Wind-resistant unmanned aerial vehicle

Abstract

The invention provides a wind-resistant unmanned aerial vehicle which comprises a duct structure, a power assembly is installed in the duct structure, and the power assembly is used for providing lift force for flight of the wind-resistant unmanned aerial vehicle; the duct structure is used for preventing external airflow from entering the duct structure; in the level flight state, the duct structure inclines, so that the air flow pressure difference inside and outside the duct structure generates lift force. The anti-wind unmanned aerial vehicle has excellent anti-wind performance and high high-speed flight efficiency.

Description

Technical Field

[0001] This application pertains to the field of aerospace technology, and particularly relates to an anti-wind unmanned aerial vehicle (UAV). Background Art

[0002] Currently, multi-rotor vertical takeoff and landing UAVs have been widely used in military research and civilian fields due to their advantages of low takeoff and landing requirements and simple operation.

[0003] However, most of the existing vertical takeoff and landing UAVs adopt a multi-rotor aerodynamic layout, that is, multiple rotor propellers are installed on the UAV to provide lift for takeoff, landing, and flight. In terms of anti-wind performance, conventional multi-rotor vertical takeoff and landing UAVs are prone to losing the air compression area under the propellers due to flight attitude and airflow interference in complex terrain and variable airflow conditions, resulting in a reduction in the lift of the rotors and causing crash accidents. Moreover, due to the structure of the rotor arms of multi-rotor UAVs, they have the disadvantage of high drag at high speeds, that is, the UAV has low efficiency and short cruise time during high-speed flight.

[0004] Therefore, how to provide an anti-wind UAV with excellent anti-wind performance and high high-speed flight efficiency has become an urgent problem for those skilled in the art to solve. Summary of the Invention

[0005] Therefore, the technical problem to be solved by this application is to provide an anti-wind UAV with excellent anti-wind performance and high high-speed flight efficiency.

[0006] To solve the above problems, this application provides an anti-wind UAV, including:

[0007] A ducted structure, in which a power component is installed. The power component is used to provide lift for the flight of the anti-wind UAV; and the ducted structure is used to prevent external airflow from entering the interior of the ducted structure; in the level flight state, the ducted structure is inclined so that the air pressure difference inside and outside the ducted structure generates lift.

[0008] Further, the ducted structure is cylindrical, with an inlet end and an outlet end. The cross-sectional area of the inlet end is larger than the cross-sectional area of the outlet end.

[0009] Further, the cross-section of the ducted structure is an asymmetric double convex airfoil with a thickness of 10% - 15%.

[0010] Further, the opening angle of the ducted structure is 2° - 5°;

[0011] And / or, the diameter of the ducted structure is 0.5 m - 0.8 m;

[0012] And / or, the height of the ducted structure is 0.5 m - 0.8 m.

[0013] Further, an installation shaft is provided inside the ducted structure; the power assembly includes a first propeller group and a second propeller group; the first propeller group and the second propeller group are sequentially arranged on the installation shaft in the axial direction; the wind-resistant unmanned aerial vehicle further includes a first motor and a second motor, the first motor is connected to the first propeller group; the second motor is connected to the second propeller group; the first motor is used to drive the first propeller group to rotate in a first direction, and the second motor is used to drive the second propeller group to rotate in a second direction; the first direction is opposite to the second direction.

[0014] For the wind-resistant unmanned aerial vehicle according to claim 5, a spindle-shaped propeller cover is provided at the top of the installation shaft, and the propeller cover is used to install avionics and flight control equipment.

[0015] Further, a slipstream rudder group is provided at the bottom of the ducted structure; the slipstream rudder group is used to adjust the takeoff and landing attitude of the wind-resistant unmanned aerial vehicle; the slipstream rudder group includes slipstream rudders; the shape of the slipstream rudders is a straight airfoil.

[0016] Further, the slipstream rudder group includes 4 - 6 slipstream rudders.

[0017] Further, the wind-resistant unmanned aerial vehicle further includes landing brackets, and the landing brackets are evenly arranged on the outer periphery of the ducted structure, and the landing brackets are used to support the ducted structure after takeoff and landing.

[0018] Further, the length of the landing brackets is 0.3 m; and / or, the number of the landing brackets is 3.

