Retractable rotor for aircraft vertical take-off and landing

Abstract

The invention provides a retractable rotor for aircraft vertical take-off and landing and belongs to the technical field of aircrafts. The retractable rotor comprises a main shaft, blade support frames, a plurality of blades and blade hinges; the main shaft is vertically intersected with and fixedly connected with the geometric center of the blade support frames, and the main shaft and the blade support frames synchronously rotate; the blade hinges are parallel to the main shaft and vertical to blade airfoils, the blades are connected with the blade support frames through the blade hinges, and the blades freely rotate around the blade hinges under the influence of centrifugal force and aerodynamic force and have different working conditions; when the blades are completely unfolded, the main shaft, the blade support frames and the blade hinges synchronously rotate around the main shaft. When the blades are folded, the blades overlap and piece a rectangle or other proper shapes; the blade support frames according to different ways are matched with the blades in a certain shape and number. The rotor aerodynamic shape can be automatically changed according to the demands of flying working conditions, and therefore resistance is reduced, lift force is increased, stationary shift and effective compatibility of working modes of vertical take-off and landing are horizontal flying are achieved, and the retractable rotor for aircraft vertical take-off and landing has the advantages of being coordinative in mechanism, simple in structure, low in cost, high in reliability, good in adaptability and the like.

Description

technical field [0001] The invention relates to a retractable rotor used for vertical take-off and landing of an aircraft, in particular to a retractable rotor that is opened during vertical take-off and landing and retracted during horizontal flight, and belongs to the technical field of aircraft. Background technique [0002] Manned aircraft can be divided into two categories: fixed wing and rotary wing. Fixed wing is commonly used in horizontal take-off and landing aircraft (such as jet airliners), while rotary wing is commonly used in vertical take-off and landing aircraft (such as helicopters). As far as the technical level has been reached so far, fixed-wing aircraft can fly at high speed and are easy to operate, but they need to rely on runways to take off and land. Rotary wing aircraft can take off and land vertically without relying on runways, and has strong adaptability, but the mechanism is out of balance, the control is complicated, the flight speed is slow, and...

AI Technical Summary

Problems solved by technology

(2) Low reliability

The waving of the rotor blades produces mechanical vibrations, which increases the wear of the hinges and makes the reliability always inferior to that of fixed-wing aircraft

(3) Poor roll stability

Uneven lift on both sides of the rotor can cause the rotary wing aircraft to roll, capsizing and losing control within seconds

(4) Complex manipulation

The rotor of the helicopter not only provides the maneuverability of flight, but also causes the complexity of flight control

The control load is much greater than that of fixed-wing aircraft, which increases the probability of human error

(5) Can't be bigger

The diameter and speed of the rotor are limited by the speed of the tip of the wing that cannot exceed the speed of sound. The diameter of the rotor is generally a maximum of more than ten meters. The size of the aircraft is limited and it cannot be made larger

(6) Flight mechanism disorder

Although the helicopter has been developed for nearly 70 years, the inherent coordination of the flight mechanism is poor and full of innate contradictions

For example: use the tail rotor to balance the rotor torque, use the flapping hinge and the shimmy hinge to balance the turning moment of the forward flight, the rotor area is required to be large for vertical take-off and landing, and the rotor area is expected to be small for horizontal flight, the flight mechanism of the vertical take-off and landing state and the horizontal flight state Contradictions, inability to unify, etc., directly lead to complex control of flight status and poor stability

[0004] In short, the above-mentioned defects of rotary-wing aircraft come from the contradiction between the two flight modes that the rotor needs to take into account both vertical take-off and landing and horizontal flight.

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