Wind-resistant unmanned aerial vehicle

Abstract

The application provides an anti-wind unmanned aerial vehicle, comprising a duct structure, a power assembly is installed in the duct structure, the power assembly is used for providing lift for anti-wind unmanned aerial vehicle flight; and the duct structure is used for preventing external airflow from entering the inside of the duct structure; the duct structure is inclined in the level flight state, so that the air pressure difference between the inside and outside of the duct structure generates lift. 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, specifically relating to a wind-resistant unmanned aerial vehicle (UAV). Background Technology

[0002] Currently, multi-rotor vertical take-off and landing unmanned aerial vehicles (UAVs) are widely used in military research and civilian fields due to their advantages of low take-off and landing requirements and simple operation.

[0003] However, most existing vertical takeoff and landing (VTOL) drones employ a multi-rotor aerodynamic configuration, meaning they are equipped with multiple rotors to provide lift for takeoff and landing. Conventional multi-rotor VTOL drones, in terms of wind resistance, are prone to losing air compression under the rotors due to complex terrain and variable airflow in situations involving flight attitude and airflow interference. This reduces rotor lift and can lead to crashes. Furthermore, due to their rotor arm structure, multi-rotor drones suffer from high drag at high speeds, resulting in low efficiency and short cruise time at high speeds.

[0004] Therefore, how to provide a wind-resistant drone with excellent wind resistance and high-speed flight efficiency has become an urgent problem for those skilled in the art. Utility Model Content

[0005] Therefore, the technical problem to be solved by this application is to provide a wind-resistant drone with excellent wind resistance and high-speed flight efficiency.

[0006] To address the aforementioned problems, this application provides a wind-resistant drone, comprising:

[0007] The duct structure houses a power unit that provides lift for the wind-resistant drone. The duct structure also prevents external airflow from entering its interior. During level flight, the duct structure tilts to generate lift due to the pressure difference between the airflow inside and outside the duct.

[0008] Furthermore, the duct structure is cylindrical, with an inlet end and an outlet end, and the cross-sectional area of ​​the inlet end is larger than that of the outlet end.

[0009] Furthermore, the cross-section of the duct structure is an asymmetrical double-convex airfoil with a thickness of 10% to 15%.

[0010] Furthermore, the opening angle of the culvert structure is 2° to 5°;

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

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

[0013] Furthermore, the duct structure has an internal mounting shaft; the power assembly includes a first propeller assembly and a second propeller assembly; the first propeller assembly and the second propeller assembly are sequentially mounted on the mounting shaft in the axial direction; the wind-resistant UAV also includes a first motor and a second motor, the first motor being connected to the first propeller assembly; the second motor being connected to the second propeller assembly; the first motor is used to drive the first propeller assembly to rotate in a first direction, and the second motor is used to drive the second propeller assembly to rotate in a second direction; the first direction and the second direction are opposite.

[0014] Furthermore, the wind-resistant drone has a spindle-shaped propeller cover on the top of the mounting shaft, which is used to install avionics and flight control equipment.

[0015] Furthermore, a slipstream rudder assembly is installed at the bottom of the duct structure; the slipstream rudder assembly is used to adjust the take-off and landing attitude of the wind-resistant UAV; the slipstream rudder assembly includes a slipstream rudder; the slipstream rudder is in the shape of a straight airfoil.

[0016] Furthermore, the slipstream rudder assembly includes 4-6 slipstream rudders.

[0017] Furthermore, the wind-resistant drone also includes landing gear, which is evenly distributed around the outer periphery of the duct structure and is used to support the duct structure after takeoff and landing.

[0018] Furthermore, the length of the landing gear is 0.3m; and / or, the number of landing gears is 3.

[0019] The wind-resistant drone provided in this application has excellent wind resistance and high-speed flight efficiency. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the structure of a wind-resistant drone according to an embodiment of this application.

[0021] Figure 2 This is a top view of a wind-resistant drone according to an embodiment of this application.

[0022] Figure 3 This is a side view of a wind-resistant drone according to an embodiment of this application.

[0023] Figure 4 This is a rear view of a wind-resistant UAV according to an embodiment of this application;

[0024] Figure 5 This is a front view of a wind-resistant drone according to an embodiment of this application;

[0025] Figure 6 This is a bottom view of the wind-resistant drone according to an embodiment of this application.