[0019] The wind-resistant unmanned aerial vehicle provided by the present application. The wind-resistant unmanned aerial vehicle of the present application has excellent wind resistance performance and high high-speed flight efficiency. Description of the Drawings

[0020] Figure 1 It is a schematic structural diagram of the wind-resistant unmanned aerial vehicle according to an embodiment of the present application.

[0021] Figure 2 It is a top view of the wind-resistant unmanned aerial vehicle according to an embodiment of the present application.

[0022] Figure 3 It is a side view of the wind-resistant unmanned aerial vehicle according to an embodiment of the present application.

[0023] Figure 4 It is a rear view of the wind-resistant unmanned aerial vehicle according to an embodiment of the present application;

[0024] Figure 5 It is a front view of the wind-resistant unmanned aerial vehicle according to an embodiment of the present application;

[0025] Figure 6 It is a bottom view of the wind-resistant unmanned aerial vehicle according to an embodiment of the present application.

[0026] The reference numerals are shown as:

[0027] 1. Duct structure; 2. Propeller shroud; 3. Takeoff and landing support; 4. Slipstream rudder; 5. Propeller. Detailed implementation manners

[0028] Referring to Figures 1-6 As shown, an anti-wind unmanned aerial vehicle includes a duct structure 1. A power assembly is installed inside the duct structure 1. The power assembly is used to provide lift for the flight of the anti-wind unmanned aerial vehicle; and the duct structure 1 is used to prevent external airflows from entering the inside of the duct structure 1. When in the level flight state, the duct structure 1 is inclined so that the air pressure difference between the inside and outside of the duct structure 1 generates lift. The anti-wind unmanned aerial vehicle of the present application includes an unmanned aerial vehicle; further, the unmanned aerial vehicle includes a vertical takeoff and landing unmanned aerial vehicle. In the present application, the duct structure 1 can serve as a barrier, which can block the airflow from interfering with the air compression area of the propeller 5 inside the duct, and avoid a crash accident caused by the loss of lift. The anti-wind unmanned aerial vehicle of the present application has the ability of vertical takeoff and landing flight. The present application adopts a duct fuselage aerodynamic layout. By tilting the duct frame, the air pressure difference generated by the airflow passing through the inner arm of the duct frame is used to generate lift, thereby improving the flight efficiency of the anti-wind unmanned aerial vehicle and increasing the endurance time. The duct structure 1 is used to prevent external airflows from entering the inside of the duct structure 1, so that the unmanned aerial vehicle improves its anti-wind ability; when in the level flight state, the duct structure 1 will tilt at a certain angle, that is, the overall attitude of the fuselage will tilt, so that the air pressure difference between the inside and outside of the duct structure 1 generates lift (Principle: When in level flight, the whole unmanned aerial vehicle tilts, the duct arm tilts to form an angle of attack with the oncoming flow. At this time, the airflow inhaled inside the duct wall and the oncoming flow of flight form an internal and external pressure difference, generating lift beneficial to flight.).

[0029] The duct structure 1 is an inclined structure. During cruise flight, the unmanned aerial vehicle can tilt the duct structure 1, and the air pressure difference generated by the airflow passing through the inner arm of the duct structure 1 can be used to generate lift, thereby improving the flight efficiency of the anti-wind unmanned aerial vehicle and increasing the endurance time. While the conventional multi-rotor unmanned aerial vehicle has no lift body structure design on the fuselage, and only additional adverse flight resistance is added to the fuselage during cruise flight.

[0030] The present application also discloses some embodiments. The duct structure 1 is cylindrical, with an inlet end and an outlet end. The cross-sectional area of the inlet end is larger than that of the outlet end. The design of the large opening and small outlet of the duct wall further compresses the airflow passing through the duct. This design can provide greater lift than the conventional rotor unmanned aerial vehicle under the same power, and can obtain a longer flight time under the same capacity battery, improving the endurance ability.

[0031] The present application also discloses some embodiments. The cross-section of the duct structure 1 is an asymmetric double convex airfoil with a thickness of 10% - 15%.

[0032] The present application also discloses some embodiments. The opening angle of the duct structure 1 is 2° - 5°;

[0033] And / or, the diameter of the duct structure 1 is 0.5 m to 0.8 m;

[0034] And / or, the height of the duct structure 1 is 0.5 m to 0.8 m.

