A dual-float surface take-off and landing UAV

Abstract

The present invention relates to a double-float water surface take-off and landing UAV, comprising a fuselage, wings, propeller engines, tail wings, and two floats arranged symmetrically below the fuselage; the floats are of a left-right symmetrical special-shaped structure, the bottom surface of the floats is inclined upward from the middle to both sides, so that the bottom of the floats has a V-shaped cross-section; the rear end of the float bottom surface forms a step, the tail of the float is inclined backward and upward from the upper end of the step, so that the tail is lifted off the water surface; the bow of the float is inclined forward and upward from the front end of the bottom, so that the bow is lifted off the water surface. The floats of the present invention adopt a structure similar to the hull, and the stepped structure design allows sufficient air flux at the bottom of the floats, reducing fluid resistance; the special leading edge angle and trailing edge angle structural design reduces the fluid resistance value of the floats, so that the power loss in the gliding stage reaches a minimum value; during landing, when the double floats of the UAV touch the water surface, the special side edge angle structural design reduces the impact force of the aircraft with the water surface during landing, thereby improving the landing safety factor of the UAV.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft, and in particular relates to a water surface take-off and landing unmanned aerial vehicle. Background Art

[0002] Existing fixed-wing drones have high takeoff runway requirements and demanding recovery conditions. If a drone encounters an unexpected situation while performing a maritime mission and cannot find a suitable landing environment, it will crash when its energy runs out. Existing fixed-wing drones capable of water takeoff and landing also have the problem of being difficult to take off. Because they rely on a single engine for power, taking off in high-resistance waters can prevent the drone from taking off, reducing its efficiency and hindering its development. Therefore, reducing the fluid resistance during takeoff has become an urgent issue.

[0003] Chinese patent CN109263975A discloses a vertical take-off and landing amphibious aircraft, comprising a fuselage, a control system, a first power unit, a second power unit, wings, connecting rods, floats, a horizontal tail, and a vertical tail. The floats provide buoyancy for the amphibious aircraft during water navigation. The floats described in this patent merely provide buoyancy, resulting in poor gliding performance on the water, high aerodynamic drag during flight, increased fuel consumption, poor landing performance, and difficulty taking off in high-drag areas. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to provide a double-float water surface take-off and landing UAV in response to the shortcomings of the above-mentioned existing technologies. It can not only reduce the resistance of the UAV's gliding and flying on the water surface, but also improve the UAV's landing safety factor, solving the problem that the UAV has too high requirements for take-off and landing conditions.

[0005] The technical solution adopted by the present invention to solve the above-mentioned technical problems is:

[0006] A dual-float surface take-off and landing UAV, comprising a fuselage, wings, a propeller engine and a tail; and two floats arranged below the fuselage and in a bilaterally symmetrical arrangement;

[0007] The buoy is a bilaterally symmetrical special-shaped structure, with the bottom surface of the buoy tilted upward from the middle to both sides, so that the bottom of the buoy has a V-shaped cross-section; a step is formed at the rear end of the bottom surface of the buoy, and the tail of the buoy tilts backward and upward from the upper end of the step, so that the tail is lifted out of the water surface; the bow of the buoy tilts forward and upward from the front end of the bottom, so that the bow is lifted out of the water surface.

[0008] In the above solution, the bottom slope angle of the buoy, that is, the side edge angle β is 20° to 25°.

[0009] In the above solution, an arc-shaped wave suppression groove is formed at the outer end of the bottom surface of the buoy, and an arc-shaped wave suppression plate is formed on the outer edge of the wave suppression groove.

[0010] In the above solution, the height of the step at the rear end of the bottom surface of the buoy is 5% to 9% of the maximum width of the buoy.

[0011] In the above solution, the step is located at 1 / 16 of the length of the buoy behind the buoyancy center of the buoy.

[0012] In the above solution, the tail ramp angle of the buoy, that is, the trailing edge angle γ, is 6° to 10°; the bow ramp angle of the buoy, that is, the leading edge angle α, is 20° to 26°.

[0013] In the above solution, the top surface of the buoy is a plane, connected to the fuselage through a connecting rod; the side surface of the buoy is a smooth curved surface connecting the bottom surface and the top surface.

