Direct radiation type radiation convection coupling aerodynamic heat ground simulation test device

Abstract

The invention relates to a direct radiation and convection coupling aerodynamic heat ground simulation test device which comprises a convection heat source, a four-way mixing chamber, a radiation heat source, an ellipsoid reflector, a water cooling spray pipe, a test model and a model feeding base. The two convection heat sources are in butt joint with the two ends of a transverse through cavity of an airflow cavity of the four-way mixing chamber through bolts, the tail of the radiation heat source is connected to a radiation source mounting hole of the four-way mixing chamber through threads, and the back face of the ellipsoid reflector is coated with high-heat-conduction silicone grease and then attached to the interior of a radiation cavity of the four-way mixing chamber. A radiation cavity of the four-way mixing chamber and an airflow cavity are pressed and fixed, a water-cooling spray pipe is connected to the small end of a longitudinal through cavity of the airflow cavity of the four-way mixing chamber through a bolt, a test model is installed on a model feeding base, and a model stagnation point is spaced from an outlet of the water-cooling spray pipe by a certain distance and located at the far focus of the ellipsoid reflector. The device is mainly used for the radiation convection coupling aerodynamic heat ground simulation test.

Description

Technical Field

[0001] This patent relates to a direct radiation convection coupled aerodynamic thermal ground simulation test device, which belongs to the field of aerospace aircraft aerodynamic thermal ground simulation test devices. Technical Background

[0002] When designing thermal protection for reentry vehicles for lunar exploration and interstellar return, it is necessary to consider both convection heating and radiation heating. The ratio of these two heating methods varies with the speed and altitude of the vehicle. In the ground simulation test of thermal protection materials, these two heating methods also need to be tested and evaluated. In the design of thermal protection for vehicles, the main mechanism of convection heating is the heating caused by the convection heat transfer of high-temperature airflow directly flushing the surface of thermal protection materials, and the main mechanism of radiation heating is the radiation heating of thermal protection materials after the dissociation and ionization of high-temperature gas. As an important test method for the refined design of thermal protection structures for high-speed reentry vehicles, radiation-convection coupled aerodynamic thermal tests have begun to be gradually promoted. In this test, high-temperature airflow generated by equipment such as arc heaters and gas flow is used as a convection heat source, and high-energy flux radiation generated by equipment such as quartz lamps, carbon arc lamps, and xenon arc lamps is used as a radiation heat source. They will act on the surface of the test model at the same time to simulate the coupling effect of convection heating generated by the atmosphere and radiation heating generated by high-intensity shock waves on the thermal protection materials of the vehicle when the vehicle reenters at high speed.

[0003] In the above-mentioned convective heat source and radiant heat source generating devices, the arc heater or gas flow device as the convective heat source is usually large and complex, while the radiant heat source is usually simple in structure. Therefore, the radiation convection coupled pneumatic thermal test devices currently used are all improved on the basis of the convective heat source device. The traditional convective heating equipment and the test model are arranged on the same axis, so that the radiation convection coupled test equipment improved on this basis, the radiation heat source generates rays that need to be reflected or obliquely illuminated to act on the test model, which makes the radiation heat efficiency and the radiation uniformity received by the surface of the test model low. In order to improve the above-mentioned radiant heat environment disadvantages in the radiation convection coupled test device, it is necessary to develop a new set of test equipment. Summary of the invention

[0004] The technical problem to be solved by the present invention is to overcome the deficiencies of the prior art and provide a radiation-convection coupling test device capable of generating a direct irradiation radiant heat environment and a convective heat environment with a higher flow field quality.

[0005] The technical solution of the present invention is: a direct radiation convection coupled aerodynamic thermal ground simulation test device, comprising a convection heat source, a four-way mixing chamber, a radiation heat source, an ellipsoidal reflector, a water-cooled nozzle, a test model and a model feeding base; wherein:

[0006] The four-way mixing chamber comprises an airflow cavity and a radiation cavity; the airflow cavity is a cross-shaped cavity formed by the intersection of a longitudinal cavity and a transverse cavity; the longitudinal cavity is a cone-shaped cavity, and the transverse cavity is a cylindrical cavity with small ends and a large middle; the radiation cavity is a semi-ellipsoidal cavity; the large end of the longitudinal cavity of the airflow cavity is connected to the large end of the semi-ellipsoidal cavity, and the axes coincide with each other;

[0007] There are two convection heat sources, which are connected to the two ends of the transverse cavity of the airflow cavity. There is one radiation heat source, which is installed on the outside of the small end of the semi-ellipsoidal cavity. The back of the ellipsoidal reflector is coated with heat-conducting material and then attached to the semi-ellipsoidal cavity and fixed. The water-cooling nozzle is connected to the small end of the longitudinal cavity of the airflow cavity. The test model is installed on the model feeding base. The model stationary point is separated from the outlet of the water-cooling nozzle by a certain distance and is located at the far focus of the ellipsoidal reflector.