[0035] This application also discloses some embodiments. An installation shaft is provided inside the duct structure 1; the power assembly includes 5 groups of first propellers and 5 groups of second propellers; the 5 groups of first propellers and the 5 groups of second propellers are arranged on the installation shaft in sequence along the axial direction; the wind-resistant unmanned aerial vehicle also includes a first motor and a second motor, the first motor is connected to the 5 groups of first propellers; the second motor is connected to the 5 groups of second propellers; the first motor is used to drive the 5 groups of first propellers to rotate in a first direction, and the second motor is used to drive the 5 groups of second propellers to rotate in a second direction; the first direction is opposite to the second direction. The first propeller 5 is a right-handed propeller; the second propeller 5 is a counter-rotating propeller; that is, the vertical take-off unmanned aerial vehicle of this application adopts a coaxial contra-rotating propeller duct aerodynamic layout design. The unmanned aerial vehicle of this application adopts a single-duct aerodynamic layout, with 2 motors coaxially installed in the center of the duct, one motor connected to the right-handed propeller 5 and the other connected to the counter-rotating propeller 5, providing lift for the flight of the wind-resistant unmanned aerial vehicle. The duct structure 1 can provide lift for the unmanned aerial vehicle during inclined flight.

[0036] The wind-resistant unmanned aerial vehicle adopts a ducted vertical take-off and landing technology. Compared with conventional multi-rotor vertical take-off and landing unmanned aerial vehicles, its advantage lies in the adoption of a coaxial contra-rotating propeller duct design, that is, the double-layer propeller blades are coaxially installed but rotate in opposite directions, not only balancing the deflection torque of the single-direction rotation, but also the first-stage propeller can provide "pre-compression" for the second-stage propeller, and the second stage has a larger intake air compression volume.

[0037] In terms of wind resistance performance, in the prior art, when multi-rotor unmanned aerial vehicles face complex terrain and changing airflows, it is easy to lose the air compression area under the propeller 5 due to flight attitude and airflow interference, resulting in a reduction in the lift of the rotor and causing a crash accident. However, this application adopts a coaxial contra-rotating propeller duct structure 1, and its duct structure 1 can serve as a barrier to block the airflow from interfering with the air compression area of the propeller 5 in the duct, avoiding a crash accident caused by the loss of lift.

[0038] In terms of power safety, the coaxial contra-rotating propeller power structure of this application adopts a dual-motor design and has the ability to take off and land with a single motor; that is, when one motor fails, a single motor can provide power to meet the requirement for the safe landing of the wind-resistant unmanned aerial vehicle.

[0039] This application also discloses some embodiments. A spindle-shaped propeller cover 2 is provided at the top of the installation shaft, and the propeller cover 2 is used to install avionics and flight control equipment. The propeller cover 2 is arranged in the center of the duct.

[0040] The present application also discloses some embodiments. Four groups of slipstream rudders 4 are provided at the bottom of the ducted structure 1; the four groups of slipstream rudders 4 are used to adjust the take-off and landing attitude of the wind-resistant unmanned aerial vehicle; the four groups of slipstream rudders 4 include the slipstream rudders 4; the shape of the slipstream rudders 4 is a straight airfoil.

[0041] The present application also discloses some embodiments. The four groups of slipstream rudders 4 include 4 - 6 slipstream rudders 4. When the four groups of slipstream rudders 4 include 6 slipstream rudders 4, 6 independently controllable deflected slipstream rudders 4 are symmetrically installed at the bottom of the ducted structure of the present application along the central axis to control the flight attitude of the unmanned aerial vehicle.

[0042] The present application also discloses some embodiments. The wind-resistant unmanned aerial vehicle further includes a landing support. The landing support is evenly arranged on the outer periphery of the ducted structure 1, and the landing support is used to support the ducted structure 1 after take-off and landing.

[0043] The present application also discloses some embodiments. The length of the landing support is 0.3 m; and / or, the number of the landing supports is 3. A three-point landing support is installed on the outer periphery of the ducted structure 1 and can be used as a support leg after vertical take-off and landing.

[0044] During the take-off and landing process of the coaxial contra-rotating ducted unmanned aerial vehicle of the present application, the adjustment of the take-off and landing attitude of the aircraft is realized by the 6 slipstream rudders 4 installed at the bottom of the ducted structure. The flight thrust of the unmanned aerial vehicle is provided by the coaxial thrust propellers 5 installed in the ducted structure, and in cooperation with the deflection control of the slipstream rudders 4 installed at the bottom of the ducted structure, the course and fuselage attitude control during the level flight are realized.

