Convective-radiative coupled heating chamber for aerodynamic hot ground simulation test

Abstract

The application provides a convection-radiation coupling heating test cabin for aerodynamic thermal ground simulation test, which comprises a test section front cabin and a test section rear cabin, the test section rear cabin is installed at the rear side of the test section front cabin, the test section rear cabin is installed on an externally connected vacuum cabin section, the test section front cabin is provided with a nozzle flange at the front end, the nozzle flange is used for installing a nozzle, a plurality of observation windows and radiation windows are uniformly and staggeredly arranged on the conical surface of the test section front cabin, and a plurality of support adapter flanges for installing supports and feeding devices of test models are arranged on the cylindrical wall surface of the test section rear cabin. The convection heating device and a plurality of radiation heating devices of multiple types are integrated, and the unexpected high-energy convection or radiation heating can be effectively resisted. A plurality of test model supports and feeding devices of multiple types can be simultaneously installed through the support adapter flanges, and the test model can be in a vacuum environment through the installation of the test section rear cabin on the externally connected vacuum cabin section.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aerospace thermal dynamic test devices, in particular to a convection-radiation coupling heating test cabin for aerodynamic heating ground simulation test. BACKGROUND

[0002] In the thermal protection design of a lunar exploration and interstellar return reentry vehicle, both convection heating and radiation heating need to be considered, and the proportion of the two heating methods varies with the speed and altitude of the vehicle. In the ground simulation test of thermal protection materials, both heating methods need to be tested and evaluated. In the thermal protection design of a vehicle, the main mechanism of convection heating is the convection heat exchange caused by the direct scouring of high-temperature airflow on the surface of the thermal protection material, and the main test method in the ground simulation test is an arc wind tunnel or a gas flow test device; the main mechanism of radiation heating is the radiation heating of the thermal protection material caused by the dissociation and ionization of high-temperature gas, and the main test method in the ground simulation test is a quartz lamp, a carbon lamp, and a xenon arc lamp.

[0003] When the vehicle is flying at a high speed, both convection heating and radiation heating act on the surface of the thermal protection material. Therefore, when the aerodynamic heating ground simulation test is performed, a convection-radiation coupling heating test technology needs to be used to combine the two types of heating methods. However, there is no test cabin that can integrate a convection heating device, multiple radiation heating devices, and multiple supports and feeding devices available for a test model into one. SUMMARY

[0004] The present application aims to provide a convection-radiation coupling heating test cabin for aerodynamic heating ground simulation test, which can integrate a convection heating device, multiple radiation heating devices, and multiple supports and feeding devices available for a test model into one.

[0005] According to one object of the present application, the present application provides a convection-radiation coupling heating test cabin for aerodynamic heating ground simulation test, which comprises a test section front cabin and a test section rear cabin, the test section rear cabin is installed on the rear side of the test section front cabin, the test section rear cabin is installed on an externally connected vacuum cabin section, the test section front cabin is provided with a nozzle flange at the front end, the nozzle flange is used to install a nozzle, a plurality of observation windows and radiation windows are uniformly and alternately arranged on the conical surface of the test section front cabin, and at least two support adapter flanges are arranged on the cylindrical wall surface of the test section rear cabin, and supports and feeding devices used for a test model are installed on the support adapter flanges.

[0006] Further, the test section front cabin has a conical structure, and the half-cone angle of the conical section is not greater than 50°; the test section rear cabin has a cylindrical shape, and the test section rear cabin is coaxial with the test section front cabin.

[0007] Further, the test section front cabin is provided with a convection end adapter, an observation window adapter, a radiation end adapter and a test section rear cabin adapter; the convection end adapter is located at the front end of the test section front cabin, and is used for connecting the nozzle flange; the observation window adapter is used for installing the observation window; the radiation end adapter is used for installing a radiation adapter flange, and the radiation adapter flange is used for installing the radiation window.

[0008] Further, the observation window adapters and the radiation end adapters are uniformly and staggeredly distributed on the conical surface of the test section front cabin.

[0009] Further, the inner planes of the observation window adapters and the radiation end adapters are tangent to the outer lateral wall surface of the test section front cabin.

[0010] Further, the intersection points of the normal lines of the observation window adapters and the radiation end adapters and the outer lateral wall surface of the test section front cabin are located on the same vertical plane.

[0011] Further, the number of the observation windows and the radiation adapter flanges is greater than or equal to 4.

[0012] Further, the radiation end adapter is a circle with a size not less than a diameter of Φ300mm, and the central normal line of the radiation end adapter is not located on a plane perpendicular to the ground; the radiation adapter flange is located at a distance of not less than 100mm from the observation glass at the radiation end adapter.

