Hypersonic speed wind tunnel test model support with active cooling function and test method of hypersonic speed wind tunnel test model support

Abstract

The invention belongs to the technical field of hypersonic wind tunnel tests, and discloses a hypersonic wind tunnel test model support with an active cooling function and a test method thereof. A cooling water inlet and a cooling water outlet are formed in an inclined column of the bracket, so that the bracket has an active cooling function and can effectively support a test model to carry out a hypersonic wind tunnel test; the rear portion of the support is provided with a cavity defined by the cross beam, the skin and the like and a wire outlet hole of the tail cover, and the cavity and the wire outlet hole can be used for wiring of a test model measurement and control cable, the measurement and control cable is isolated from high-speed airflow, and thermal protection is achieved. The test method comprises the steps of mounting the batter post; installing a tail cover; the sealing plate is mounted on the inclined column; installing a left cross beam and a right cross beam; installing the skin; installing a test model; mounting a bracket; and performing a hypersonic wind tunnel test. The test method can meet the requirement of a hypersonic wind tunnel test, is compatible with an existing hypersonic wind tunnel test method, is stable and reliable, is high in efficiency, and has engineering practical value.

Description

Technical Field

[0001] The present invention belongs to the technical field of hypersonic wind tunnel testing, and particularly relates to a hypersonic wind tunnel test model support with active cooling and a test method thereof. Background Technique

[0002] Hypersonic wind tunnels are mainly used to conduct wind tunnel tests with an oncoming flow velocity reaching Mach number 5 or above. In order to obtain aerodynamic data such as aerodynamic drag and aerodynamic lift generated by the test model in the wind tunnel test, the test model needs to be installed on the wind tunnel balance through a support and then the wind tunnel test is carried out. The support needs to have a high load-bearing capacity to ensure test safety and also needs to have high stiffness to prevent support deformation from affecting test accuracy.

[0003] Compared with wind tunnel tests in lower speed ranges, the biggest challenge in hypersonic wind tunnel tests is that the model and the support are subjected to severe aerodynamic heating. For example, in an aerodynamic heating environment with an oncoming flow velocity of Mach number 6, the surface temperatures of the model and the support will rise sharply, and the temperature at the leading edge can reach 1000°C - 1250°C, which has exceeded the temperature resistance limit of ordinary metals, resulting in a sharp reduction in the support life and making it impossible to be reused.

[0004] In order to improve the temperature resistance of the support, high-temperature alloys, ceramic matrix composites, etc. can be used for the support structure design. However, these high-performance materials will greatly increase the manufacturing cost of the support. On the other hand, after repeated use in extreme thermal environments, the performance of high-temperature alloys and ceramic matrix composites will gradually degrade, resulting in a reduction in the load-bearing capacity or stiffness of the support, thereby increasing test risks or reducing test accuracy.

[0005] Currently, there is an urgent need to develop a hypersonic wind tunnel test model support with active cooling and a test method thereof. Summary of the Invention

[0006] One technical problem to be solved by the present invention is to provide a hypersonic wind tunnel test model support with active cooling, and another technical problem to be solved by the present invention is to provide a test method for the hypersonic wind tunnel test model support with active cooling to overcome the defects of the prior art.

[0007] The hypersonic wind tunnel test model support with active cooling of the present invention includes a bottom plate, an inclined column, a sealing plate, a water inlet, a left cross beam, a right cross beam, a left skin, a right skin, a rear skin, a tail cover and a water outlet; At the front section of the upper surface of the bottom plate, a pointed wedge-shaped inclined column is fixed; the inclined column is inclined towards the oncoming flow of the hypersonic wind tunnel, and the central symmetry plane of the inclined column is parallel to the axis of the hypersonic wind tunnel; a sealing plate is covered on the rear end face of the inclined column, and on the sealing plate of the rear end face, a water inlet is sealed and welded near the top surface of the inclined column, and a water outlet is sealed and welded near the bottom surface of the inclined column; On the left side of the rear end face of the inclined column, a number of left crossbeams with equal lengths, equal spacings and parallel to the axis of the hypersonic wind tunnel are fixed in sequence from top to bottom. The outer side surfaces of the left crossbeams are covered with left skins from top to bottom; on the right side of the rear end face of the inclined column, a number of right crossbeams symmetrically distributed with the left crossbeams are fixed. The outer side surfaces of the right crossbeams are covered with right skins from top to bottom; a sealing plate is covered above the topmost left crossbeam and right crossbeam; At the rear section of the upper surface of the bottom plate, a tail cover is fixed. The height of the tail cover is less than the height of the inclined column. The front end of the tail cover is clamped and wrapped around the corresponding left crossbeam and right crossbeam from back to front; a rear skin is covered on the end face formed by the rear ends of the remaining left crossbeams and right crossbeams.