[0045] The vertical take-off and landing coaxial contra-rotating ducted unmanned aerial vehicle of the present application adopts the following technical solutions:

[0046] A new type of coaxial contra-rotating ducted unmanned aerial vehicle aerodynamic layout includes a ducted structure 1 fuselage, a spindle-shaped propeller cover 2, a three-point take-off and landing support 3, slipstream rudders 4, a forward-rotating propeller, and a reverse-rotating propeller.

[0047] The main body structure of the fuselage is composed of the ducted structure 1; the cross-section of the ducted structure 1 is an asymmetric double-convex airfoil with a thickness of 10% - 15%, the opening angle of the ducted structure is 2° - 5°, the ducted diameter is 0.5 m - 0.8 m, and the ducted height is 0.5 m - 0.8 m; the slipstream rudders 4 are symmetric double-convex airfoils with a relative thickness of 10% - 15%, and the slipstream rudders 4 are straight airfoils; the three-point vertical take-off and landing supports 3 are installed on the outer wall of the ducted structure 1 and are symmetrically distributed along the central axis of the ducted structure 1. Two vertical take-off and landing electric rotors are installed on the central support of the ducted structure 1, the two propellers 5 are coaxial contra-rotating propellers, and a spindle-shaped propeller cover 2 is installed at the central position on the top of the ducted structure.

[0048] The coaxial contra-rotating ducted drone of the present application. Its ducted structure 1 can serve as a barrier during flight. When flying in strong wind weather, it blocks the airflow from interfering with the air compression area of the propeller 5 inside the duct, improving the wind resistance performance. It can also tilt the ducted structure 1 to generate lift by using the airflow pressure difference flowing through the inner arm of the ducted structure 1, thereby improving the flight efficiency of the wind-resistant drone and increasing the endurance time. In terms of power safety, the coaxial contra-rotating power structure of the present invention adopts a dual-motor design and has the ability to take off and land with a single motor; that is, when a motor fails, a single motor can provide power to ensure the requirement for the safe landing of the wind-resistant drone. Therefore, the coaxial contra-rotating ducted drone has the advantages of simple structure, excellent aerodynamic performance, and good wind resistance performance.

[0049] In the present application, the aerodynamic layout of the drone includes a ducted structure 1 fuselage, a propeller cover 2, a landing gear 3, a slipstream rudder 4, and a propeller 5.

[0050] Based on the overall index requirements, the shape parameters are determined, specifically

[0051] (1) Ducted fuselage: Some parameters (height, diameter),

[0052] The height of the ducted fuselage is 0.35 m and the diameter of the fuselage is 0.7 m.

[0053] (2) Propeller cover 2: Some parameters (height, diameter),

[0054] The height of the fuselage is 0.35 m and the diameter of the fuselage is 0.7 m.

[0055] (3) Landing gear 3: (Length, number of supports,),

[0056] The length of the landing gear 3 is 0.3 m and the number of supports is 3 - 4.

[0057] (4) Slipstream rudder 4: Some parameters (number of rudder surfaces, relative thickness),

[0058] The number of slipstream rudders 4 is 4 - 6, and the symmetric double convex airfoil with a relative thickness of 10% - 15%.

[0059] (5) Propeller 5: Some parameters (number, propeller size, number of propeller blades),

[0060] The propeller 5 is a pair of forward rotating propellers and a pair of reverse rotating propellers, the propeller size is 25 - 30 inches, and the number of propeller blades is 6.

[0061] Embodiment 1

[0062] The drone of this embodiment adopts a coaxial contra-rotating ducted aerodynamic layout design.

[0063] The ducted structure 1 has a height of 0.35 m and a fuselage diameter of 0.7 m; the nacelle 2 has a fuselage height of 0.35 m and a fuselage diameter of 0.7 m; the landing gear 3 has a length of 0.3 m and the number of supports is 3; the slipstream rudder 4 has 6 slipstream rudders 4 and a symmetric double convex airfoil with a relative thickness of 12%; the propellers 5 are one pair of right-handed propellers and one pair of left-handed propellers, the propeller size is 25 - 30 inches, and the number of propeller blades is 6 blades.

