Low-speed wind channel virtual flying test aircraft model designing method

A technology for flight test and aircraft model, which is applied in computing, special data processing applications, instruments, etc., and can solve problems such as inability to meet requirements, complex test model design process, and small geometric reduction.

Active Publication Date: 2017-10-13
中国航空工业集团公司哈尔滨空气动力研究所
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Problems solved by technology

The wind tunnel virtual flight test also requires the use of a scaled model, especially for airplanes, whose geometric scale is relatively small. In addition to the unsteady aerodynamic force during the test, in order to achieve the attitude control of the model, it is also necessary to consider the The control computer, attitude measurement system, steering gear control system, etc. are installed in appropriate positions inside the scaled model. The design process of the test model is very complicated, and after the model is scaled down, the overall structure must meet the requirements of light weight and high strength.
At this time, the use of metal materials can no longer meet the requirements.

Method used

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  • Low-speed wind channel virtual flying test aircraft model designing method

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Embodiment Construction

[0027] The following specific implementation examples are listed in conjunction with the accompanying drawings to further illustrate the technical solution of the present invention.

[0028] A low-speed wind tunnel virtual flight test aircraft model design method, including the following content, such as figure 1 as shown,

[0029] The selection of model size, according to the size of the wind tunnel test section, the maximum extension of the virtual flight test model should not exceed 70% of the width of the test section, determine the reduction ratio, and obtain a dynamic similar model;

[0030] According to the shape layout characteristics of the model and the installation of the internal equipment of the model, the overall structure of the model is analyzed, and the spatial structure and installation method of each component inside the model are coordinated. The overall structure of the model is divided into a model main body, a rudder surface control component, a counter...

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Abstract

The invention relates to a low-speed wind channel virtual flying test aircraft model designing method and belongs to the field of wind channel virtual flying test model designing. By the method, a control plane driving mode is optimized, and a model operation plane can be changed a control plane automatically to realize a model pneumatic / movement / control coupling function. Weight and inertial load of a model are reduced, balancing of center of mass of the model is realized in the aspect of structural design, and aircraft model reference center, model actual center of mass and virtual flying supporting mechanism rotating center are ensured to be coincident at the same time. The method meets requirements of processing techniques and test equipment, processing accuracy of the model meets requirements on virtual flying wind channel test data measuring accuracy, and the model is stable in running when being applied in virtual flying wind channel tests and convenient to mount and demount.

Description

technical field [0001] The invention relates to a design method of a low-speed wind tunnel virtual flight test aircraft model. Background technique [0002] Wind tunnel tests usually provide aerodynamic parameters for aircraft design and control system design. However, with the continuous improvement of the maneuvering characteristics of the aircraft, higher requirements are put forward for the performance of the aircraft. At present, there is no good description and prediction of the overload, stability and control force required for the maneuvering of the aircraft at high angles of attack. ground test method. For this problem, an advanced wind tunnel dynamic test technology, that is, wind tunnel virtual flight test technology, has been developed in recent years. This technology makes it possible to realize the flight dynamics characteristics of the aircraft, the flight control system, and the comprehensive verification of the navigation system in the wind tunnel by simul...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/15
Inventor 黄丹刘淑丽卜忱吴佳莉刘传辉
Owner 中国航空工业集团公司哈尔滨空气动力研究所
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