[0008] Further, the bottom plate is a long strip-shaped flat plate; On the outer circle of the bottom plate, a number of through holes matching the lower wall plate of the test section of the hypersonic wind tunnel are arranged along the circumferential direction; In the inner circle of the bottom plate, a number of threaded holes for installing the inclined column are arranged in the front section, which match the inclined column; two rib strips parallel to the central axis of the wind tunnel are arranged in the middle section. A number of threaded holes corresponding to the left skin and the right skin are respectively arranged on the outer sides of the two rib strips; a number of threaded holes for installing the tail cover, which match the tail cover, are arranged in the rear section.

[0009] Further, the inner cavity of the inclined column is a cavity, and the horizontal cross-section of the cavity is a wedge shape; A circle of protruding wing plate I is arranged at the bottom of the inclined column. The wing plate I is provided with through holes matching the threaded holes for installing the inclined column on the bottom plate; On the rear end face of the inclined column, a sealing groove, a set of threaded holes for installing the sealing plate and a set of threaded holes for installing the crossbeam are arranged in sequence from inside to outside. A fluororubber strip is placed in the sealing groove; A sealing plate is arranged on the top surface of the inclined column, and a set of threaded holes for installing the wind tunnel test model are arranged on the sealing plate.

[0010] Further, the sealing plate on the rear end face of the inclined column is fixed on the rear end face of the inclined column by screws. The sealing plate presses the fluororubber strip to seal the cooling water.

[0011] Further, a circle of protruding wing plate II is arranged at the bottom of the tail cover. A set of through holes matching the threaded holes for installing the tail cover on the bottom plate are distributed on the wing plate II; On the front end face of the tail cover, an inclined rib is arranged above. Threaded holes for fixing the rear skin are arranged on the inclined rib; On both sides of the tail cover, threaded holes for fixing the corresponding left crossbeam and right crossbeam are respectively arranged; An outlet hole is arranged on the rear end face of the tail cover.

[0012] The test method of the hypersonic wind tunnel test model support with active cooling of the present invention includes the following steps: S10. Install the inclined column; Align the through holes on the wing plate Ⅰ at the bottom of the inclined column with the threaded holes for installing the inclined column on the bottom plate, and fixedly connect them with a screw assembly; S20. Install the tail cover; Align the through holes on the wing plate Ⅱ at the bottom of the tail cover with the threaded holes for installing the tail cover on the bottom plate, and fixedly connect them with a screw assembly; S30. Install the sealing plate on the inclined column; Place a rubber strip in the sealing groove of the inclined column, install the sealing plate on the threaded holes for installing the sealing plate on the rear end face of the inclined column with a screw assembly, and press the fluororubber strip; S40. Install the left cross beam and the right cross beam; Fix several left cross beams on the left side of the rear end face of the inclined column from top to bottom in sequence through the threaded holes for installing the cross beam. Similarly, fix several right cross beams on the right side of the rear end face of the inclined column from top to bottom in sequence through the threaded holes for installing the cross beam; S40. Install the skin; Cover the left skin on the outer side of each left cross beam from top to bottom. Fix between each left cross beam and the left skin with a screw assembly, and fix the lower end of the left skin on the threaded holes of the corresponding rib on the bottom plate with a screw assembly. Similarly, cover the right skin on the outer side of each right cross beam from top to bottom. Also fix between each right cross beam and the right skin with a screw assembly, and fix the lower end of the right skin on the threaded holes of the corresponding rib on the bottom plate with a screw assembly; Cover the rear skin on the end face formed by the rear ends of the left cross beam and the right cross beam above the tail cover, and fix the rear skin on the inclined rib on the front end face of the tail cover with a screw assembly; Cover a sealing plate above the top left cross beam and right cross beam; S50. Install the test model; Use a screw assembly to install the wind tunnel test model on the sealing plate above the inclined column through the threaded holes for installing the wind tunnel test model; S60. Install the support; Use a screw assembly to fix the bottom plate of the support on the lower wall plate of the hypersonic wind tunnel test section through the through holes. Then, arrange the measurement and control cables of the test model into a bundle and pass them through the cavity surrounded by the left cross beam, the left skin, the right cross beam, and the right skin, and pull them out from the wire outlet hole of the tail cover and connect them to the measurement and control system of the hypersonic wind tunnel; S70. Conduct hypersonic wind tunnel tests; Before the hypersonic wind tunnel test, cooling water is injected into the water inlet and discharged from the water outlet; during the hypersonic wind tunnel test, the cooling water is continuously supplied and discharged; after the hypersonic wind tunnel test is completed, the cooling water is continuously supplied and discharged within a pre-determined time period, and after reaching the pre-determined time, the cooling water is shut off.