[0013] Further, the rear end of the test section front cabin is provided with a test section rear cabin adapter for installing the test section rear cabin, and the test section rear cabin adapter is perpendicular to the axis of the conical lateral wall of the test section front cabin and coaxial with the axis of the conical lateral wall of the test section front cabin.

[0014] Further, the test section rear cabin is provided with a test section front cabin adapter, a support adapter, a second water inlet, a second cooling water channel, a second water outlet and a vacuum section adapter; the test section front cabin adapter is located at the front end of the test section rear cabin, and is perpendicular to the axis of the lateral wall of the test section rear cabin and coaxial with the axis of the lateral wall of the test section rear cabin; the support adapter is at least two, and the central normal line of the support adapter is located on a plane perpendicular to the ground; the second cooling water channel is concentratedly distributed near the generatrix where the radiation end adapter is located, the second water inlet and the second water outlet are respectively connected to the two ends of the second cooling water channel, and the vacuum section adapter is located at the rear end of the test section rear cabin.

[0015] The technical scheme of the present application integrates a convection heating device and multiple radiation heating devices of multiple types, can effectively resist high-energy convection or radiation heating caused by accident, and can simultaneously install multiple test model supports and feeding devices of multiple types through the support adapter flange, and the test section rear cabin is installed on an externally connected vacuum cabin section to enable the test model to be in a vacuum environment. BRIEF DESCRIPTION OF DRAWINGS

[0016] In order to more clearly illustrate the technical scheme in the specific embodiments of the present application or the prior art, the drawings needed in the specific embodiments or the prior art description will be briefly introduced as follows. Obviously, the drawings in the following description are some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative labor.

[0017] Figure 1 The structure schematic diagram of the embodiment of the present application is shown in the figure.

[0018] Figure 2 The sectional structure schematic diagram of the embodiment of the present application is shown in the figure.

[0019] Figure 3 The structure schematic diagram of the test section front cabin of the embodiment of the present application is shown in the figure.

[0020] Figure 4 The sectional view of the test section front cabin of the embodiment of the present application is shown in the figure.

[0021] Figure 5 The structure schematic diagram of the test section rear cabin of the embodiment of the present application is shown in the figure.

[0022] Figure 6 The structure schematic diagram of the embodiment of the present application is shown in the figure. Figure 5 The local enlarged view of I in the embodiment of the present application is shown in the figure.

[0023] In the figure, 1 is a test section front cabin, 2 is an observation window, 3 is a nozzle flange, 4 is a radiation adapter flange, 5 is a test section rear cabin.

[0024] 51 is a test section front cabin interface, 52 is a support adapter interface, 53 is a second water inlet, 54 is a second cooling water channel, 55 is a second water outlet, and 56 is a vacuum section interface.

[0025] 6 is a support adapter flange, and 7 is a cabin section adapter flange.

[0026] 8 is a convection end adapter interface, 9 is an observation window adapter interface, 10 is a radiation end adapter interface, and 11 is a test section rear cabin interface. DETAILED DESCRIPTION

[0027] The technical solution of the present invention will be clearly and completely described below with reference to the embodiments. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0028] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," and "counterclockwise," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting this invention.

[0029] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the stated features. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified. Furthermore, the terms "installed," "connected," and "linked" should be interpreted broadly; for example, they may refer to a fixed connection, a detachable connection, or an integral connection; they may refer to a mechanical connection or an electrical connection; they may refer to a direct connection or an indirect connection through an intermediate medium; and they may refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0030] Example 1

[0031] like Figures 1-6 As shown,

[0032] A convection-radiation coupled heating test chamber for aerodynamic thermal ground simulation experiments includes a front test chamber 1 and a rear test chamber 5. The front test chamber 1 has a conical structure with a semi-cone angle of no more than 50°. The rear test chamber 5 is cylindrical with a diameter of no less than Φ1.2m and a length of no less than 1m. It is installed on the rear side of the front test chamber 1 via a flange and is coaxial with the front test chamber 1.

[0033] The front cabin 1 of the test section is equipped with a convection end adapter 8, an observation window adapter 9, a radiation end adapter 10, and a rear cabin interface 11.

[0034] The convection end adapter 8 is located at the front end of the test section front cabin 1, perpendicular to the axis of the conical side wall of the test section front cabin 1 and coaxial with it, for connecting the nozzle flange 3. The nozzle flange 3 is vertically installed at the front end of the test section front cabin 1 by bolts, and is coaxial with the test section front cabin 1. The nozzle flange 3 can be adapted to different interfaces according to different nozzles required by the test. The nozzle flange 3 is used to install the nozzle, and the coming flow generated by the nozzle of the heater is used to conduct convective heating on the model to generate a high-pressure high-enthalpy gas flow.

