, which is arranged on the fuselage, and the driving mechanism is used to drive the slider 240 to move forward and backward; Figure 5 As shown, when the slider 240 slides forward driven by the driving mechanism, the slider 240 drives the rear side of the rotating frame 260 to rotate in a direction close to the fuselage through the first transfer link 241, so that the sweep angle of the entire wing becomes larger; and when the slider 240 moves backward, the slider 240 drives the rear side of the rotating frame 260 to rotate in a direction away from the fuselage through the first transfer link 241, so that the sweep angle of the entire wing becomes smaller until it becomes a straight wing state with a sweep angle of 0; at this time, the driving mechanism can adjust the sweep angle of the wing by controlling the front and rear positions of the slider 240.

[0035] It is understandable that the driving mechanism can adjust the front and rear position of the slider 240 in a variety of ways, such as driving the slider 240 to move forward and backward through a linear motor, or driving the slider 240 to move forward and backward through a motor gear rack mechanism.

[0036] like Figure 5As shown, the driving mechanism includes: a bracket 210, which is arranged on the fuselage; a driving screw 230, which is rotatably arranged on the bracket 210, the driving screw 230 extends in the front-to-back direction, and the driving screw 230 is threadedly matched with the slider 240; a driving motor 250, which is arranged on the bracket 210, and the driving motor 250 is used to drive the driving screw 230 to rotate; wherein, the driving motor 250 drives the screw to rotate to drive the slider 240 to move forward and backward; since the transmission ratio of the threaded transmission mechanism is large, the forward and backward movement position of the slider 240 can be accurately controlled, which is convenient for accurately controlling the sweep angle of the wing; and the reverse self-locking characteristics of the screw nut mechanism can enable the slider 240 to better maintain its position after the motor stops, thereby ensuring that the sweep angle of the wing remains stable.

[0037] like Figure 5 As shown, the driving mechanism also includes a slide rail 220 arranged on the bracket 210, and the slide rail 220 extends in the front-to-back direction. The slide rail 220 and the slider 240 are slidably matched, wherein the slide rail 220 can limit the slider 240 in the front-to-back direction to ensure the stability of the slider 240 in the front-to-back movement; specifically, there are two sliders 240, which are respectively arranged on the left and right sides of the driving screw 230.

[0038] like Figure 5 As shown, in order to ensure the stability of the wing surface flapping, the variable sweep wing assembly also includes a second swing arm 280, the first swing arm 270 is rotatably set at the front end of the rotating frame 260, and the second swing arm 280 is rotatably set at the rear end of the rotating frame 260, the second swing arm 280 can swing up and down relative to the rotating frame 260, and the wing surface is fixedly connected to the second swing arm 280; wherein, the first swing arm 270 is fixedly connected to the front side of the wing surface, and the second swing arm 280 is fixedly connected to the rear side of the wing surface, thereby ensuring that the wing surface can stably flap up and down relative to the rotating frame 260.

[0039] like Figure 2 , Figure 3 As shown, the flapping-wing drive mechanism includes: a flapping-wing crank 540, which is rotatably arranged on the fuselage; a flapping-wing connecting rod 530, both ends of which are connected to the flapping-wing crank 540 and the first swing rod 270 through ball hinges respectively; a power mechanism, which is used to drive the flapping-wing crank 540 to rotate; wherein the power mechanism drives the flapping-wing connecting rod 530 to move up and down, and drives the first swing rod 270 to swing up and down by driving the flapping-wing crank 540 to rotate; and the two ends of the flapping-wing connecting rod 530 are respectively connected to the flapping-wing crank 540 and the first swing rod 270 through ball hinges, which can ensure that after the rotating frame 260 rotates driven by the slider 240, the first swing rod 270 can still swing up and down driven by the flapping-wing connecting rod 530, thereby avoiding the mutual influence between the flapping movement and the rotation of the rotating frame 260.

[0040] Specifically, the power mechanism includes: a flapping motor 510, which is arranged on the fuselage; a transmission gear set 520, which is arranged on the fuselage. The flapping motor 510 drives the flapping crank 540 to rotate through the transmission gear set 520; wherein the power of the flapping motor 510 is transmitted to the flapping crank 540 through the transmission gear set 520, and the transmission gear set 520 can play a role in reducing speed and increasing torque.

[0041] Specifically, the fuselage includes: a fuselage main pole 100; a main mounting plate 101, which is arranged on the lower side of the fuselage main pole 100, on which a flapping motor 510 and a transmission gear set 520 are both arranged, and the main mounting plate 101 is hollowed out; wherein, a main mounting plate 101 and a side mounting plate are arranged on the lower side of the front end of the fuselage, with a gap between the main mounting plate 101 and the side mounting plate, the flapping motor 510 is arranged on the outer side of the main mounting plate 101, and a portion of the transmission gear set 520 is arranged in the gap between the main mounting plate 101 and the side mounting plate, and both the main mounting plate 101 and the side mounting plate are hollowed out to facilitate weight reduction.

[0042] The present embodiment also includes a water-to-air cross-medium flapping-wing aircraft, including the variable-sweep wing assembly of the above-mentioned water-to-air cross-medium flapping-wing aircraft, which can not only adapt to flights in different working conditions during water-to-air cross-medium operation, but also has good adaptability in high-speed cruising and medium and low-speed maneuvering flight.

