Variable-diameter rotor device and variable-pitch control method thereof

Abstract

The invention provides a variable-diameter rotor device and a variable-pitch control method thereof. The variable-diameter rotor device comprises blades, a transmission mechanism, a blade contraction and extension structure, a blade variable-pitch structure and a contraction rod unloading structure. The blade contraction and extension structure comprises a propeller hub, a central shaft, a contraction disc, contraction rods and a variable-pitch sleeve, the propeller hub is fixedly connected with the central shaft, the contraction disc is connected with the pair of contraction rods through rotating hinges, and the other ends of the contraction rods are connected with blades through the variable-pitch sleeve; the blade variable-pitch structure comprises a variable-pitch disc, folding rods, variable-pitch connecting pieces and variable-pitch pull rods, the variable-pitch disc is connected with a connecting rod mechanism composed of the two pairs of folding rods through rotating hinges, the other ends of the folding rods are connected with the variable-pitch connecting pieces, and the variable-pitch connecting pieces are connected with the upper ends of the blades through the variable-pitch pull rods. According to the invention, by controlling the contraction disc and the variable-pitch disc, the diameters of the blades can be changed according to different incoming flows and flight states, so that the aircraft is in an optimal flight state.

Description

technical field [0001] The invention relates to the field of rotor design, in particular to a variable-diameter rotor device and a variable-pitch control method thereof. Background technique [0002] Since the advent of the tilt rotor aircraft in the last century, it has attracted widespread attention from the whole world. The tilt rotor aircraft not only has the vertical take-off and landing, hovering and other capabilities of a helicopter, but also has the high-speed cruise capability of a propeller aircraft. [0003] In order to meet the high maneuverability in the helicopter mode, the blade radius of the tiltrotor will inevitably be much larger than that of the general propeller aircraft, which also leads to greater air resistance in the aircraft propeller mode due to the large size of the blades. Thereby it directly leads to problems such as energy loss and voyage shortening. [0004] Traditional tiltrotors use general blades, and the diameter of the blades cannot be ...

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Problems solved by technology

[0003]In order to meet the high maneuverability in helicopter mode, the blade radius of the tilt rotor aircraft will inevitably be much larger than that of the general propeller aircraft, which also leads to large-scale The blades generate greater air resistance in the propeller mode of the aircraft, which directly leads to energy loss and shortened flight range.

[0004]Traditional tiltrotors use common blades, which cannot change the diameter of the blades according to different flight conditions, which makes the tiltrotor aircraft fly forward at high speed When taking off due to the large size of the blades, it brings a lot of drag, and when taking off vertically, the overload is small because it does not reach the length of the helicopter blades

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