[0064] The coaxial contra-rotating ducted UAV of this embodiment. Its ducted structure 1 can serve as a barrier during flight. When flying in strong wind weather, it blocks the air flow to interfere with the air compression area of the propeller 5 in the duct, improving the wind resistance performance. Also, by tilting the ducted structure 1, it utilizes the air pressure difference of the air flow passing through the inner arm of the ducted structure 1 to generate lift, thereby improving the flight efficiency of the wind-resistant UAV and increasing the endurance time. In terms of power safety, the coaxial contra-rotating power structure of the present invention adopts a dual-motor design and has the ability to take off and land with a single motor; that is, when one motor fails, a single motor can provide power to ensure the requirement for the safe landing of the wind-resistant UAV. Therefore, the coaxial contra-rotating ducted UAV has the advantages of simple structure, excellent aerodynamic performance, and good wind resistance performance.

[0065] It is easy for those skilled in the art to understand that, on the premise of no conflict, the above-mentioned advantageous ways can be freely combined and superimposed.

[0066] The above are only the preferred embodiments of this application, and are not intended to limit this application. Any modifications, equivalent replacements, and improvements made within the spirit and principle of this application shall be included in the protection scope of this application. The above is only the preferred implementation manner of this application. It should be noted that for those of ordinary skill in the art in this technical field, without departing from the technical principle of this application, several improvements and modifications can still be made, and these improvements and modifications should also be regarded as the protection scope of this application.

Claims

1. An anti-wind drone, characterized in that, Comprising: A ducted structure (1), within which a power assembly is installed. The power assembly is used to provide lift for the flight of the wind-resistant unmanned aerial vehicle. And the ducted structure (1) is used to prevent external airflows from entering the interior of the ducted structure (1). When in the level flight state, the ducted structure (1) is inclined so that the air pressure difference between the inside and outside of the ducted structure (1) generates lift.

2. The wind-resistant unmanned aerial vehicle according to claim 1, wherein The ducted structure (1) is cylindrical, the cylinder having an inlet end and an outlet end, and the cross-sectional area of the inlet end is larger than the cross-sectional area of the outlet end.

3. The anti-wind drone according to claim 1, characterized in that, The cross-section of the ducted structure (1) is an asymmetric double convex airfoil with a thickness of 10% - 15%.

4. The wind-resistant unmanned aerial vehicle according to claim 1, wherein, The opening angle of the ducted structure (1) is 2° - 5°; And / or, the diameter of the ducted structure (1) is 0.5 m - 0.8 m; And / or, the height of the ducted structure (1) is 0.5 m - 0.8 m.

5. The wind-resistant unmanned aerial vehicle according to claim 1, wherein, An installation shaft is provided inside the ducted structure (1). The power assembly includes a first propeller (5) group and a second propeller (5) group. The first propeller (5) group and the second propeller (5) group are arranged on the installation shaft in sequence axially. The wind-resistant unmanned aerial vehicle further includes a first motor and a second motor. The first motor is connected to the first propeller (5) group. The second motor is connected to the second propeller (5) group. The first motor is used to drive the first propeller (5) group to rotate in a first direction, and the second motor is used to drive the second propeller (5) group to rotate in a second direction; The first direction is opposite to the second direction.

6. The wind-resistant unmanned aerial vehicle according to claim 5, characterized in that, A spindle-shaped propeller cover (2) is provided at the top of the installation shaft, and the propeller cover (2) is used to install avionics and flight control equipment.

7. The wind-resistant unmanned aerial vehicle according to claim 1, wherein A group of slipstream rudders (4) is provided at the bottom of the ducted structure (1). The group of slipstream rudders (4) is used to adjust the takeoff and landing attitude of the wind-resistant unmanned aerial vehicle. The group of slipstream rudders (4) includes slipstream rudders (4). The shape of the slipstream rudders (4) is a straight airfoil.

8. The wind-resistant unmanned aerial vehicle according to claim 7, wherein, The group of slipstream rudders (4) includes 4 - 6 slipstream rudders (4).

9. The wind-resistant unmanned aerial vehicle according to claim 1, wherein, The wind-resistant unmanned aerial vehicle further includes landing brackets, which are evenly arranged on the outer periphery of the ducted structure (1), and the landing brackets are used to support the ducted structure (1) after takeoff and landing.

10. The wind-resistant unmanned aerial vehicle according to claim 9, characterized in that, The length of the landing brackets is 0.3 m; and / or, the number of the landing brackets is 3.

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