Composite conventional rotor high-speed helicopter combined model wind tunnel test device and method

A combined model and wind tunnel test technology, applied in the field of aviation aircraft, can solve the problem that it is difficult to find relevant information on wind tunnel test devices and methods

Active Publication Date: 2022-02-11
LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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  • Abstract
  • Description
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Problems solved by technology

[0003] Wind tunnel test is one of the important means of helicopter aerodynamic characteristics research. The existing test devices for helicopter wind tunnel test are basically aimed at conventional single rotor with tail rotor and coaxial configuration (refer to CN110261057A, CN208109379U, CN106226024B) , but it is difficult to find relevant information about the composite conventional rotor high-speed helicopter rotor / fuselage / propeller combined model wind tunnel test device and method in the open literature

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  • Composite conventional rotor high-speed helicopter combined model wind tunnel test device and method
  • Composite conventional rotor high-speed helicopter combined model wind tunnel test device and method

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Embodiment Construction

[0039] Embodiments of the present invention are described in detail below, examples of which are shown in the drawings, wherein the same or similar reference numerals designate the same or similar elements or elements having the same or similar functions throughout. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention.

[0040] Such as figure 1As shown, the compound conventional rotor high-speed helicopter combination model wind tunnel test device of the present embodiment includes a main test stand 1 installed in the pit and the axis passes through the center of the pit, and the other end of the main test stand 1 is connected with a fuselage 2 And rotor 3, wing 4 and landing gear 21 are installed on the fuselage 2, rotor balance and fuselage balance are installed in the fuselage 2 interior of hollow, the torque balance that is connected to the r...

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Abstract

The invention belongs to the technical field of aviation aircraft, and in particular relates to a combined model wind tunnel test device and method for a composite conventional rotor high-speed helicopter. The invention comprises a main test stand, the other end of the main test stand is connected with a fuselage and a rotor, the fuselage is equipped with wings, the inside of the fuselage is equipped with a rotor balance and a fuselage balance, the lower end of the rotor shaft is connected with a rotor balance, and the rotor balance A torque balance is set between the upper and lower plates of the fuselage. The tail of the fuselage is equipped with a horizontal tail and a vertical tail. The vertical tails on both sides are equipped with rudders. The end of the support mechanism away from the pit is connected with a propeller nacelle, a propeller is installed inside the propeller nacelle, and a propeller balance is installed inside the propeller nacelle. The invention provides a combined model wind tunnel test device and method for a composite conventional rotor high-speed helicopter with a single rotor, wings, propulsion propellers on both sides, and a vertical tail configuration.

Description

technical field [0001] The invention belongs to the technical field of aviation aircraft, and in particular relates to a combined model wind tunnel test device and method for a composite conventional rotor high-speed helicopter. Background technique [0002] Due to the limitation of its own configuration, the existing single-rotor helicopter with tail rotor cannot further increase the maximum flight speed. High-speed helicopters are a major trend in the development of next-generation helicopters. The composite conventional rotor high-speed helicopter can reduce the forward tilt angle of the rotor disc during forward flight by means of propeller propulsion and lower rotor speed, and weaken the shock wave resistance on the forward side of the propeller disc and the separation of the airflow on the rearward side, effectively improving The maximum flight speed of the helicopter. The European X3 compound high-speed helicopter reached a maximum flight speed of more than 470km / h d...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64F5/60
CPCB64F5/60
Inventor 王亮权吴松岭黄明其杨仕鹏何龙赵宇杨永东彭先敏徐栋霞聂博文尹欣繁
Owner LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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