A rotor blade suitable for tilting rotorcraft
A technology for tilting rotorcraft and propellers, applied in the field of propellers, which can solve the problems of difficult power source layout and complex control mechanism, and achieve the effects of light weight, large blade pitch change range and high reliability
Active Publication Date: 2022-04-12
BEIHANG UNIV
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Problems solved by technology
[0006] In order to solve the above problems, the present invention provides a rotor blade (also called a paddle rotor) suitable for a tilt rotor aircraft to solve the problems of difficult power source arrangement and complicated control mechanism of traditional tilt rotor aircraft; drive, and design a new collective pitch, longitudinal period variable pitch mechanism and electric tilting mechanism, which is more suitable for small and medium-sized unmanned tilt rotor aircraft, with simple structure, high reliability and light weight; compared with conventional helicopter rotor systems, the present invention A wider blade pitch range can be realized, meeting the demand for large pitch of the tiltrotor in the forward-flying axial flow state
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[0026] In order to make the above objects, features and advantages of the present invention more comprehensible, specific embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings. It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention.
[0027] see figure 1 , a rotor blade (also called a paddle rotor) suitable for a tiltrotor, including an electric drive assembly 100, a rotor paddle manipulation assembly 200, a tilt assembly 300 and blades 400, the electric drive assembly 100 is used to drive the paddle The blade 400 rotates at a high speed; the propeller control assembly 200 can adjust the installation angle of the propeller blade 400, which is used for collective pitch adjustment and longitudinal periodic pitch change of the propeller; the tilting component 300 is used to drive the electric drive component 100 and the pr...
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The invention provides a rotor blade suitable for a tilt rotor aircraft, comprising: an electric drive assembly for driving the blades to rotate at high speed; a rotor blade control assembly for realizing collective pitch adjustment and periodic pitch change of the rotor blade; The rotating assembly is used to drive the electric drive assembly and the rotor paddle control assembly to rotate; the electric drive assembly is connected to the rotor paddle control assembly, and the rotor paddle shaft in the electric drive assembly is arranged at the center of the rotor paddle control assembly. The two propeller control assemblies are respectively arranged at the left and right ends of the tilt assembly, and the chord length, twist angle and airfoil shape of the blades are constantly changing along the radial direction.
Description
technical field [0001] The invention relates to the technical field of unmanned aerial vehicles, in particular to a rotor blade suitable for a tilt rotor aircraft. Background technique [0002] Tilt rotor aircraft is similar to the tip of the wings of fixed-wing aircraft, each equipped with a set of rotor tilting components that can rotate between the horizontal position and the vertical position. When the aircraft takes off and lands vertically, the rotor axis is perpendicular to the ground , it is in the flying state of a horizontal helicopter, and can hover in the air, fly forward and backward, and fly sideways. After the tiltrotor takes off and reaches a certain speed, the rotor shaft can be tilted forward or backward at an angle of 90°, and it is in a horizontal state. The rotor is used as a pull propeller or a thrust propeller. At this time, the tiltrotor can fly at a higher speed for a long distance like a fixed-wing aircraft, that is, the power system of the tiltroto...
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IPC IPC(8): B64C29/00B64C27/14B64C27/52
CPCB64C29/0033B64C27/14B64C27/52
Inventor 刘振臣王强马铁林王英勋钱浩苗培鑫
Owner BEIHANG UNIV