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Tilting transition corridor wind tunnel experiment balancing method and system for tilt rotorcraft

A technology for tilting rotorcraft and wind tunnel experiments, which is applied in the field of wind tunnel experiment trimming for tilting transition corridors of tilting rotorcrafts. It can solve the distortion of the calculation results of the tilting transition flight corridor and the inability to accurately obtain the upper and lower boundaries of the tilting transition corridor , trail interference and other problems, to achieve the effect of improving the accuracy of trim results and experiment efficiency, improving the accuracy of trim results and experiment efficiency, and reducing the complexity of calculation

Active Publication Date: 2022-04-12
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

[0004] This method can effectively solve the problem of preliminary design of the tilting transition corridor of the tilting rotorcraft, but it has the following disadvantages: First, the effectiveness of this method depends heavily on the accuracy of the flight dynamics model, and the mathematical modeling error is large, which will lead to The calculation results of the tilt transition flight corridor are seriously distorted; second, the method must compromise between the accuracy and complexity of the modeling, and it is difficult to establish accurate blade flapping, rotor inflow, wake interference, aeroelasticity, and high angle of attack Dynamic and other mathematical models
Therefore, the existing technology cannot accurately obtain the upper and lower boundaries of the tilted transition corridor. Therefore, it is necessary to find a better method to obtain the corridor boundary, so that it has better engineering application value

Method used

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  • Tilting transition corridor wind tunnel experiment balancing method and system for tilt rotorcraft
  • Tilting transition corridor wind tunnel experiment balancing method and system for tilt rotorcraft
  • Tilting transition corridor wind tunnel experiment balancing method and system for tilt rotorcraft

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Experimental program
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Effect test

Embodiment 1

[0083] A method for trimming a tilting rotorcraft tilting transition corridor wind tunnel experiment, such as figure 1 described, including the following steps:

[0084] S1. Start and initialize the trimming equipment;

[0085] The trim method of the present invention adopts wind tunnel experiments, and performs trim calculation under the parameters measured in experiments. Compared with the numerical trim method based on the mathematical model of flight dynamics in the prior art, it has the following advantages: it can be more realistically performed in the wind tunnel. By simulating complex aerodynamic / kinematic coupling characteristics such as blade flapping, rotor inflow, and wake interference, the obtained trim results of the tilt transition corridor are closer to the true value. Therefore, start and initialize the trim device first.

[0086] S2. Select balance subjects;

[0087] The trimming subject includes the upper boundary of the tilting corridor and the lower bo...

Embodiment 2

[0135] This embodiment provides a system for performing the trimming method of the wind tunnel experiment on the tilting transition corridor of the tilting rotorcraft as in Embodiment 1, such as Figure 5 As shown, it includes a support device 1, a tilt rotor aircraft model 2, a main balance 3, a plurality of small balances 4, a data acquisition subsystem 8, a drive control system 8, a trim calculation system 9,

[0136] The supporting device 1 supports the tilt rotor model 2, and controls the angle of attack and the sideslip angle of the tilt rotor model 2;

[0137] The main balance 3 is connected between the support device 1 and the tilt rotor model 2, and is used to measure the load of the whole machine;

[0138] The small balance 4 is arranged inside the tilt mechanism or the rotor 5 of the tilt rotor model 2, and is used for measuring rotor load and rotor tilt angle.

[0139] The data acquisition system 8 gathers the data measured by the main balance 3 and a plurality of...

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Abstract

The invention is suitable for the technical field of wind tunnel driving force measurement, and provides a balancing method and system for a tilting transition corridor wind tunnel experiment of a tilting rotorcraft. Mechanical parameters under complex pneumatic / motion coupling conditions such as blade waving, rotor wing inflow and wake flow interference are actually measured, the balancing method is designed in combination, and a tilting transition corridor balancing result closer to a real value is obtained.

Description

technical field [0001] The invention relates to the technical field of wind tunnel driven force measurement, in particular to a method and system for trimming a tilting rotorcraft tilt transition corridor wind tunnel experiment. Background technique [0002] The tilting transition of a tiltrotor is a flight process with variable configuration and variable speed, which requires a reasonable matching of rotor and wing aerodynamic forces at different forward flight speeds to complete successfully. However, too low forward flight speed will cause the wing stall of the tiltrotor, and too high forward flight speed will be limited by factors such as rotor forward blade compressibility, backward blade stall and rotor available power. In order to ensure flight safety, the tilt transition process of the tiltrotor needs to be kept within the "nacelle tilt angle-velocity" envelope, that is, within the tilt transition velocity corridor. [0003] In the prior art, the patent 201810750002...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M9/08G01M9/04B64F5/60
Inventor 聂博文武杰郭天豪彭先敏张卫国何龙刘志涛蒋永张磊靳秋硕任忠才
Owner LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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