A high temperature gas wind tunnel Mach number measurement device and method
A gas-fired wind tunnel and measurement device technology, which is applied in the field of wind tunnel test and flow field test, can solve the problems of complex calculation formula, high design cost, and low measurement accuracy, so as to achieve easy repeated disassembly and assembly, reduce design difficulty, and avoid influence Effect
Active Publication Date: 2020-02-14
BEIJING AEROSPACE INST OF THE LONG MARCH VEHICLE +1
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[0003] The technical problem solved by the present invention is to provide a high-temperature gas-fired wind tunnel Mach number measuring device to solve the problems of high design cost, complex calculation formula and low measurement accuracy of the above-mentioned existing Mach number measuring device
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[0032] The present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.
[0033] The invention relates to a high-temperature gas wind tunnel Mach number measurement device and method. The measurement device includes a measurement mechanism, a support mechanism and a water supply mechanism. The measurement mechanism includes a water-cooled measurement model and a camera assembly. By taking images of the flow around the water-cooled measurement model, the shock angle at the head of the model is obtained, and the Mach number data of the wind tunnel is calculated. Among them, the water-cooled measurement model is in the shape of a sharp wedge, which is composed of an outer wall and an inner core. The outer wedge wall is a thin-walled shell to withstand the external airflow load. The inner core is equipped with a water-cooling channel to cool the model head and wedge surface and protect The measurement model is ...
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The invention relates to a high-temperature gas wind tunnel Mach number measuring device and method. The measuring device includes a measuring mechanism, a supporting mechanism and a water supply mechanism. The measuring mechanism includes a water-cooling measuring model and a camera assembly. By capturing a detour flow image of the water-cooling measuring model, a head shock angle of the model isobtained, and wind tunnel Mach number data are calculated. The water-cooling measuring model has a sharp wedge profile and consists of an outer wall and an inner core. The outer wedge wall is a thin-walled shell that is used to withstand the external airflow load. The inner core is provided with a water-cooling channel to cool the model head and the wedge surface to protect the measuring model from being damaged during measurement. The water supply mechanism provides high-pressure cooling water for the model. The supporting mechanism is internally designed with a water supply channel, and hasthe functions of supporting and water supply. According to the invention, the high-temperature thermal protection of the measuring model under a gas wind tunnel and the stable measurement of the headshock angle of the model are realized through the measuring model design and the water supply flow control, and the Mach number measurement accuracy of the high-temperature gas wind tunnel is increased.
Description
technical field [0001] The invention relates to a Mach number measuring device and method in a high-temperature gas wind tunnel, and belongs to the technical fields of wind tunnel test and flow field test. Background technique [0002] The high-temperature wind tunnel is an important equipment for the ground heat insulation test and assessment of aircraft. In order to ensure the accuracy of the ground and test assessment, it is necessary to master the flow field parameters in the test area, and the Mach number is one of the key parameters of the wind tunnel flow field. Existing Mach number measurements mostly obtain the Mach number indirectly by measuring the total pressure or static pressure of the flow field. However, for high-temperature wind tunnels, since the total temperature of the test environment can exceed 3000 degrees, the total pressure and static pressure measurement devices face the problems of high design costs and complex calculation formulas, making it diffi...
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IPC IPC(8): G01M9/06
CPCG01M9/06
Inventor 赵玲曹宇清张昕邹样辉田宁张凯曹知红姜一通岳晖张利嵩那伟杨驰夏吝时肖泽娟李文浩李红亮宋文潇徐秀明鲁宇朱广生李建林孟刚周岩水涌涛张喦陈卫国
Owner BEIJING AEROSPACE INST OF THE LONG MARCH VEHICLE