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Two-blade propeller applicable to tilt-rotor aircraft

A technology of tilting rotors and propellers, which is used in the testing of propellers, aircraft parts, and aircraft components. It can solve the problems of lack of system-level test verification and large gaps, and achieve good aerodynamic performance, high reliability and high aerodynamic efficiency. Effect

Pending Publication Date: 2018-08-21
CAIHONG DRONE TECH CO LTD
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, most of the research work done is still theoretical research, lacking system-level experimental verification, and there is still a big gap between the actual application of engineering and the advanced level of foreign countries.

Method used

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  • Two-blade propeller applicable to tilt-rotor aircraft
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  • Two-blade propeller applicable to tilt-rotor aircraft

Examples

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Embodiment

[0044] Through the above implementation measures, a pair of two-bladed propellers is obtained, which meets the design objectives. The geometric parameters of the blade are shown in Table 2:

[0045] Table 2 Chord length and twist angle distribution of blade airfoil

[0046] (r is the spanwise position of the local airfoil, R is the blade radius of 1.6m, Cr is the chord length of the local airfoil, Beta is the twist angle of the local airfoil)

[0047]

[0048] CFD numerical simulation calculation data results display (see Figure 4 , Figure 5 ), the propeller is in the helicopter state (see Figure 4 ), the hovering efficiency of the blade reaches 75%, the power-to-weight ratio reaches 6.8, and the hovering lift meets the design requirements; the propeller is in the state of a fixed-wing aircraft (see Figure 5 ), the cruise efficiency of the blade reaches 72%, and the cruise pull meets the design requirements. At present, the propeller has been processed into a real ...

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Abstract

The invention discloses a two-blade propeller applicable to a tilt-rotor aircraft. The two-blade propeller is different from a common propeller and has two main characteristics, that is, the two-bladepropeller can be used as a helicopter rotor for achieving a vertical take-off and landing function, and can be also used as a thrusting propeller to enable an aircraft to fly forwards at a high speed. The propeller comprises propeller blades and a propeller hub. The propeller is characterized in that the two propeller blades are connected through the propeller hub to form an overall structure; the airfoil profile of the propeller blades is adjusted on the basis of a basic airfoil profile; the basic airfoil profile is a laminar flow airfoil profile; at 0.2R of a propeller blade, the relative thickness of the airfoil profile is adjusted to 20-25%, the chord length of the airfoil profile is adjusted to 280-310mm, and the torsional angle of the airfoil profile is adjusted to minus 2 degree to1 degree; at 1.0R of one propeller blade, the relative thickness of the airfoil profile is adjusted to 8-10%, the chord length of the airfoil profile is adjusted to 120-160mm, and the torsional angleof the airfoil profile is adjusted to minus 10 degree to minus 6 degree; R is the radius of one propeller blade.

Description

technical field [0001] The invention relates to an air propeller, which can be used as the flight power of a tilt-rotor aircraft. The technology adopted involves the fields of rotor aerodynamics, experimental aerodynamics and the like. Background technique [0002] The tilt rotor aircraft realizes high-speed flight by switching the rotor function, that is, uses the tilt mechanism to realize the conversion of its main aerodynamic components between the rotor and the propeller, and realizes flying in helicopter mode when flying vertically, and flying forward in fixed-wing propeller aircraft mode at high speed , so as to take into account both low-speed and high-speed flight performance. The tilt-rotor aircraft takes into account the characteristics of both helicopters and fixed-wing propeller aircraft, and has the advantages of low vibration, low noise, and good economy. [0003] The concept of the tilting rotor aircraft was proposed by Bell Corporation in the early 1940s. Si...

Claims

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Application Information

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IPC IPC(8): B64C11/20B64C11/18B64C11/32B64F5/60
CPCB64C11/18B64C11/20B64C11/32B64F5/60
Inventor 付义伟孙凯军叶川张练
Owner CAIHONG DRONE TECH CO LTD
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