[0035] The observation window adapter 9 is used to install the observation window 2, which is used to observe the change process during the model test and can also record the test process, which can be used to reproduce the test phenomenon.

[0036] The radiation end adapter 10 is used to install the radiation adapter flange 4, which is installed with a radiation window for erecting a radiation xenon lamp. The xenon lamp radiation heater is used to conduct radiation heating test on the heat-resistant material.

[0037] The observation window adapter 9 and the radiation end adapter 10 are uniformly and staggered distributed on the conical surface of the test section front cabin 1; the inner plane of all observation window adapters 9 and radiation end adapters 10 is tangent to the outer side wall surface of the test section front cabin 1 along the line; the normal line of all observation window adapters 9 and radiation end adapters 10 intersects with the outer side wall surface of the test section front cabin 1 at the same vertical plane. In this embodiment, the observation window 2 and the radiation adapter flange 4 are uniformly distributed on the conical surface of the test section front cabin 1, and the number of the observation window 2 and the radiation adapter flange 4 is greater than or equal to 4. In this embodiment, the radiation end adapter 10 is a circle with a size not less than Φ300mm in diameter, and the central normal line of all radiation end adapters 10 is not located on the plane perpendicular to the ground. The radiation adapter flange 4 is spaced apart from the observation glass at the radiation end adapter 10 by not less than 100mm; the observation window adapter 9 and the radiation end adapter 10 are installed with special glass windows having the required transmission wave band and transmittance for the test.

[0038] The test section rear cabin adapter 11 is located at the rear end of the test section front cabin 1, perpendicular to the axis of the conical side wall of the test section front cabin 1 and coaxial with it, for installing the test section rear cabin 5.

[0039] The test section rear cabin 5 is provided with a test section front cabin adapter 51, a support adapter 52, a second water inlet 53, a second cooling water channel 54, a second water outlet 55 and a vacuum section adapter 56;

[0040] The test section front cabin adapter 51 is located at the front end of the test section rear cabin 5, perpendicular to the axis of the side wall of the test section rear cabin 5 and coaxial with it, and the interface form is matched with the vacuum section adapter 56; the support adapter 52 has at least two, the central normal line of which is located on the plane perpendicular to the ground, and one is below and one is above;

[0041] The second cooling water channel 54 is slightly concentrated and distributed near the busbar where the radiation end adapter 10 is located, and is connected as a whole, the second water inlet 53 and the second water outlet 55 are connected to two ends of the second cooling water channel 54 respectively, and the vacuum section adapter 56 is located at the rear end of the test section rear cabin 5 and is used for mounting the test cabin on the externally connected vacuum cabin section as a whole. Specifically, the cabin section adapter flange 7 is arranged on the vacuum section adapter 56 and is located on the rear end face of the test section rear cabin.

[0042] The cylindrical wall surface of the test section rear cabin 5 is provided with not less than two support adapter flanges 6, and the support and feeding device used for the test model is mounted on the support adapter flange 6.

[0043] The test section rear cabin 5 is cooled by cooling water, the cooling water enters from the rear adapter flange pipe nozzle of the test section rear cabin 5, is arranged in the outer layer U-shaped water channel, covers the surface of the cabin body, and flows out from the front flange pipe nozzle of the test section rear cabin 5.

[0044] The structural strength design of the device meets the use environment of static pressure 10 Pa, and fluorine rubber sealing elements are used for sealing between each component; the welding surface of all components processed and connected by welding cannot be on the inner wall surface.

[0045] When the device is used, the test cabin is mounted on the externally connected vacuum cabin section through the cabin section adapter flange 7. The support and feeding device used for the test model is mounted on the support adapter flange 6, the radiation heating device is mounted on the radiation adapter flange 4, the optical or other non-contact measurement and recording device is mounted on the observation window 2, the nozzle and other convection test devices are mounted on the nozzle flange 3, and finally the cooling water is connected to the test section front cabin 1 and the test section rear cabin 5.

[0046] The plurality of radiation windows can simultaneously erect a plurality of radiation heating devices; the radiation windows are arranged in four and are cross-distributed and uniformly distributed in the same section as the observation windows, which facilitates superposition of the heating effects of the plurality of radiation heating devices and facilitates unified observation.

[0047] The plurality of support adapter flanges 6 are arranged at different positions, different supports are erected for different test purposes to complete the test, including different model support systems such as rapid insertion, compensation feeding, and angle of attack mechanism support.

[0048] The plurality of observation windows can erect various observation equipment, and various non-contact measurement (single colorimeter, double colorimeter pyrometer, etc.) and observation detection equipment (high-temperature thermal imager, etc.) are often used in the test, and the plurality of observation windows can meet the requirements of various non-contact measurement observation to the greatest extent.