[0008] The central axes of the radiation heat source and the test model are collinear, and the central axes of the two convection heat sources are collinear, and the two lines are orthogonal;

[0009] After being reflected by the ellipsoidal reflector, the rays emitted by the radiation heat source gradually converge on the end face of the test model stagnation point along the longitudinal axis of the device, forming a radiation heating field;

[0010] The high-pressure cold air introduced from the two convection heat sources is heated to become high-pressure hot air, which enters the airflow cavity of the four-way mixing chamber relatively, and is mixed with the high-pressure cold air introduced from the airflow cavity and the radiation cavity. It enters the water-cooled nozzle through the longitudinal cavity of the airflow cavity, and after being accelerated by the water-cooled nozzle, it flows through the surface of the test model to form a convection heating field.

[0011] Preferably, the air flow cavity comprises a four-way inner shell, a first air inlet ring, a small end flange, a four-way outer shell, an upstream flange, and a large end flange; the outer wall surface of the four-way inner shell has a rib structure; the four-way outer shell is wrapped around the outer side of the four-way inner shell, and the cavity formed between the ribs of its inner wall surface and the outer wall surface of the four-way inner shell is the first water cooling channel; the small end flange is installed on the small end side of the longitudinal through cavity of the four-way inner shell, the outer wall surface of the flange circumferentially has a first water outlet channel, and the inner wall surface has a first annular water collecting groove; the upstream flange is installed on both sides of the transverse through cavity of the four-way inner shell, a total of two pieces, the outer wall surface of the flange circumferentially has a first water inlet channel, and the inner wall surface has a first annular water collecting groove; the large end flange is installed on the large end side of the longitudinal through cavity of the four-way inner shell, the outer wall surface of the flange circumferentially has a first water outlet channel and a first air inlet channel, and the inner wall surface has a first annular water collecting groove and a first air collecting groove; the first air inlet ring is installed on the inner side of the first air collecting groove of the large end flange, and a number of first air inlet holes are evenly distributed on it;

[0012] The radiation cavity comprises a radiation cavity inner shell, a second air inlet ring, a connecting flange, a radiation cavity outer shell, and a radiation flange; wherein, the outer wall surface of the radiation cavity inner shell has ribs, and an air cooling channel is opened along the symmetry axis at the tip of the ellipsoid; the radiation cavity outer shell is wrapped around the outer side of the radiation cavity inner shell, and the channel between its inner wall surface and the ribs of the outer wall of the radiation cavity inner shell forms a second water cooling channel; the connecting flange is installed at the large end of the radiation cavity inner shell, and a second water outlet channel is opened on its circumferential outer wall surface, and a second annular water collecting groove is opened on the inner wall surface; the radiation flange is installed at the small end of the radiation cavity inner shell, and a second water inlet channel and a second air inlet channel are opened on the circumferential outer wall surface of the flange, and a second annular water collecting groove and a second air collecting groove are opened on the inner wall surface, and a radiation source mounting hole is opened on the end face close to the second air collecting groove along the symmetry axis; the second air inlet ring is installed on the inner side of the second air collecting groove of the radiation flange, and a number of second air inlet holes are evenly distributed thereon.

[0013] Preferably, the first air inlet ring is an equal-diameter circular ring, and the inlet direction of the first air inlet hole thereon on the outer circumferential surface of the first air inlet ring is the same as the radial direction, and the outlet direction on the inner circumferential surface of the first air inlet ring is at a 45° angle to the axis of the first air inlet ring, with a rounded transition between the two, and the radius of the transition rounded corner on the central axis of the first air inlet hole is not less than the thickness of the first air inlet ring; the sum of the cross-sectional areas of the first air inlet holes is equal to the sum of the cross-sectional areas of the first air inlet channels; the taper of the longitudinal through cavity is consistent with the converging light path of the radiation source; the inner surfaces of the longitudinal through cavity and the transverse through cavity are tangent at the junction.

[0014] Preferably, the second air inlet ring and the axis of the radiation cavity are in a 45° cone, and the second air inlet holes distributed thereon are perpendicular to the surface of the second air inlet ring; the sum of the cross-sectional areas of the second air inlet holes is equal to the sum of the cross-sectional areas of the second air inlet channels; the sum of the number and cross-sectional areas of the second air inlet channels are respectively greater than the sum of the number and cross-sectional areas of the first air inlet channels.