[0026] The reference numerals in the attached figures are as follows:

[0027] 1. Duct structure; 2. Propeller cover; 3. Landing support; 4. Slipstream rudder; 5. Propeller. Detailed Implementation

[0028] See also Figure 1-6 As shown, a wind-resistant unmanned aerial vehicle (UAV) includes a ducted structure 1, within which a power unit is installed. The power unit provides lift for the wind-resistant UAV's flight. The ducted structure 1 also prevents external airflow from entering its interior. In level flight, the ducted structure 1 is tilted to generate lift due to the pressure difference between the airflow inside and outside the ducted structure. This application's wind-resistant UAV includes a UAV; further, the UAV includes a vertical takeoff and landing (VTOL) UAV. In this application, the ducted structure 1 acts as a barrier, preventing airflow from interfering with the air compression area of ​​the propeller 5 inside the duct, thus avoiding crashes caused by lift loss. This application's wind-resistant UAV possesses VTOL flight capability. This application employs a ducted fuselage aerodynamic layout. By tilting the duct frame, lift is generated using the pressure difference of the airflow flowing through the inner arm of the duct frame, thereby improving the flight efficiency and increasing the endurance of the wind-resistant UAV. The duct structure 1 is used to prevent external airflow from entering the interior of the duct structure 1, thereby improving the wind resistance of the UAV. In level flight, 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 inside and outside the duct structure 1 generates lift (principle: when flying at level, the UAV tilts as a whole, the duct arm tilts and creates an angle of attack with the incoming airflow. At this time, the airflow drawn in into the duct wall and the incoming airflow form an internal and external pressure difference, generating lift that is beneficial to flight).

[0029] The duct structure 1 is an inclined structure. During cruise flight, the UAV can utilize the pressure difference of the airflow passing through the internal arm of the duct structure 1 to generate lift, thereby improving the flight efficiency and increasing the endurance of the wind-resistant UAV. In contrast, conventional multi-rotor UAVs do not have a lifting body structure design in their fuselage, and the fuselage only adds unfavorable flight drag during cruise flight.

[0030] This application also discloses some embodiments in which the duct structure 1 is cylindrical, with an inlet end and an outlet end, the cross-sectional area of ​​the inlet end being larger than that of the outlet end. The design of a large opening and a small outlet in the duct wall further compresses the airflow passing through the duct. This design can provide greater lift than conventional rotary-wing UAVs at the same power, and achieve a longer flight time with the same battery capacity, thus improving endurance.

[0031] This application also discloses some embodiments in which the cross-section of the duct structure 1 is an asymmetrical double-convex airfoil with a thickness of 10% to 15%.

[0032] This application also discloses some embodiments in which the opening angle of the duct structure 1 is 2° to 5°;

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

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

[0035] This application also discloses some embodiments. The ducted structure 1 has an internal mounting shaft; the power assembly includes a first propeller assembly and a second propeller assembly; the first and second propeller assemblies are sequentially mounted axially on the mounting shaft; the wind-resistant UAV also includes a first motor and a second motor, the first motor being connected to the first propeller assembly; the second motor being connected to the second propeller assembly; the first motor drives the first propeller assembly to rotate in a first direction, and the second motor drives the second propeller assembly to rotate in a second direction; the first direction and the second direction are opposite. The first propeller 5 is a forward-rotating propeller; the second propeller 5 is a counter-rotating propeller; that is, the vertical takeoff UAV of this application adopts a coaxial counter-rotating ducted aerodynamic layout design. The UAV of this application adopts a single-ducted aerodynamic layout, with two motors coaxially mounted in the center of the duct, one motor connected to the forward-rotating propeller 5 and the other connected to the counter-rotating propeller 5, providing lift for the wind-resistant UAV's flight. The ducted structure 1 can provide lift for the UAV during tilted flight.

[0036] The wind-resistant drone adopts ducted vertical take-off and landing technology. Compared with conventional multi-rotor vertical take-off and landing drones, its advantage lies in the use of a coaxial counter-rotating ducted design, which means that the two layers of blades are installed on the same axis but rotate in opposite directions. This not only balances the deflection torque of unidirectional rotation, but also allows the first-stage blade to provide "pre-compression" for the second-stage blade, resulting in a larger intake compression volume for the second stage.

[0037] Regarding wind resistance, in existing technologies, multi-rotor UAVs are prone to losing the air compression zone under the propeller 5 due to complex terrain and variable airflow when facing complex terrain and changing airflow conditions. This reduces the lift of the rotor and can lead to a crash. However, this application uses a coaxial counter-rotor duct structure 1, which acts as a barrier to prevent airflow from interfering with the air compression zone of the propeller 5 within the duct, thus avoiding crashes caused by loss of lift.