[0043] Specifically, Figure 6 As shown, a tail mounting frame for mounting a tail assembly is provided at the rear end of the fuselage, and the tail mounting frame includes: a vertical mounting plate, which is arranged at the rear end of the rear side of the fuselage main rod 100; a horizontal mounting plate, which is arranged at the lower end of the vertical mounting plate, and the horizontal mounting plate is used to mount the tail assembly; two servo mounting parts are provided on the horizontal mounting plate, and the two servo mounting parts are respectively located on the left and right sides of the vertical mounting plate; wherein, the first servo 421 is installed on the servo mounting part on the left, and the second servo 422 is installed on the servo mounting part on the right.

[0044] The tail assembly includes an integrated tail, which is rotatably connected to the tail mounting frame, and the integrated tail includes an integrated horizontal tail 441 and a vertical tail 442; wherein the cranks of the first servo 421 and the second servo 422 are respectively connected to the upper ends of the horizontal tails 441 on both sides through the first rear connecting rod 431 and the second rear connecting rod 432, wherein the entire integrated tail has two rotational degrees of freedom relative to the tail mounting frame, that is, the entire integrated tail can rotate up and down and left and right; when the two motors are respectively rotated along the same When rotating in opposite directions by the same angle, the pitch angles of the horizontal tail wings 441 on both sides are the same, that is, the pitch angle of the horizontal tail wing 441 can be controlled by controlling the first motor at an equal angle. When the rotation angles of the first servo 421 and the second servo 422 are different, the entire integrated tail assembly deflects left and right relative to the fuselage, so that the deflection angle of the vertical tail wing 442 changes. At this time, the pitch and yaw states of the entire aircraft can be controlled by controlling the rotation state of the first servo 421 and the second servo 422.

[0045] The embodiments of the present invention are described in detail above in conjunction with the accompanying drawings, but the present invention is not limited to the above embodiments, and various changes can be made within the knowledge scope of ordinary technicians in the relevant technical field without departing from the purpose of the present invention.

Claims

1. A variable-sweep wing assembly for a water-to-air medium-spanning flapping-wing aircraft, characterized in that: include: body; A rotating frame (260) is arranged on one side of the front end of the fuselage, and the front end of the rotating frame (260) is rotatably connected to the fuselage; A first swing rod (270) is rotatably disposed on the rotating frame (260), and the first swing rod (270) can swing up and down relative to the rotating frame (260); An airfoil fixedly mounted on the first swing rod (270); a flapping-wing driving mechanism, arranged on the fuselage, the flapping-wing driving mechanism being used to drive the first swing rod (270) to swing up and down relative to the rotating frame (260); A wing adjustment mechanism is arranged on the fuselage, and the wing adjustment mechanism is used to drive the rotating frame (260) to rotate left and right relative to the fuselage; a second swing rod (280), wherein the first swing rod (270) is rotatably disposed at the front end of the rotating frame (260), and the second swing rod (280) is rotatably disposed at the rear end of the rotating frame (260), the second swing rod (280) can swing up and down relative to the rotating frame (260), and the wing surface is fixedly connected to the second swing rod (280); Wherein the flapping-wing drive mechanism comprises: A flapping crank (540) rotatably mounted on the fuselage; A flapping-wing connecting rod (530), two ends of which are respectively connected to the flapping-wing crank (540) and the first swing rod (270) through ball hinges; A power mechanism, used for driving the flapping-wing crank (540) to rotate; Wherein the wing adjustment mechanism comprises: A slider (240) is slidably disposed on the fuselage, and the slider (240) can slide forward and backward relative to the fuselage; A first transfer connecting rod (241), both ends of which are rotatably connected to the rotating frame (260) and the sliding block (240) respectively; A driving mechanism is arranged on the machine body, and is used to drive the slider (240) to move forward and backward.

2. The variable-sweep wing assembly of the water-to-air medium-spanning flapping-wing aircraft according to claim 1, characterized in that: The driving mechanism comprises: A bracket (210) is arranged on the body; a driving screw rod (230) is rotatably arranged on the bracket (210), the driving screw rod (230) extends in the front-rear direction, and the driving screw rod (230) is threadedly matched with the slider (240); A driving motor (250) is arranged on the bracket (210), and the driving motor (250) is used to drive the driving screw rod (230) to rotate.

3. The variable-sweep wing assembly of the water-to-air medium-spanning flapping-wing aircraft according to claim 2, characterized in that: The driving mechanism further comprises a slide rail (220) arranged on the bracket (210), the slide rail (220) extending in the front-rear direction, and the slide rail (220) slidingly cooperates with the slider (240).

4. The variable-sweep wing assembly of the water-to-air medium-spanning flapping-wing aircraft according to claim 3, characterized in that: There are two slide rails (220), and the two slide rails (220) are respectively located on the left and right sides of the driving screw rod (230).

5. The variable-sweep wing assembly of the water-to-air medium-spanning flapping-wing aircraft according to claim 4, characterized in that: The power mechanism comprises: a flapping-wing motor (510) arranged on the fuselage; A transmission gear set (520) is arranged on the fuselage, and the flapping-wing motor (510) drives the flapping-wing crank (540) to rotate through the transmission gear set (520).

6. The variable-sweep wing assembly of the water-to-air medium-spanning flapping-wing aircraft according to claim 5, characterized in that: The fuselage comprises: a fuselage main rod (100); A main mounting plate (101) is arranged on the lower side of the fuselage main rod (100); the flapping-wing motor (510) and the transmission gear set (520) are both arranged on the main mounting plate (101); and the main mounting plate (101) is hollowed out.

7. A water-to-air medium flapping wing aircraft, characterized in that: A variable-sweep wing assembly for a water-to-air medium-spanning flapping-wing aircraft comprising any one of claims 1 to 6.

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