[0015] Preferably, the ratio of the sum of the water resistances of the first water-cooling channel and the second water-cooling channel in the four-way mixing chamber to the total water resistance of all the test devices is less than 0.3.

[0016] Preferably, the width of the gap between the outer wall surface of the radiation heat source and the air cooling channel of the four-way mixing chamber is not less than 2 mm.

[0017] Preferably, the focal length of the ellipsoidal reflector is not greater than 1 m, and the outer wall shape of the semi-ellipsoidal inner cavity is the same as that of the ellipsoidal reflector.

[0018] Preferably, the inner wall surface of the water-cooling nozzle does not intersect with the radiation convergence area formed by the radiation heat source, and the length of the water-cooling nozzle is such that the distance between its outlet and the stagnation point of the test model is less than 10 mm.

[0019] Preferably, the pressure of the high-pressure cold air introduced into the four-way mixing chamber is greater than the pressure of the high-pressure hot air inside the convection heat source after the convection heat source is started.

[0020] Preferably, the spherical radius or plane radius of the stagnation point end surface of the test model is not greater than 1.2 times the outlet radius of the water-cooling nozzle.

[0021] Preferably, the feeding speed of the model into the base is greater than 1 m / s, the control accuracy is less than 0.2 mm, and the maximum thrust is greater than 3 t.

[0022] A test method implemented by using the direct radiation convection coupled aerodynamic thermal ground simulation test device comprises:

[0023] Before the test device is started, the model is sent into the base to control the test model to move to the outlet of the water-cooling nozzle; high-pressure cooling water is introduced into the two convection heat sources, the four-way mixing chamber and the water-cooling nozzle, and high-pressure cold air is introduced into the two convection heat sources and the four-way mixing chamber;

[0024] The test device is started, and the model is sent into the base to control the test model to move to the outlet center of the water-cooled nozzle; the rays emitted by the radiation heat source are reflected by the ellipsoid reflector and gradually converge on the stagnation point end face of the test model along the longitudinal axis of the device to form a radiation heating field; at this time, the high-pressure cooling water in the radiation cavity of the four-way mixing chamber is used to cool the ellipsoid reflector, and the high-pressure cold air cooling is used for the radiation heat source; the high-pressure cold air in the two convection heat sources is heated to become high-pressure hot air, which enters the airflow cavity of the four-way mixing chamber relatively, and is mixed with the high-pressure cold air introduced into the airflow cavity and the radiation cavity of the four-way mixing chamber, and enters the water-cooled nozzle through the longitudinal cavity of the airflow cavity of the four-way mixing chamber. After being rectified by the water-cooled nozzle, it flows through the surface of the test model to form a convection heating field; at this time, the high-pressure cooling water in the convection heat source, the airflow cavity of the four-way mixing chamber and the water-cooled nozzle is used to cool the corresponding devices;

[0025] After the test, the model is sent into the base to control the test model to move to the outlet of the water-cooling nozzle. The two convection heat sources, the air flow cavity of the four-way mixing chamber, and the water-cooling nozzle stop supplying high-pressure cooling water and high-pressure cold air, and the radiation cavity of the four-way mixing chamber continues to supply high-pressure cooling water and high-pressure cold air until the radiation heat source cools to room temperature.

[0026] Compared with the prior art, the present invention has the following beneficial effects:

[0027] (1) The present invention can provide a direct radiation heating field without reflection or oblique illumination, effectively improving the radiation heat efficiency and the radiation uniformity of the receiving surface;

[0028] (2) The present invention can integrate two convection heat sources, effectively increasing the total convection heat power, thereby expanding the size of the convection flow field and further expanding the size of the test model;

[0029] (3) The present invention places two convective heat sources opposite to each other, and the high-pressure hot air generated collides with each other in the four-way mixing chamber, which can be more effectively mixed and de-racemized with the high-pressure cold air, and then rectified by the longitudinal cavity of the four-way mixing chamber to form a flow field with higher uniformity. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 It is a schematic diagram of a direct radiation convection coupled aerodynamic thermal ground simulation test device according to an embodiment of the present invention.

