Heat reflecting screen design method in hypersonic flight vehicle structure heat intensity test
A hypersonic and strength test technology, applied in design optimization/simulation, computer-aided design, calculation, etc., can solve problems such as inability to accurately simulate uniform extreme high-temperature environments, large radiant heat flow, and uneven temperature distribution on the surface of test pieces. Achieve the effect of improving the uniformity of the heat flow field, simple principle, and ensuring the uniformity and accuracy of the heat flow field
Active Publication Date: 2022-07-08
CHINA AIRPLANT STRENGTH RES INST
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Problems solved by technology
One of the cores of the heat intensity test is to accurately simulate the extremely high-temperature thermal environment caused by pneumatic heating in the ground environment. Therefore, radiation heating devices are generally used to simulate the extreme high-temperature thermal environment caused by pneumatic heating. However, the heat reflection screen in the radiation heating device Most of them are flat heat reflective screens, which will cause a large amount of radiant heat flow in the center of the hypersonic aircraft structure test piece, and gradually decrease to the surrounding direction, which will lead to uneven temperature distribution on the surface of the test piece, and will not be able to accurately simulate the structural heat flow of the hypersonic vehicle. Uniform extreme high temperature environment required for strength testing
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Embodiment Construction
[0048] like Figure 1 to Figure 3 As shown, the present invention comprises the following steps:
[0049] Step 1. Construction of the structural thermal strength test of the hypersonic vehicle:
[0050] Step 101 , build a hypersonic aircraft structure thermal strength test device in an aircraft laboratory; wherein, the hypersonic aircraft structure thermal strength test device includes a radiation heating device and a hypersonic aircraft structure test piece disposed below the radiation heating device , the structural test piece of the hypersonic aircraft is denoted as a rectangular body test piece (3), and the radiation heating device includes an array of radiation heating elements and a heat reflection screen (1);
[0051] Step 102: Set the radiation heating element array to include a plurality of parallel and uniform radiation heating elements (2), the radiation heating element (2) is cylindrical, and the plurality of radiation heating elements (2) are arranged according t...
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The invention discloses a heat reflecting screen design method in a hypersonic flight vehicle structure heat intensity test. The method comprises the following steps: 1, building a hypersonic flight vehicle structure heat intensity test; 2, establishing coordinates; 3, obtaining the total radiation heat flow of the rectangular body test piece; and 4, optimizing the parameter design of the heat reflecting screen. The method is reasonable in steps and design, design optimization of structural parameters of the heat reflecting screen in the hypersonic flight vehicle structure heat intensity test is achieved, the uniformity of a heat flow field on the surface of the hypersonic flight vehicle structure test piece is improved, so that the surface temperature field of the hypersonic flight vehicle structure test piece is uniform, and the performance of the hypersonic flight vehicle structure test piece is improved. Therefore, the accuracy of a subsequent hypersonic aircraft structure thermal strength test is improved.
Description
technical field [0001] The invention belongs to the technical field of structural thermal strength test of hypersonic aircraft, and in particular relates to a design method for a heat reflection screen in a structural thermal strength test of hypersonic aircraft. Background technique [0002] The thermal strength test of the hypersonic vehicle structure is a test to verify and evaluate the strength of the hypersonic vehicle structure in the simulated aerodynamic and thermal environment on the ground. When a hypersonic vehicle flies at a high speed in the atmosphere, the outer surface is subjected to severe aerodynamic heating, so that the structure of the hypersonic vehicle is placed in an extremely high temperature environment (ie, a high temperature environment of 1200°C to 1600°C). The influence of aerodynamic heating on the structure of hypersonic aircraft is mainly reflected in the following aspects: the strength limit and elastic modulus of the material are reduced in ...
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IPC IPC(8): G06F30/17G06F30/27G06F111/06G06F119/08
CPCG06F30/17G06F30/27G06F2119/08G06F2111/06Y02T90/00
Inventor 王彬文姚港秦强丛琳华
Owner CHINA AIRPLANT STRENGTH RES INST