A Structural Design Method for Axisymmetric Nozzles in Hypersonic Wind Tunnels
An axisymmetric nozzle, hypersonic technology, applied in design optimization/simulation, computer-aided design, testing of machine/structural components, etc., can solve the problem of high cost, long processing cycle, and difficulty in processing hypersonic wind tunnel nozzles Large and other problems, to achieve the effect of reducing weight, reducing processing difficulty, and good velocity field index performance
Active Publication Date: 2022-05-10
中国空气动力研究与发展中心超高速空气动力研究所
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Problems solved by technology
[0006] The hypersonic wind tunnel nozzle is difficult to process, the cost is high, and the processing cycle is long. Therefore, it is necessary to develop a structural design method for the axisymmetric nozzle of the hypersonic wind tunnel to ensure that the performance index of the nozzle velocity field can be realized. Provide a basis for the subsequent development of the nozzle manufacturing process, through a reasonable manufacturing process route and control strategy to meet the requirements of the nozzle structure design and manufacturing technology, and reduce the nozzle manufacturing cost through structural optimization design
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Embodiment 1
[0067] The structural design method for the axisymmetric nozzle of the hypersonic wind tunnel in this embodiment is based on the principle of aerodynamic design of the inner profile of the nozzle, reasonably divides the segmented position of the nozzle structure, and minimizes the segmentation of key parts.
[0068] Such as figure 1 As shown, the aerodynamic design of the nozzle is generally divided into three parts: the subsonic contraction section 1, the initial expansion section 2, and the parallel flow section 3. The location of the subsonic constriction section 1 is the OA section, that is, the nozzle inlet O to the nozzle throat A with the smallest diameter. In order to avoid separation, the airflow reaches the speed of sound at the outlet, and at the same time, the pulsation degree of the airflow is improved, so that the airflow at the throat A of the nozzle is uniform and stable. The position area of the initial expansion section 2 is the AB section, and its functi...
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The invention belongs to the technical field of hypersonic wind tunnel equipment design, and discloses a structural design method for an axisymmetric nozzle of a hypersonic wind tunnel. The structural design method includes the following steps: aerodynamic segmental design, structural segmental design, processing segmental design, mechanical analysis of each segment, material selection of each segment, machining accuracy, coaxiality, step difference, roughness and gap accuracy of each segment Indicators, the cooling method of each section and the nozzle are sealed with the test section. The structural design method is a structural design method that can ensure that the axisymmetric nozzle of the hypersonic wind tunnel meets the quality requirements of the velocity field of the hypersonic wind tunnel nozzle in the national military standard; it can reduce the risk of design and processing. This structural design method has been applied in the design of axisymmetric nozzles in hypersonic wind tunnels of Ф0.5m, Ф1m and Ф2m levels, and the obtained maximum Mach number deviations in the uniform velocity field of the nozzles are all less than 1 %, meeting the requirements of the national military standard.
Description
technical field [0001] The invention belongs to the technical field of hypersonic wind tunnel equipment design, and in particular relates to a structural design method for an axisymmetric nozzle of a hypersonic wind tunnel. Background technique [0002] The range of Mach number in hypersonic wind tunnel is generally Mach number 3 to Mach number 10. The hypersonic wind tunnel is a ground simulation test equipment for the development of hypersonic aircraft and aerodynamic research. The axisymmetric profile nozzle is a core component of the hypersonic wind tunnel and is an important component to ensure a certain Mach number and a certain uniformity of airflow. . After the incoming flow in the hypersonic wind tunnel is rectified and stabilized in the stable section, it enters the contraction section, and the airflow gradually accelerates from the subsonic speed to the sonic speed, and then starts from the throat, the airflow accelerates through expansion, and reaches a given Ma...
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IPC IPC(8): G06F30/17G06F30/23G06F30/28G16C60/00G16C10/00G01M9/04G06F113/08G06F113/14G06F119/14
Inventor 孙启志凌岗杨波陈映东朱涛许晓斌将万秋母波
Owner 中国空气动力研究与发展中心超高速空气动力研究所
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