[0031] FIG2( a ) is a schematic diagram of the flow of high-pressure cooling water when an embodiment of the present invention is used;

[0032] FIG2( b ) is a schematic diagram of the direction of high-pressure cold air and the convection heating field and the radiation heating field when the embodiment of the present invention is used;

[0033] Figure 3 A side cross-sectional view of a four-way mixing chamber used in an embodiment of the present invention;

[0034] Figure 4 A cross-sectional view of the airflow cavity of a four-way mixing chamber used in an embodiment of the present invention;

[0035] Figure 5 A cross-sectional view of a four-way mixing chamber radiation cavity used in an embodiment of the present invention;

[0036] Figure 6 This is a schematic diagram of the use of a four-way mixing chamber used in an embodiment of the present invention. DETAILED DESCRIPTION

[0037] Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although exemplary embodiments of the present disclosure are shown in the accompanying drawings, it should be understood that the present disclosure can be implemented in various forms and should not be limited by the embodiments described herein. On the contrary, these embodiments are provided in order to enable a more thorough understanding of the present disclosure and to fully convey the scope of the present disclosure to those skilled in the art. It should be noted that, in the absence of conflict, the embodiments of the present invention and the features described in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0038] The present invention provides a direct radiation convection coupled aerodynamic heat ground simulation test device, comprising a convection heat source 1, a four-way mixing chamber 2, a radiation heat source 3, an ellipsoidal reflector 4, a water-cooled nozzle 5, a test model 6 and a model feeding base 7, such as Figure 1 As shown. Among them:

[0039] There are two convection heat sources 1, which are connected to the two ends of the transverse through-cavity of the airflow cavity of the four-way mixing chamber 2 by bolts. There is one radiation heat source 3, and the tail is connected to the radiation source mounting hole of the four-way mixing chamber 2 by threads. The back of the ellipsoidal reflector 4 is coated with high thermal conductivity silicone grease and then attached to the radiation cavity of the four-way mixing chamber 2, and is pressed and fixed between the radiation cavity and the airflow cavity of the four-way mixing chamber 2. The water-cooling nozzle 5 is connected to the small end of the longitudinal through-cavity of the airflow cavity of the four-way mixing chamber 2 by bolts. The test model 6 is installed on the model feeding base 7. The model stationary point is separated from the outlet of the water-cooling nozzle 5 by a certain distance and is located at the far focus of the ellipsoidal reflector 4.

[0040] Before the test device is started, the model is fed into the base 7 to control the test model 6 to move to the outlet of the water cooling nozzle 5. High-pressure cooling water is introduced into the two convection heat sources 1, the four-way mixing chamber 2 and the water cooling nozzle 5. Figure 2a As shown, high pressure cold air is introduced into two convection heat sources 1 and four-way mixing chamber 2. After the device is started, Figure 2b As shown, the model is fed into the base 7 to control the test model 6 to move to the outlet center of the water-cooled nozzle 5. After the rays emitted by the radiation heat source 4 are reflected by the ellipsoid reflector 4, they gradually converge on the stagnation point end face of the test model 5 along the longitudinal axis of the device to form a radiation heating field. At this time, the high-pressure cooling water in the radiation cavity of the four-way mixing chamber 2 is used to cool the ellipsoid reflector 4, and the high-pressure cold air is used for cooling the radiation heat source 3. The high-pressure cold air in the two convection heat sources 1 is heated to become high-pressure hot air, which enters the airflow cavity of the four-way mixing chamber 2 relatively, and is mixed with the high-pressure cold air that is jointly introduced into the airflow cavity and the radiation cavity of the four-way mixing chamber 2, and enters the water-cooled nozzle 5 through the longitudinal through cavity of the airflow cavity of the four-way mixing chamber 2. After being accelerated by the water-cooled nozzle 5, it flows through the surface of the test model 6 to form a convection heating field. At this time, the high-pressure cooling water in the convection heat source 1, the airflow cavity of the four-way mixing chamber 2 and the water-cooled nozzle 5 is used to cool the corresponding devices. After the test, the model is sent into the base 7 to control the test model 6 to move to the outlet of the water-cooling nozzle 5, and the two convection heat sources 1, the air flow cavity of the four-way mixing chamber 2, and the water-cooling nozzle 5 stop supplying high-pressure cooling water and high-pressure cold air, and the radiation cavity of the four-way mixing chamber 2 continues to supply high-pressure cooling water and high-pressure cold air until the radiation heat source 3 is cooled to room temperature.