[0014] In the above solution, the connecting rods form a triangular frame to stabilize the fuselage and the pontoon.

[0015] In the above scheme, a battery, a flight control computer, and an electronic speed regulator are installed inside the fuselage; the battery is arranged in the rear section of the fuselage; the flight control computer is arranged in the middle section of the fuselage; and the electronic speed regulator is symmetrically arranged on the left and right sides of the flight control computer.

[0016] In the above solution, the propeller engines include a left propeller engine and a right propeller engine symmetrically installed on the left and right wings, and the propellers of the two propeller engines are located in front of the wings.

[0017] The beneficial effects of the present invention are:

[0018] 1. The buoys of the drone of this invention utilize a hull-like structure. Their unique shape reduces the resistance of the drone during gliding and flight on the water, and also improves the safety factor of landing. The stepped structure ensures sufficient air flow at the bottom of the buoys, reducing fluid resistance. The unique leading and trailing angles reduce the buoy's fluid resistance, minimizing power loss during gliding. During landing, when the drone's dual buoys contact the water, the unique side angles reduce the impact force of the aircraft on the water, improving the safety factor of landing.

[0019] 2. The outer end of the bottom surface of the buoy of the present invention forms an arc-shaped wave suppression groove, and a wave suppression plate is formed on the outer edge of the wave suppression groove, which can effectively reduce splashing during sliding.

[0020] 3. The present invention makes full use of the rotational power of the twin-propeller engine, so that the dual-float surface take-off and landing UAV can reach the take-off speed in a short time, and is suitable for working in high-resistance waters such as complex sea surfaces.

[0021] 4. The buoy structure of the present invention is light in weight, beautiful in appearance and easy to maintain.

[0022] 5. The present invention is applied to fields such as scientific research vessels. It does not require the construction of a runway and can achieve take-off and landing on the water surface. There is no need to reserve power for return. When the power is insufficient, the drone can land directly and safely on the water surface, which nearly doubles the maximum working time of the drone and the detection range of the drone. It has high application value. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] The present invention will be further described below with reference to the accompanying drawings and embodiments, in which:

[0024] Figure 1 This is a front view of the dual-buoy water surface take-off and landing UAV of the present invention;

[0025] Figure 2 This is a top view of the dual-buoy water surface take-off and landing UAV of the present invention;

[0026] Figure 3 This is a perspective view of the buoys of the dual-buoy surface take-off and landing UAV of the present invention;

[0027] Figure 4-5 This is a perspective view from another angle of the buoys of the double-buoy water surface take-off and landing UAV of the present invention;

[0028] Figure 6 This is a front view of the buoys of the double-buoy surface take-off and landing UAV of the present invention;

[0029] Figure 7 The figure is a side view of the buoys of the double-buoy water surface take-off and landing UAV of the present invention.

[0030] In the figure: 10, fuselage; 11, battery; 12, flight control computer; 13, electronic speed controller;

[0031] 20, wing; 21, left wing; 22, right wing;

[0032] 30. Propeller engine; 31. Left propeller engine; 32. Right propeller engine;

[0033] 40. Tail wing;

[0034] 50, buoy; 51, bottom; 511, step; 512, wave suppression tank; 52, tail; 53, bow;

[0035] 60. Connecting rod. DETAILED DESCRIPTION

[0036] In order to have a clearer understanding of the technical features, purposes and effects of the present invention, specific embodiments of the present invention are now described in detail with reference to the accompanying drawings.

[0037] like Figure 1-2 As shown, a dual-float surface take-off and landing UAV provided by an embodiment of the present invention includes a fuselage 10, wings 20, propeller engines 30, and a tail 40. The wings 20 are divided into a left wing 21 and a right wing 22. The left and right wings 21 and 22 are connected to the fuselage 10 and located at the front of the fuselage 10, and the left and right wings 21 and 22 are symmetrically distributed. The propeller engines 30 are divided into a left propeller engine 31 and a right propeller engine 32. The left propeller engine 31 and the right propeller engine 32 are symmetrically distributed. The left propeller engine 31 is connected to the left wing 21 and located at the front end of the left wing 21; the right propeller engine 32 is connected to the right wing 22 and located at the front end of the right wing 22. The tail 40 is located at the rear of the fuselage 10. The surface take-off and landing UAV also includes two floats 50 disposed below the fuselage 10 and arranged symmetrically. The left and right floats 50 are connected to the fuselage 10 via a connecting rod 60.

