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A method for testing and simulating the aerodynamic interference characteristics of multiple components of a full-motion horizontal tail helicopter

A technology of interference characteristics and helicopters, which is applied in the field of wind tunnel tests, can solve the problems of sudden increase of fuselage pitching moment, sudden change of lift coefficient, reduction of helicopter control stability and safety, etc., so as to ensure the authenticity and effectiveness of the test and reduce the test process Effect

Active Publication Date: 2022-02-11
LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Especially for a full-motion horizontal tail with a large area, when it is hovering and flying forward at a low speed, it is greatly affected by the rotor wake, and the lift coefficient changes suddenly, resulting in a sudden increase in the pitching moment of the fuselage, which seriously reduces the control of the helicopter. Stability and Security

Method used

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  • A method for testing and simulating the aerodynamic interference characteristics of multiple components of a full-motion horizontal tail helicopter
  • A method for testing and simulating the aerodynamic interference characteristics of multiple components of a full-motion horizontal tail helicopter
  • A method for testing and simulating the aerodynamic interference characteristics of multiple components of a full-motion horizontal tail helicopter

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Embodiment 1

[0049] This embodiment provides a method for testing and simulating the aerodynamic interference characteristics of multiple components of a full-motion horizontal tail helicopter, based on a combined rotor and fuselage model wind tunnel test rig, the measurement system of the combined rotor and fuselage model wind tunnel test rig includes a rotor balance 3. Torque balance 4, fuselage balance 6, and horizontal tail balance 8. The test content includes a single rotor model test, a separate fuselage model test and a combined rotor and fuselage model test, such as figure 1 As shown, it specifically includes the following steps:

[0050] Step 1. Carry out a hovering test of a single rotor model based on the combined rotor and fuselage model wind tunnel test rig, and obtain the rotor aerodynamic load R1 during hovering;

[0051] Step 2, carry out the hovering test of the combined rotor and fuselage model based on the wind tunnel test bench of the combined rotor and fuselage model, ...

Embodiment 2

[0070] Such as figure 2 As shown, this embodiment carries out the forward flight test of the combined rotor and fuselage model based on the wind tunnel test bench of the rotor and fuselage model, so as to obtain the rotor aerodynamic load R4 during forward flight, the fuselage aerodynamic load F3 during forward flight, and the forward flight time Full motion horizontal tail aerodynamic load H3.

[0071] Before the test starts, first judge whether the wind tunnel test bed of the combined rotor and fuselage model can work normally. If the system can work normally, change the installation angle of the full-motion horizontal tail to the test value, collect zero readings and save them, and start the rotor. Combined with the fuselage model wind tunnel test bench, when the collective pitch angle and the periodic pitch angle are zero, the rotor speed is raised to the working speed for safe operation, and the wind tunnel is started;

[0072] (1) Adjust the wind speed to a given test ...

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Abstract

The invention discloses a multi-component aerodynamic interference characteristic test simulation method of a full-motion horizontal tail helicopter. The rotor aerodynamic load test data of the helicopter under the coaxial system is obtained based on the wind tunnel test bench test of the combined rotor and fuselage model, and the coaxial rotor and the helicopter are coaxial. The airframe aerodynamic load test data and the full-motion horizontal tail aerodynamic load test data under the system; according to the rotor aerodynamic load test data, the fuselage aerodynamic load test data and the full-motion horizontal tail aerodynamic load test data, the interference characteristic model is used to analyze the helicopter components. The aerodynamic interference characteristics among them; the aerodynamic interference law between the rotor, fuselage and full-motion horizontal tail can be accurately obtained, which provides an important basis for the design of the helicopter's aerodynamic components, layout optimization and flight control law design.

Description

technical field [0001] The invention relates to the technical field of wind tunnel tests, in particular to a test simulation method for the aerodynamic interference characteristics of multiple components of a full-motion horizontal tail helicopter. Background technique [0002] Due to the complexity of the aerodynamic layout of the helicopter, there are multiple aerodynamic components including the rotor, the fuselage and the vertical tail. When the helicopter is hovering, climbing, flying forward, and descending, due to changes in flight attitude and speed, various aerodynamic components have different degrees of aerodynamic interference, which will have a great impact on the flight performance, flight characteristics and flight quality of the helicopter. . Among them, as one of the important parts to adjust the helicopter's flight attitude, the horizontal tail has an important influence on the aerodynamic characteristics and control stability of the helicopter. Especiall...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M9/02G01M9/04G01M9/08B64F5/00B64F5/60
CPCG01M9/02G01M9/04G01M9/08B64F5/00B64F5/60
Inventor 黄明其徐栋霞王畅彭先敏何龙杨仕鹏
Owner LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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