[0041] Specifically, the four-way mixing chamber 2 is a four-way mixing chamber for radiation convection coupled pneumatic thermal testing, including an airflow chamber 21 and a radiation chamber 22. Figure 3 As shown. Among them:

[0042] The air flow chamber 21 includes a small end flange 211, a four-way inner shell 212, a four-way outer shell 213, an upstream flange 214, a large end flange 215 and a first intake ring 216. Figure 4As shown. Among them, the four-way inner shell 212 is a cross-shaped cylindrical structure composed of a longitudinal through cavity 2104 and a transverse through cavity 2106. The longitudinal through cavity 2104 is a conical cylinder, and the transverse through cavity 2106 is a cylindrical shape with small ends and a large middle. The outer wall of the four-way inner shell 212 has a rib structure. The four-way outer shell 213 is wrapped around the outside of the four-way inner shell 212, and the cavity formed between its inner wall and the ribs on the outer wall of the four-way inner shell 212 is the first water-cooling channel 2103. The small end flange 211 is installed on the small end side of the longitudinal through cavity 2104 of the four-way inner shell 212, and the outer wall surface of the flange circumferentially is provided with a first water outlet channel 2101, and the inner wall surface is provided with a first annular water collecting trough 2102. The upstream flange 214 is installed on both sides of the transverse through cavity 2106 of the four-way inner shell 212, and there are two of them. The outer wall surface of the flange is provided with a first water inlet channel 2105, and the inner wall surface is provided with an annular first water collecting groove 2102. The large end flange 215 is installed on the large end side of the longitudinal through cavity 2104 of the four-way inner shell 212. The outer wall surface of the flange is provided with a first water outlet channel 2101 and a first air inlet channel 2107, and the inner wall surface is provided with an annular first water collecting groove 2102 and a first air collecting groove 2108. The first air inlet ring 216 is installed on the inner side of the first air collecting groove 2108 of the large end flange 215, and a plurality of first air inlet holes 2109 are evenly distributed thereon.

[0043] The radiation cavity 22 includes a connecting flange 221, a radiation cavity inner shell 222, a radiation cavity outer shell 223, a radiation flange 224 and a second air inlet ring 225. Figure 5 As shown. The radiation cavity inner shell 222 is a semi-ellipsoid inner cavity 2204, whose outer wall surface has ribs, and an air cooling channel 2209 is opened along the symmetry axis at the apex of the ellipsoid. The radiation cavity outer shell 223 is wrapped around the outer side of the radiation cavity inner shell 222, and the channel between its inner wall surface and the outer wall ribs of the radiation cavity inner shell 222 forms a second water cooling channel 2203. The connecting flange 221 is installed at the large end of the radiation cavity inner shell 222, and the circumferential outer wall surface thereof is opened with a second water outlet channel 2201, and the inner wall surface is opened with an annular second water collecting groove 2202. The radiation flange 224 is installed at the small end of the radiation cavity inner shell 222, and the circumferential outer wall surface of the flange is opened with a second water inlet channel 2210 and a second air inlet channel 2205, and the inner wall surface is opened with an annular second water collecting groove 2202 and a second air collecting groove 2206, and the flange is opened with a radiation source mounting hole 2208 along the symmetry axis on the end surface close to the second air collecting groove 2206. The second air inlet ring 225 is installed on the inner side of the second air collecting groove 2206 of the radiation flange 224, and has a plurality of second air inlet holes 2207 evenly distributed thereon.

[0044] like Figure 6As shown, when in use, the airflow chamber 21 and the radiation chamber 22 are bolted together through the large end flange 215 and the connecting flange 221, and high-pressure cooling water and high-pressure cold air are respectively introduced into the airflow chamber 21 and the radiation chamber 22. For the airflow chamber 21, the high-pressure cooling water enters the first water cooling channel 2103 through the first water collecting groove 2102 from the first water inlet channel 2105 of the two upstream flanges 214, and flows out from the two sides, namely the first water outlet channel 2101 of the small end flange 211 and the large end flange 215 after merging at the intersection of the longitudinal through cavity 2104 and the transverse through cavity 2106. The high-pressure cold air enters the first collecting groove 2108 from the first air inlet channel 2107 of the large end flange 215, and then enters the four-way inner shell 212 from the first air inlet holes 2109 of the first air inlet ring 216. For the radiation cavity 22, high-pressure cooling water enters the second water cooling channel 2203 from the second water inlet channel 2210 of the radiation flange 224 through the second water collecting tank 2202, and then flows out from the second water outlet channel 2201 of the connecting flange 221. High-pressure cold air enters the second air collecting tank 2206 from the second air inlet channel 2205 of the radiation flange 224, passes through several second air inlet holes 2207 of the second air inlet ring 225, flows through the air cooling channel 2209 and enters the radiation cavity inner shell 222.

[0045] Specifically, the first air inlet ring 216 of the air flow cavity 21 is an equal diameter circular ring, and the inlet direction of the first air inlet hole 2109 on the outer circumferential surface of the first air inlet ring 216 is the same as the radial direction, and the outlet direction on the inner circumferential surface of the first air inlet ring 216 is at a 45° angle to the axis of the first air inlet ring 216, and there is a fillet transition between the two, and the radius of the transition fillet on the central axis of the first air inlet hole 2109 is not less than the thickness of the first air inlet ring 216. The second air inlet ring 225 of the radiation cavity 22 is conical at 45° to the axis of the radiation cavity 22, and the second air inlet holes 2207 distributed thereon are perpendicular to the surface of the second air inlet ring 225.