[0038] like Figure 3-7 As shown, a single buoy 50 has a bilaterally symmetrical, irregularly shaped structure. The bottom surface of the buoy 50 tilts upward from the center toward the sides, giving the bottom 51 of the buoy 50 a V-shaped cross-section, effectively reducing the impact force on the water surface during landing. A step 511 is formed at the rear end of the bottom surface of the buoy 50. The tail 52 of the buoy 50 tilts backward and upward from the top of the step 511, lifting the tail 52 off the water surface and reducing fluid resistance. The bow 53 of the buoy 50 tilts upward from the front end of the bottom surface, lifting the bow 53 off the water surface. The step 511 design plays a crucial role in the takeoff and roll phase of a drone. As the drone glides over the water, as its speed increases, the step 511 creates an "air pocket" at the rear of the buoy 50, allowing sufficient air flow to the bottom 51 of the buoy 50, reducing the downward suction force of the water on the buoy 50, thereby reducing fluid resistance and ensuring the stability of the aircraft gliding through the water. The bottom 51 of the buoy 50 is V-shaped, with both the bow 53 and tail 52 elevated above the water surface. This creates a twisted, upward flow pattern for the buoy 50, minimizing the wetted surface area, gliding resistance, and splashing when the drone glides through the water. The top surface of the buoy 50 is flat, with notches for securing the connecting rods. The side surfaces of the buoy 50 are smoothly curved, connecting the bottom and top surfaces.

[0039] According to further optimization, the bottom 51 of the buoy 50 has an inclined rising angle, that is, a side edge angle β, of 20° to 25°.

[0040] A further improvement is the formation of an arc-shaped wave-suppression groove 512 at the outer end of the bottom surface of the buoy 50, and a wave-suppression plate is formed on the outer edge of the wave-suppression groove 512. When the water drone glides through the water, the splash generated from the bottom 51 of the buoy 50 climbs along the bottom surface of the buoy 50 and enters the wave-suppression groove 512. Because the wave-suppression plate blocks the original flow direction of the splash, the splash rotates within the wave-suppression groove 512 and flows out from the bottom side of the wave-suppression plate.

[0041] According to further optimization, the height of the step 511 at the rear end of the bottom surface of the buoy 50 is 5% to 9% of the maximum width of the buoy 50 .

[0042] According to further optimization, the step 511 is located at a position about 1 / 16 of the length of the buoy 50 behind the buoyancy center of the buoy 50 .

[0043] According to further optimization, the tail portion 52 of the pontoon 50 has a ramp angle, that is, a trailing edge angle γ, of 6° to 10°.

[0044] According to further optimization, the oblique rise angle of the bow 53 of the buoy 50, that is, the leading edge angle α is 20° to 26°.

[0045] Further optimized, the connecting rods 60 form a triangular frame to stabilize the fuselage 10 and the pontoon 50.

[0046] Further optimization is carried out, a battery 11, a flight control computer 12, and an electronic speed regulator 13 are set inside the fuselage 10; the battery 11 is arranged in the rear section of the fuselage 10; the flight control computer 12 is arranged in the middle section of the fuselage 10; there are two electronic speed regulators 13, which are symmetrically arranged on the left and right sides of the flight control computer 12.

[0047] The operating principle of the dual-float 50 surface takeoff and landing drone of the present invention is as follows: When the drone takes off, it is placed on the water surface. The drone floats on the surface using the buoyancy of the floats 50. The battery 11 powers the flight control computer 12 and the propeller engine 30. Upon receiving the takeoff command, the flight control computer 12 transmits a signal to the electronic speed controller 13, which activates the propeller engine 30 on the wings 20, driving the drone to glide on the water surface. During the glide phase, the unique structural design of the floats 50 reduces glide resistance and minimizes splashing as the drone glides through the water. The stepped structure 511 ensures sufficient air flow through the bottom 51 of the floats 50, reducing fluid resistance. The unique trailing edge angle design also minimizes the fluid resistance of the floats 50, minimizing power loss during the glide phase. After reaching a certain speed, the drone lifts off from the water. When the drone needs to land on the sea, the flight control computer 12 receives the landing command and transmits the signal to the electronic speed governor 13. The electronic speed governor 13 controls the propeller engine 30 on the wing 20 to slowly decelerate, causing the drone's flight altitude to gradually decrease. When the drone's double buoys 50 touch the water surface, the special side edge angle structure design reduces the impact force between the aircraft and the water surface during landing, improving the drone's landing safety factor. The propeller engine 30 slowly decelerates to a stop, the drone glides to a stop, and the drone lands safely.