[0013] On the inclined columns of the test model support of the hypersonic wind tunnel with active cooling of the present invention, there are provided a cooling water inlet and a water outlet, which have the function of active cooling and can effectively support the test model to carry out hypersonic wind tunnel tests; the cavity formed by the cross beam and the skin at the rear of the support, as well as the wire outlet holes of the tail cover, can be used for the routing of the measurement and control cables of the test model, isolating the measurement and control cables from the high-speed airflow and realizing thermal protection. The test method of the test model support of the hypersonic wind tunnel with active cooling of the present invention can meet the requirements of hypersonic wind tunnel tests, is compatible with the existing hypersonic wind tunnel test methods, is safe, reliable and efficient, and has engineering practical value. Brief Description of the Drawings

[0014] Figure 1 It is a cross-sectional view of the test model support of the hypersonic wind tunnel with active cooling of the present invention; Figure 2 It is a top view of the test model support of the hypersonic wind tunnel with active cooling of the present invention; Figure 3 It is a positive triaxial view of the test model support of the hypersonic wind tunnel with active cooling of the present invention after hiding the skins on both sides; Figure 4 It is a positive triaxial view of the bottom plate in the test model support of the hypersonic wind tunnel with active cooling of the present invention; Figure 5 It is a positive triaxial view of the inclined column in the test model support of the hypersonic wind tunnel with active cooling of the present invention; Figure 6 It is a positive triaxial view of the tail cover in the test model support of the hypersonic wind tunnel with active cooling of the present invention.

[0015] In the figure: 1. Bottom plate; 2. Inclined column; 3. Sealing plate; 4. Water inlet; 5. Left cross beam; 6. Right cross beam; 7. Left skin; 8. Right skin; 9. Rear skin; 10. Tail cover; 11. Water outlet; 1-1. Through hole; 1-2. Threaded hole for inclined column installation; 1-3. Rib; 1-4. Threaded hole for tail cover installation; 2-1. Wing plate Ⅰ; 2-2. Cavity; 2-3. Sealing groove; 2-4. Threaded hole for sealing plate installation; 2-5. Threaded hole for cross beam installation; 2-6. Threaded hole for wind tunnel test model installation; 10-1. Wing plate Ⅱ; 10-2. Wire outlet hole; 10-3. Inclined rib. Detailed implementation mode

[0016] The following describes the implementation modes of the present invention through specific examples. Those skilled in the art can easily understand other advantages and effects of the present invention from the content disclosed in this specification. The present invention can also be implemented or applied through other different specific implementation modes. Various details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of the present invention.