[0038] In terms of power safety, the coaxial counter-rotating propeller power structure of this application adopts a dual-motor design and has the capability of single-motor take-off and landing; that is, in the event of a failure of one motor, a single motor can provide power to ensure the safe landing of the wind-resistant UAV.

[0039] This application also discloses some embodiments in which a spindle-shaped propeller cover 2 is provided on the top of the mounting shaft. The propeller cover 2 is used to install avionics and flight control equipment. The propeller cover 2 is located in the center of the duct.

[0040] This application also discloses some embodiments, wherein a slipstream rudder 4 group is provided at the bottom of the duct structure 1; the slipstream rudder 4 group is used to adjust the take-off and landing attitude of the wind-resistant UAV; the slipstream rudder 4 group includes a slipstream rudder 4; the slipstream rudder 4 is in the shape of a straight airfoil.

[0041] This application also discloses some embodiments in which the slipstream rudder group 4 includes 4-6 slipstream rudders 4. When the slipstream rudder group 4 includes 6 slipstream rudders 4, 6 independently controllable slipstream rudders 4 are symmetrically installed on the bottom of the duct along the central axis to control the flight attitude of the UAV.

[0042] This application also discloses some embodiments, in which the wind-resistant drone also includes a landing gear, which is evenly disposed on the outer periphery of the duct structure 1, and is used to support the duct structure 1 after takeoff and landing.

[0043] This application also discloses some embodiments in which the length of the landing gear is 0.3m; and / or, the number of landing gears is 3. Three landing gears are installed on the outer periphery of the duct structure 1, which can be used as vertical take-off and landing support legs.

[0044] In this application, the anti-axis ducted unmanned aerial vehicle (UAV) adjusts its takeoff and landing attitude using six slipstream rudders 4 mounted at the bottom of the duct. The UAV's flight thrust is provided by a coaxial thrust propeller 5 installed within the duct, which, in conjunction with the deflection control of the slipstream rudders 4 at the bottom of the duct, enables heading and fuselage attitude control during level flight.

[0045] The vertical takeoff and landing coaxial counter-rotating ducted unmanned aerial vehicle (UAV) of this application adopts the following technical solution:

[0046] A novel coaxial counter-rotating ducted unmanned aerial vehicle (UAV) aerodynamic layout includes a ducted structure 1 fuselage, a spindle-shaped propeller cover 2, a 3-point take-off and landing support 3, a slipstream rudder 4, a forward propeller, and a counter-rotating propeller.

[0047] The main fuselage structure consists of a duct structure 1; the duct structure 1 has an asymmetrical double-convex airfoil with a thickness of 10%–15%, a duct opening angle of 2°–5°, a duct diameter of 0.5m–0.8m, and a duct height of 0.5m–0.8m; the slipstream rudder 4 is a symmetrical double-convex airfoil with a relative thickness of 10%–15%, and the slipstream rudder 4 is a straight airfoil; the three-point vertical takeoff and landing (VTOL) support 3 is installed on the outer wall of the duct structure 1, symmetrically distributed around the central axis of the duct structure 1. Two VTOL electric rotors are installed on the central support of the duct structure 1, and the two propellers 5 are coaxial counter-rotating propellers, with a spindle-shaped propeller cover 2 installed at the center of the top of the duct.

[0048] This application relates to a coaxial reverse-rotor ducted unmanned aerial vehicle (UAV). Its duct structure 1 acts as a barrier during flight, preventing airflow interference with the air compression area of ​​the propeller 5 within the duct during windy conditions, thus improving wind resistance. Furthermore, by tilting the duct structure 1, lift is generated using the pressure difference of the airflow passing through the internal arms of the duct structure 1, thereby improving the flight efficiency and increasing the endurance of the wind-resistant UAV. Regarding power safety, this utility model's coaxial reverse-rotor power structure adopts a dual-motor design, possessing single-motor takeoff and landing capability; that is, in the event of a motor failure, a single motor can provide power to ensure the safe landing of the wind-resistant UAV. Therefore, the coaxial reverse-rotor ducted UAV has advantages such as simple structure, excellent aerodynamic performance, and good wind resistance.

[0049] In this application, the aerodynamic layout of the UAV includes a ducted structure 1 fuselage, a propeller cover 2, a take-off and landing bracket 3, a slipstream rudder 4, and a propeller 5.

[0050] The shape parameters are determined based on the overall indicator requirements, specifically as follows:

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

[0052] The ducted fuselage is 0.35m high and 0.7m in diameter.