[0048] The unique structural design of the float 50 of the present invention can reduce the air resistance experienced by traditional waterborne drones, improve fluid dynamics, and reduce overload when landing on wave surfaces, thereby enhancing the performance of existing seaplanes. Furthermore, the unique structural design of the float 50 enables the drone to take off and land on the water without requiring a reserve battery for return flight. When power is insufficient, it can land safely on the water, nearly doubling the drone's maximum operating time and thus its detection range. The structural design of the twin-propeller engine 30 of the present invention, with its dual-engine power supply, solves the problem of difficult takeoff for existing fixed-wing drones capable of waterborne takeoff and landing.

[0049] It should be noted that, in the present invention, the outer side refers to the end away from the central axis of the drone, and the inner side refers to the end close to the central axis of the drone.

[0050] The embodiments of the present invention are described above in conjunction with the accompanying drawings, but the present invention is not limited to the above-mentioned specific implementation methods. The above-mentioned specific implementation methods are merely illustrative and not restrictive. Under the guidance of the present invention, ordinary technicians in this field can also make many forms without departing from the scope of protection of the present invention and the claims, all of which are protected by the present invention.

Claims

1. A dual-float surface take-off and landing UAV, comprising a fuselage, wings, propeller engines, and tail wings; and two floats disposed below the fuselage and arranged symmetrically on both sides; characterized in that: The buoy is a bilaterally symmetrical special-shaped structure, with the bottom surface of the buoy tilting upward from the middle to both sides, so that the bottom of the buoy has a V-shaped cross-section, and the bottom oblique rise angle of the buoy, that is, the side edge angle β, is 20° to 25°; a step is formed at the rear end of the bottom surface of the buoy, and the tail of the buoy tilts upward from the upper end of the step to the rear, so that the tail is lifted off the water surface, and the tail oblique rise angle of the buoy, that is, the trailing edge angle γ, is 6° to 10°; the bow of the buoy tilts upward from the front end of the bottom to the front, so that the bow is lifted off the water surface, and the bow oblique rise angle of the buoy, that is, the leading edge angle α, is 20° to 26°; An arc-shaped wave suppression groove is formed at the outer end of the bottom surface of the buoy, and an arc-shaped wave suppression plate is formed at the outer edge of the wave suppression groove.

2. The dual-buoy water surface take-off and landing UAV according to claim 1, characterized in that: The height of the step at the rear end of the bottom surface of the buoy is 5% to 9% of the maximum width of the buoy.

3. The dual-buoy water surface take-off and landing UAV according to claim 1 or 2, characterized in that: The position of the step is 1 / 16 of the length of the buoy behind the buoyancy center of the buoy.

4. The dual-buoy surface take-off and landing UAV according to claim 1, characterized in that: The top surface of the buoy is a plane, connected to the fuselage through a connecting rod; the side surface of the buoy is a smooth curved surface connecting the bottom surface and the top surface.

5. The dual-buoy surface take-off and landing UAV according to claim 4, characterized in that: The connecting rods form a triangular frame to stabilize the fuselage and the pontoon.

6. The dual-buoy water surface take-off and landing UAV according to claim 1, characterized in that: A battery, a flight control computer, and an electronic speed regulator are arranged inside the fuselage; the battery is arranged in the rear section of the fuselage; the flight control computer is arranged in the middle section of the fuselage; and the electronic speed regulator is symmetrically arranged on the left and right sides of the flight control computer.

7. The dual-buoy water surface take-off and landing UAV according to claim 1, characterized in that: The propeller engines include a left propeller engine and a right propeller engine which are symmetrically installed on the left wing and the right wing, and the propellers of the two propeller engines are located in front of the wings.

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