Separated half-mode injection type nacelle dynamic influence test method

A test method and ejector technology, applied in the field of wind tunnel test, can solve the problems of high risk of result error, complicated model position change, and high cost, so as to reduce application difficulty, optimize model selection test ability, and eliminate influence. Effect

Inactive Publication Date: 2020-03-24
LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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Problems solved by technology

In the application process of the above test scheme, there are disadvantages of high cost, complicated test process, and high

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  • Separated half-mode injection type nacelle dynamic influence test method
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[0028] All features disclosed in this specification, or steps in all methods or processes disclosed, may be combined in any manner, except for mutually exclusive features and / or steps.

[0029] Such as figure 1 As shown, the half-model of the aircraft is fixed on the turntable of the wind tunnel wall, and the ejector nacelle is separated from the wing of the model. In order to achieve this goal, it is considered that the ejector nacelle must be fixed to the corresponding position with a supporting structure, and in the traditional test, the test of the ejector nacelle needs to be separately designed with a high-pressure air pipe device for gas supply. Therefore, the present invention separates the high-pressure air pipe, and replaces the supporting effect of the ejection type nacelle with the high-pressure air pipe. Therefore, a ventilation strut is designed, and the ventilation strut communicates with the ejection nacelle, and the ventilating strut provides a high-pressure ...

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Abstract

The invention discloses a separated half-mold injection type nacelle power influence test method. A semi-model of an aircraft is arranged on a tunnel wall turntable of a wind tunnel, an injection typenacelle is arranged at a nacelle hanger of a semi-model wing, the injection type nacelle is not in contact with the semi-model wing, and a gap between the injection type nacelle and the nacelle hanger is filled with a soft material; the injection type nacelle is arranged on the tunnel wall turntable through a support, the semi-model and the injection type nacelle are driven to rotate synchronously under rotation of the tunnel wall turntable, and the interference acting force of intake and exhaust of the injection type nacelle on an airplane is obtained. According to the scheme, the injectiontype nacelle and the air supply system thereof are separated and independent from the model; the injection type nacelle does not make contact with the model to transmit force, static thrust measurement of the injection type nacelle does not need to be conducted, the injection type nacelle and the semi-model are supported on the wind tunnel test section turntable together through the special movable supporting device, synchronous movement of the nacelle and the semi-model is achieved, and a complex movement and control mechanism does not need to be designed for the nacelle.

Description

technical field [0001] The invention relates to the field of wind tunnel tests, in particular to a method for testing the dynamic influence of a separated half-model injection type nacelle. Background technique [0002] The ejector nacelle is an aero-engine power simulation device used in wind tunnel tests. Through the ejection of high-pressure gas introduced into the nacelle, the intake and exhaust of the engine can be simulated. When an aircraft model equipped with an ejector nacelle is subjected to a wind tunnel test, the influence of the intake and exhaust of the engine on the aerodynamic characteristics of the whole aircraft can be obtained. [0003] When carrying out the dynamic impact test of the half-model ejection nacelle, the usual test plan is to install the ejection nacelle directly on the wing, the high-pressure air supply line enters the model along the support rod of the model, and arranges it inside the model. It is introduced into the ejector nacelle throug...

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Application Information

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IPC IPC(8): G01M9/06
CPCG01M9/06
Inventor 王勋年许可章荣平
Owner LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
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