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

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

[0055] (3) Lifting and lowering support 3: (length, number of supports),

[0056] The lifting and lowering support frame is 0.3m in length, and there are 3 to 4 frames in total.

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

[0058] A symmetrical, double-convex airfoil with 4 to 6 slipstream rudders and a relative thickness of 10% to 15%.

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

[0060] The propeller 5 consists of one forward-rotating propeller and one reverse-rotating propeller, with a propeller size of 25-30 inches and a number of 6 blades.

[0061] Example 1: The UAV in this example adopts a coaxial counter-rotating ducted aerodynamic layout design.

[0062] Duct structure 1 has a height of 0.35m and a fuselage diameter of 0.7m; propeller cover 2 has a fuselage height of 0.35m and a fuselage diameter of 0.7m; takeoff and landing support 3 has a length of 0.3m and a number of supports of 3; slipstream rudder 4 has a number of 6 and is a symmetrical double-convex airfoil with a relative thickness of 12%; propeller 5 consists of one positive propeller and one negative propeller, with a propeller size of 25-30 inches and a number of 6 blades.

[0063] This embodiment describes a coaxial reverse-propeller ducted unmanned aerial vehicle (UAV). Its duct structure 1 acts as a barrier during flight, blocking airflow interference in the air compression zone of the propeller 5 within the duct during windy conditions, thus improving wind resistance. Furthermore, by tilting the duct structure 1, lift is generated using the pressure difference of the airflow passing through the internal arms of the duct structure 1, thereby improving the flight efficiency and increasing the endurance of the wind-resistant UAV. Regarding power safety, this utility model's coaxial reverse-propeller power structure adopts a dual-motor design, possessing single-motor takeoff and landing capability; that is, in the event of a motor failure, a single motor can provide power to ensure the safe landing of the wind-resistant UAV. Therefore, the coaxial reverse-propeller ducted UAV has advantages such as simple structure, excellent aerodynamic performance, and good wind resistance.

[0064] It will be readily understood by those skilled in the art that the aforementioned advantageous methods can be freely combined and superimposed without conflict.

[0065] The above are merely preferred embodiments of this application and are not intended to limit this application. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of this application should be included within the protection scope of this application. The above are merely preferred embodiments of this application. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the technical principles of this application, and these improvements and modifications should also be considered within the protection scope of this application.

Claims

1. A wind-resistant unmanned aerial vehicle, characterized in that, include: A duct structure (1) is provided, and a power assembly is installed inside the duct structure (1) to provide lift for the flight of the wind-resistant UAV; and the duct structure (1) is used to prevent external airflow from entering the interior of the duct structure (1); in level flight, the duct structure (1) is tilted so that the air pressure difference inside and outside the duct structure (1) generates lift. The duct structure (1) has an internal mounting shaft; the power assembly includes a first propeller assembly and a second propeller assembly; the first propeller assembly and the second propeller assembly are sequentially mounted on the mounting shaft in the axial direction; the wind-resistant UAV also includes a first motor and a second motor, the first motor being connected to the first propeller assembly; The second motor is connected to the second propeller assembly; the first motor is used to drive the first propeller assembly to rotate in a first direction, and the second motor is used to drive the second propeller assembly to rotate in a second direction; the first direction is opposite to the second direction.

2. The wind-resistant drone of claim 1, wherein The culvert structure (1) is cylindrical, and the cylindrical structure has 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.

3. The wind-resistant drone of claim 1, wherein, The cross-section of the duct structure (1) is an asymmetrical double-convex airfoil with a thickness of 10% to 15%.

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

5. The wind-resistant drone of claim 4, wherein, The top of the mounting shaft is provided with a spindle-shaped propeller cover (2), which is used to install avionics and flight control equipment.

6. The wind-resistant drone of claim 1, wherein The bottom of the duct structure (1) is provided with a slipstream rudder (4) group; the slipstream rudder (4) group is used to adjust the take-off and landing attitude of the wind-resistant UAV; the slipstream rudder (4) group includes a slipstream rudder (4); the slipstream rudder (4) is in the shape of a straight airfoil.

7. The wind-resistant drone of claim 6, wherein, The slipstream rudder (4) group includes 4-6 slipstream rudders (4).

8. The wind-resistant drone of claim 1, wherein, The wind-resistant UAV also includes a landing gear, which is evenly distributed on the outer periphery of the duct structure (1) and is used to support the duct structure (1) after takeoff and landing.

9. The wind-resistant drone of claim 8, wherein, The length of the landing gear is 0.3m; and / or, the number of landing gears is 3.

Images