[0046] Specifically, the sum of the cross-sectional areas of the first air inlet holes 2109 of the airflow cavity 21 is equal to the sum of the cross-sectional areas of the first air inlet channel 2107. The sum of the cross-sectional areas of the second air inlet holes 2207 of the radiation cavity 22 is equal to the sum of the cross-sectional areas of the second air inlet channel 2205.

[0047] Specifically, the sum of the number and the cross-sectional area of ​​the second air inlet channels 2205 is respectively greater than the sum of the number and the cross-sectional area of ​​the first air inlet channels 2107 .

[0048] Specifically, the taper of the longitudinal through cavity 2104 of the airflow cavity 21 is consistent with the convergent optical path of the radiation source. The inner surfaces of the longitudinal through cavity 2104 and the transverse through cavity 2106 are tangent at their intersections.

[0049] Specifically, the semi-ellipsoidal inner cavity 2204 of the radiation cavity inner shell 222 of the radiation cavity 22 has the same outer wall shape as the ellipsoidal reflector 4 used by the radiation source.

[0050] Specifically, the cross-way inner shell 212 and the radiation chamber inner shell 222 are made of zirconium bronze, and the remaining components are made of stainless steel. All components of the airflow chamber 21 and the radiation chamber 22 are assembled by vacuum furnace brazing.

[0051] Specifically, the central axes of the radiation heat source 3 and the test model 6 are collinear, and the central axes of the two convection heat sources 1 are collinear, and the two lines are orthogonal. The width of the gap between the outer wall of the radiation heat source 3 and the air cooling channel 2209 of the four-way mixing chamber 2 is not less than 2 mm.

[0052] Specifically, the focal length of the ellipsoidal reflector 4 is less than 1 m.

[0053] Specifically, the inner wall surface of the water-cooling nozzle 5 does not intersect with the radiation convergence area formed by the radiation heat source 2. The length of the water-cooling nozzle 5 should be such that the distance between its outlet and the stagnation point of the test model 6 is less than 10 mm.

[0054] Specifically, the pressure of the high-pressure cold air introduced into the four-way mixing chamber 2 is greater than the pressure of the high-pressure hot air inside the convection heat source 1 after it is started.

[0055] Specifically, the spherical radius or plane radius of the stagnation point end surface of the test model 6 is not greater than 1.2 times the outlet radius of the water-cooling nozzle 5 .

[0056] Specifically, the ratio of the sum of the water resistances of the first water-cooling channel 2103 and the second water-cooling channel 2203 in the four-way mixing chamber 2 to the total water resistance of all the test devices is less than 0.3.

[0057] Specifically, the feeding speed of the model into the base 7 is greater than 1 m / s, the control accuracy is less than 0.2 mm, and the maximum thrust is greater than 3 t.

[0058] The description of the component devices and the experimental verification of the present invention have proved the characteristics of the present invention. The radiation heat source colinear with the test model can provide a direct radiation heating field without reflection or oblique illumination, effectively improving the radiation heat efficiency and the radiation uniformity of the receiving surface; the two oppositely placed convection heat sources can effectively increase the total convection heat power, thereby expanding the size of the convection flow field, and then expanding the size of the test model, and the high-pressure hot air generated by the relative collision in the four-way mixing chamber can be more effectively mixed and de-racemized with the high-pressure cold air, and then formed into a flow field with higher uniformity after rectification by the longitudinal through cavity of the four-way mixing chamber.

[0059] The present invention can be applied to radiation-convection coupled aerodynamic thermal ground tests, and the undisclosed technology is common knowledge to those skilled in the art. Although the present invention has been disclosed as above in the preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solution of the present invention by using the above disclosed methods and technical contents without departing from the spirit and scope of the present invention. Therefore, any simple modification, equivalent changes and modifications made to the above embodiments according to the technical essence of the present invention without departing from the content of the technical solution of the present invention are within the protection scope of the technical solution of the present invention.