[0049] The sealing design among the components of the application is considered negative pressure, and the negative pressure is used to simulate the vacuum environment; the cabin section is water-cooled. The water-cooled design is used to reduce the damage of the harsh environment to the equipment. In the thermal environment simulation test, whether it is convective heating or radiation heating will produce a harsh high-temperature test environment, and water cooling can reduce the test of various harsh environments on the equipment as much as possible.

[0050] The application provides a test cabin which integrates a convective heating device, multiple radiation heating devices, multiple supports and feeding devices and the like, and is the basic equipment for the aerodynamic thermal ground simulation convective-radiation coupling test in the high-power convective heating, high-power and multi-frequency band radiation heating and multi-waveband observation mode.

[0051] The application can integrate a convective heating device and multiple radiation heating devices of multiple types simultaneously; can install multiple test model supports of multiple types simultaneously; can simultaneously perform multi-waveband observation measurement; can make the test model in a vacuum environment; and can effectively resist high-energy convective or radiation heating caused by accidents.

[0052] Finally, it should be noted that: the above embodiments are only used to illustrate the technical solutions of the application, and not to limit them; although the application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that: it can still modify the technical solutions recorded in the foregoing embodiments, or make equivalent replacement for part or all of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the scope of the technical solutions of the embodiments of the application.

Claims

1. Convective-radiative coupled heating test chamber for aerodynamic hot ground simulation tests, characterized by, The test section front cabin and the test section rear cabin are arranged, the test section rear cabin is arranged at the rear side of the test section front cabin, the test section rear cabin is arranged on the vacuum cabin section, the test section front cabin is provided with a nozzle flange at the front end, the nozzle flange is used for installing a nozzle, a plurality of observation windows and radiation windows are uniformly and staggered arranged on the conical surface of the test section front cabin, at least two support adapter flanges are arranged on the cylindrical wall surface of the test section rear cabin, and the support adapter flanges are used for installing the support and feeding device of the test model; the test section front cabin is provided with a convection end adapter, an observation window adapter, a radiation end adapter and a test section rear cabin adapter; the convection end adapter is located at the front end of the test section front cabin and is used for connecting the nozzle flange; the observation window adapter is used for installing the observation window; the radiation end adapter is used for installing a radiation adapter flange, and the radiation adapter flange is used for installing the radiation window; the rear end of the test section front cabin is provided with a test section rear cabin adapter used for installing the test section rear cabin, and the test section rear cabin adapter is perpendicular to the axis of the conical side wall of the test section front cabin and coaxial with the axis of the conical side wall of the test section front cabin; the test section rear cabin is provided with a test section front cabin adapter, a support adapter, a second water inlet, a second cooling water channel, a second water outlet and a vacuum section adapter; the test section front cabin adapter is located at the front end of the test section rear cabin and is perpendicular to the axis of the side wall of the test section rear cabin and coaxial with the axis of the side wall of the test section rear cabin; the support adapter has at least two, and the central normal line of the support adapter is located on a plane perpendicular to the ground; the second cooling water channel is concentratedly arranged near the generatrix where the radiation end adapter is located, the second water inlet and the second water outlet are respectively connected to the two ends of the second cooling water channel, and the vacuum section adapter is located at the rear end of the test section rear cabin.

2. The convective-radiative coupled heating chamber for aerodynamic hot ground simulation test according to claim 1, characterized in that, The test section front cabin is a conical structure, and the half-cone angle of the conical section is not greater than 50°; and the test section rear cabin is a cylindrical structure.

3. The convective-radiative coupled heating chamber for aerodynamic hot ground simulation testing of claim 1, wherein, The observation window adapter and the radiation end adapter are uniformly and staggered arranged on the conical surface of the test section front cabin.

4. The convective-radiative coupled heating chamber for aerothermal ground simulation tests according to claim 1, characterized in that, The inner plane of the observation window adapter and the radiation end adapter is tangent to the outer side wall surface of the test section front cabin along a line.

5. The convective-radiative coupled heating test chamber for aerodynamic heating ground simulation test of claim 1, wherein, The normal line of the observation window adapter and the radiation end adapter is located on the same vertical plane with the intersection point of the outer side wall surface of the test section front cabin.

6. The convective-radiative coupled heating test chamber for aerodynamic heating ground simulation test of claim 1, wherein, The number of the observation window adapter and the radiation end adapter is greater than or equal to 4.

7. The convective-radiative coupled heating test chamber for aerodynamic heating ground simulation test of claim 1, wherein, The radiation end adapter is a circle with a size not less than a diameter of Φ300mm, and the central normal line of the radiation end adapter is not located on a plane perpendicular to the ground; and the radiation adapter flange is located at a distance of not less than 100mm from the observation glass of the radiation end adapter.

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