A four-blade rotary wing and rotary wing aircraft and control method

Abstract

The invention proposes a four-blade rotary wing, a rotary wing aircraft and a control method. Aiming at the requirement of improving the loading capacity and the maximum take-off weight of the rotary wing aircraft, the present invention creatively proposes a four-blade rotary wing and applies it to the rotary wing aircraft. A pair of main rotors in the four-blade rotary wing The blades are designed taking into account the requirements of the fixed-wing mode and the helicopter mode, while a pair of auxiliary blades are designed completely in accordance with the requirements of the helicopter mode, which not only improves the maximum pulling force of the rotating wing as a whole, but also reduces the power consumption of the main and auxiliary blades. Significantly increased, but also meet the flight requirements of fixed-wing mode.

Description

technical field [0001] The invention relates to a four-blade rotary wing, a rotary wing aircraft and a control method, which are suitable for heavy-duty rotary wing aircraft. Background technique [0002] Rotary wing aircraft is a new type of manned / unmanned aircraft that has both the vertical take-off and landing performance of a helicopter and the high-speed cruise performance of a fixed-wing aircraft. The patent number is ZL201110213680.1, and the Chinese patent titled "A Rotary Wing Aircraft with Variable Flight Mode" is a typical model. A rotary wing aircraft has an aerodynamic layout of three wings. Among them, the rotating wing, that is, the main wing, can be used as a rotor in the helicopter flight mode to provide the aircraft with the pulling force required for vertical take-off and landing through rotation. At the same time, when the aircraft has a certain flying speed, it can be locked as a fixed wing. Realize high-speed and high-efficiency flight of fixed-wing....

AI Technical Summary

Problems solved by technology

[0006] If the chord length of the blade is increased while maintaining the radius of the blade and the rotational speed of the rotating wing, it will lead to a substantial increase in the weight of the rotating wing structure, but the gain to the total pulling force is very limited

[0007] If the rotational speed of the rotating wing is increased while the blade chord length and blade radius are kept constant, the speed of the blade tip will increase accordingly. Due to the characteristics of the elliptical airfoil itself, a strong air force will appear on the upper surface of the blade tip. Compression effect, leading to a sharp increase in its power consumption

[0008] If the radius of the rotating wing is increased while maintaining the length of the blade chord and the rotational speed of the rotating wing, due to the characteristics of the rotating wing aircraft, the longitudinal distance of the aircraft will increase, which will have an adverse effect on the structural design. The speed of the tip of the blade will increase accordingly, resulting in an increase in the power consumption of the rotating wing

[0009] Through a certain combination of the above three parameters, the purpose of increasing the carrying capacity and maximum take-off weight can be achieved. However, according to the current analysis results, the beneficial effect produced by this method is very limited, and it cannot maximize and efficiently Increase the load capacity and maximum take-off weight of rotary wing aircraft, while having a serious adverse effect on the structural design of the aircraft

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