Claims

1. A direct radiation convection coupled aerodynamic thermal ground simulation test device, characterized in that It includes a convection heat source, a four-way mixing chamber, a radiation heat source, an ellipsoidal reflector, a water-cooled nozzle, a test model and a model delivery base; wherein: The four-way mixing chamber comprises an airflow cavity and a radiation cavity; the airflow cavity is a cross-shaped cavity formed by the intersection of a longitudinal cavity and a transverse cavity; the longitudinal cavity is a cone-shaped cavity, and the transverse cavity is a cylindrical cavity with small ends and a large middle; the radiation cavity is a semi-ellipsoidal cavity; the large end of the longitudinal cavity of the airflow cavity is connected to the large end of the semi-ellipsoidal cavity, and the axes coincide with each other; There are two convection heat sources, which are connected to the two ends of the transverse cavity of the airflow cavity. There is one radiation heat source, which is installed on the outside of the small end of the semi-ellipsoidal cavity. The back of the ellipsoidal reflector is coated with heat-conducting material and then attached to the semi-ellipsoidal cavity and fixed. The water-cooling nozzle is connected to the small end of the longitudinal cavity of the airflow cavity. The test model is installed on the model feeding base. The model stationary point is separated from the outlet of the water-cooling nozzle by a certain distance and is located at the far focus of the ellipsoidal reflector. The central axes of the radiation heat source and the test model are collinear, and the central axes of the two convection heat sources are collinear, and the two lines are orthogonal; After being reflected by the ellipsoidal reflector, the rays emitted by the radiation heat source gradually converge on the end face of the test model stagnation point along the longitudinal axis of the device, forming a radiation heating field; The high-pressure cold air introduced from the two convection heat sources is heated to become high-pressure hot air, which enters the airflow cavity of the four-way mixing chamber relatively, and is mixed with the high-pressure cold air introduced from the airflow cavity and the radiation cavity. It enters the water-cooled nozzle through the longitudinal cavity of the airflow cavity, and after being accelerated by the water-cooled nozzle, it flows through the surface of the test model to form a convection heating field.

2. A direct radiation convection coupled aerodynamic thermal ground simulation test device according to claim 1, characterized in that: The airflow cavity comprises a four-way inner shell, a first air inlet ring, a small end flange, a four-way outer shell, an upstream flange and a large end flange; the outer wall of the four-way inner shell has a rib structure; the four-way outer shell is wrapped around the outer side of the four-way inner shell, and the cavity formed between the ribs of its inner wall and the outer wall of the four-way inner shell is the first water cooling channel; the small end flange is installed on the small end side of the longitudinal cavity of the four-way inner shell, the outer wall surface of the flange circumferentially has a first water outlet channel, and the inner wall surface has a first annular water collecting groove; the upstream flange is installed on both sides of the transverse cavity of the four-way inner shell, a total of two pieces, the outer wall surface of the flange circumferentially has a first water inlet channel, and the inner wall surface has a first annular water collecting groove; the large end flange is installed on the large end side of the longitudinal cavity of the four-way inner shell, the outer wall surface of the flange circumferentially has a first water outlet channel and a first air inlet channel, and the inner wall surface has a first annular water collecting groove and a first air collecting groove; the first air inlet ring is installed on the inner side of the first air collecting groove of the large end flange, and a number of first air inlet holes are evenly distributed on it; The radiation cavity comprises a radiation cavity inner shell, a second air inlet ring, a connecting flange, a radiation cavity outer shell, and a radiation flange; wherein, the outer wall surface of the radiation cavity inner shell has ribs, and an air cooling channel is opened along the symmetry axis at the tip of the ellipsoid; the radiation cavity outer shell is wrapped around the outer side of the radiation cavity inner shell, and the channel between its inner wall surface and the ribs of the outer wall of the radiation cavity inner shell forms a second water cooling channel; the connecting flange is installed at the large end of the radiation cavity inner shell, and a second water outlet channel is opened on its circumferential outer wall surface, and a second annular water collecting groove is opened on the inner wall surface; the radiation flange is installed at the small end of the radiation cavity inner shell, and a second water inlet channel and a second air inlet channel are opened on the circumferential outer wall surface of the flange, and a second annular water collecting groove and a second air collecting groove are opened on the inner wall surface, and a radiation source mounting hole is opened on the end face close to the second air collecting groove along the symmetry axis; the second air inlet ring is installed on the inner side of the second air collecting groove of the radiation flange, and a number of second air inlet holes are evenly distributed thereon.

3. A direct radiation convection coupled aerodynamic thermal ground simulation test device according to claim 2, characterized in that: The first air inlet ring is an equal-diameter circular ring, and the inlet direction of the first air inlet hole on the outer circumferential surface of the first air inlet ring is the same as the radial direction, and the outlet direction on the inner circumferential surface of the first air inlet ring is at a 45° angle to the axis of the first air inlet ring, and there is a rounded transition between the two, and the radius of the transition rounded corner on the central axis of the first air inlet hole is not less than the thickness of the first air inlet ring; the sum of the cross-sectional areas of the first air inlet holes is equal to the sum of the cross-sectional areas of the first air inlet channels; the taper of the longitudinal through cavity is consistent with the converging light path of the radiation source; the inner surfaces of the longitudinal through cavity and the transverse through cavity are tangent at the junction.

