A dual-duct unmanned aerial vehicle
A technology of unmanned aerial vehicle and aircraft, applied in the field of unmanned aerial vehicles, can solve the problems of slow duct response and complicated control process, and achieve the effects of low manufacturing cost, stable flight, and reduced control difficulty
Active Publication Date: 2022-03-11
涵涡智航科技(玉溪)有限公司
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Problems solved by technology
However, since the first duct and the second duct in the UAV include the duct itself, the motor, and the propeller, the moment of inertia of the duct is very large. The rotation of the UAV must have a large output torque, the response speed of the duct is slow, and the duct needs to be continuously rotated back and forth to keep the flight stability of the UAV, and the control process is more complicated
Method used
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Embodiment
[0031] combine Figure 1-3 As shown, this embodiment discloses a dual-duct unmanned aerial vehicle, which includes a frame 1 , a flight control assembly 2 , a power source assembly 3 , a first duct assembly 4 and a second duct assembly 5 .
[0032] Wherein the first duct assembly 4 and the second duct assembly 5 are relatively arranged at the two ends of the frame 1. In this embodiment, the length direction of the frame 1 is used as the length of the aircraft fuselage, and the first duct assembly The side where 4 is located is the direction of the nose, and the side where the second duct assembly 5 is located is the direction of the tail. The flight control assembly 2 and the power source assembly 3 are installed in the middle of the frame 1.
[0033] Specifically, such as figure 2 As shown, wherein the first duct assembly 4 includes a first duct housing 401, a first propeller 402, a first steering surface group 403 and a third steering surface group 404; the second duct ass...
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The invention relates to a double-duct unmanned aerial vehicle, wherein the first propeller is coaxially arranged inside the first duct casing, and the second propeller is coaxially arranged inside the second duct casing; the first rudder surface group and the second The three rudder surface groups are respectively located under the first propeller, the second rudder surface group and the fourth rudder surface group are respectively located under the second propeller; the first rudder surface group and the second rudder surface group are respectively perpendicular to the first duct shell The connecting line between the axis and the axis of the second ducted shell; the third rudder surface group and the fourth rudder surface group are respectively parallel to the connecting line where the axis of the first ducted shell and the axis of the second ducted shell are located, And respectively about the axis of the first duct shell and the axis of the second duct shell are symmetrical to the connecting line, the use of four rudder surface groups does not need to change the speed of the engine and the direction of the lift surface of the duct, by controlling the deflection angle of the rudder surface You can control the aircraft, quickly adjust the attitude of the aircraft, the response speed is fast, and the flight process of the aircraft is stable.
Description
technical field [0001] The invention belongs to the technical field of unmanned aerial vehicles, and relates to a double-duct unmanned aerial vehicle. Background technique [0002] The existing double-duct technology controls the attitude of the UAV by changing the angle between the propeller rotation plane and the horizontal plane. To change the angle between the propeller rotation plane and the horizontal plane, it is necessary to turn the propeller, engine and duct, but the weight of the propeller, engine and duct accounts for a large proportion of the weight of the entire unmanned aerial vehicle, and when the propeller in the duct rotates at a high degree, the moment of inertia of the propeller is large, and it is necessary to control the deflection of the duct. The torque overcomes the moment of inertia of the propeller, so this technique cannot adjust the attitude quickly. [0003] Chinese patent document CN107042883B discloses a double-duct unmanned aerial vehicle wi...
Claims
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IPC IPC(8): B64C11/00B64C27/20B64C9/00
CPCB64C11/00B64C27/20B64C9/00B64U50/14
Inventor 张汝康何旭东赵荟文
Owner 涵涡智航科技(玉溪)有限公司