4. A direct radiation convection coupled aerodynamic thermal ground simulation test device according to claim 2, characterized in that: The second air inlet ring and the axis of the radiation cavity are in a 45° cone, and the second air inlet holes distributed thereon are perpendicular to the surface of the second air inlet ring; the sum of the cross-sectional areas of the second air inlet holes is equal to the sum of the cross-sectional areas of the second air inlet channels; the sum of the number and cross-sectional areas of the second air inlet channels are respectively greater than the sum of the number and cross-sectional areas of the first air inlet channels.

5. The direct radiation convection coupled aerodynamic thermal ground simulation test device according to claim 2, characterized in that: The ratio of the sum of the water resistance of the first water-cooling channel and the second water-cooling channel in the four-way mixing chamber to the total water resistance of all the test devices is less than 0.

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6. The direct radiation convection coupled aerodynamic thermal ground simulation test device according to claim 1, characterized in that: The width of the gap between the outer wall surface of the radiation heat source and the air cooling channel of the four-way mixing chamber is not less than 2mm.

7. The direct radiation convection coupled aerodynamic thermal ground simulation test device according to claim 1 is characterized by: The focal length of the ellipsoid reflector is no more than 1m, and the outer wall of the semi-ellipsoidal inner cavity is the same in shape as the outer wall of the ellipsoid reflector.

8. The direct radiation convection coupled aerodynamic thermal ground simulation test device according to claim 1 is characterized by: The inner wall surface of the water-cooling nozzle does not intersect with the radiation convergence area formed by the radiation heat source, and the length of the water-cooling nozzle is such that the distance between its outlet and the stagnation point of the test model is less than 10 mm.

9. The direct radiation convection coupled aerodynamic thermal ground simulation test device according to claim 1, characterized in that: The pressure of the high-pressure cold air introduced into the four-way mixing chamber is greater than the pressure of the high-pressure hot air inside the convection heat source after the convection heat source is started.

10. The direct radiation convection coupled aerodynamic thermal ground simulation test device according to claim 1, characterized in that: The spherical radius or plane radius of the stagnation point end surface of the test model is not greater than 1.2 times the outlet radius of the water-cooling nozzle.

11. The direct radiation convection coupled aerodynamic thermal ground simulation test device according to claim 1, characterized in that: The feeding speed of the model into the base is greater than 1m / s, the control accuracy is less than 0.2mm, and the maximum thrust is greater than 3t.

12. A test method implemented by using the direct radiation convection coupled aerodynamic thermal ground simulation test device according to claim 1, characterized in that include: Before the test device is started, the model is sent into the base to control the test model to move outside the outlet of the water-cooling nozzle; High-pressure cooling water is introduced into the two convection heat sources, the four-way mixing chamber and the water-cooling nozzle, and high-pressure cold air is introduced into the two convection heat sources and the four-way mixing chamber; The test device is started, and the model is sent into the base to control the test model to move to the outlet center of the water-cooled nozzle; the rays emitted by the radiation heat source are reflected by the ellipsoid reflector and gradually converge on the stagnation point end face of the test model along the longitudinal axis of the device to form a radiation heating field; at this time, the high-pressure cooling water in the radiation cavity of the four-way mixing chamber is used to cool the ellipsoid reflector, and the high-pressure cold air cooling is used for the radiation heat source; the high-pressure cold air in the two convection heat sources is heated to become high-pressure hot air, which enters the airflow cavity of the four-way mixing chamber relatively, and is mixed with the high-pressure cold air introduced into the airflow cavity and the radiation cavity of the four-way mixing chamber, and enters the water-cooled nozzle through the longitudinal cavity of the airflow cavity of the four-way mixing chamber. After being rectified by the water-cooled nozzle, it flows through the surface of the test model to form a convection heating field; at this time, the high-pressure cooling water in the convection heat source, the airflow cavity of the four-way mixing chamber and the water-cooled nozzle is used to cool the corresponding devices; After the test, the model is sent into the base to control the test model to move to the outlet of the water-cooling nozzle. The two convection heat sources, the air flow cavity of the four-way mixing chamber, and the water-cooling nozzle stop supplying high-pressure cooling water and high-pressure cold air, and the radiation cavity of the four-way mixing chamber continues to supply high-pressure cooling water and high-pressure cold air until the radiation heat source cools to room temperature.

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