[0017] Example: As Figures 1 to 3 shown, the hypersonic wind tunnel test model bracket with active cooling in this embodiment includes a bottom plate 1, an inclined column 2, a sealing plate 3, a water inlet 4, a left cross beam 5, a right cross beam 6, a left skin 7, a right skin 8, a rear skin 9, a tail cover 10, and a water outlet 11; At the front section of the upper surface of the bottom plate 1, a pointed wedge-shaped inclined column 2 is fixed; the inclined column 2 is inclined towards the oncoming flow of the hypersonic wind tunnel, and the central symmetry plane of the inclined column 2 is parallel to the axis of the hypersonic wind tunnel; a sealing plate 3 is covered on the rear end surface of the inclined column 2, and on the sealing plate 3 of the rear end surface, a water inlet 4 is hermetically welded near the top surface of the inclined column 2, and a water outlet 11 is hermetically welded near the bottom surface of the inclined column 2; On the left side of the rear end surface of the inclined column 2, a plurality of left cross beams 5 with equal lengths, equal spacings, and parallel to the axis of the hypersonic wind tunnel are fixed in sequence from top to bottom, and the outer sides of the left cross beams 5 are covered with a left skin 7 from top to bottom; on the right side of the rear end surface of the inclined column 2, a plurality of right cross beams 6 symmetrically distributed with the left cross beams 5 are fixed, and the outer sides of the right cross beams 6 are covered with a right skin 8 from top to bottom; a sealing plate 3 is covered above the uppermost left cross beam 5 and right cross beam 6; At the rear section of the upper surface of the bottom plate 1, a tail cover 10 is fixed. The height of the tail cover 10 is less than the height of the inclined column 2, and the front end of the tail cover 10 is clamped and wrapped around the corresponding left cross beam 5 and right cross beam 6 from back to front; a rear skin 9 is covered on the end surface formed by the rear ends of the remaining left cross beams 5 and right cross beams 6.

[0018] Furthermore, as Figure 4 shown, the bottom plate 1 is a long strip-shaped flat plate; A plurality of through holes 1-1 matching the lower wall plate of the hypersonic wind tunnel test section are arranged along the circumferential direction on the outer circle of the bottom plate 1; In the inner circle of the bottom plate 1, a plurality of threaded holes 1-2 for installing the inclined column 2 are arranged in the front section; two rib strips 1-3 parallel to the central axis of the wind tunnel are arranged in the middle section, and a plurality of threaded holes corresponding to the left skin 7 and the right skin 8 are respectively arranged on the outer sides of the two rib strips 1-3; a plurality of threaded holes 1-4 for installing the tail cover 10 are arranged in the rear section.

[0019] Furthermore, as Figure 5As shown, the inner cavity of the inclined column 2 is a cavity 2-2, and the horizontal cross-section of the cavity 2-2 is a wedge shape; A protruding wing plate I 2-1 is provided at the bottom of the inclined column 2, and the wing plate I 2-1 is provided with through holes matching the inclined column installation threaded holes 1-2 on the bottom plate 1; On the rear end face of the inclined column 2, from the inside to the outside, a sealing groove 2-3, a set of sealing plate installation threaded holes 2-4 and a set of cross beam installation threaded holes 2-5 are arranged in sequence. A fluororubber strip is placed in the sealing groove 2-3; A sealing plate is provided on the top surface of the inclined column 2, and a set of wind tunnel test model installation threaded holes 2-6 are provided on the sealing plate.

[0020] Furthermore, the sealing plate 3 on the rear end face of the inclined column 2 is fixed to the rear end face of the inclined column 2 by screws. The sealing plate 3 presses the fluororubber strip to seal the cooling water.

[0021] Furthermore, as Figure 6 shown, a protruding wing plate 10-1 II is provided at the bottom of the tail cover 10, and a set of through holes matching the tail cover installation threaded holes 1-4 on the bottom plate 1 are distributed on the wing plate 10-1 II; On the front end face of the tail cover 10, an inclined rib 10-3 is provided above, and threaded holes for fixing the rear skin 9 are provided on the inclined rib 10-3; On both sides of the tail cover 10, threaded holes for fixing the corresponding left cross beam 5 and right cross beam 6 are provided respectively; On the rear end face of the tail cover 10, a wire outlet hole 10-2 is provided.

[0022] The test method of the hypersonic wind tunnel test model support with active cooling in this embodiment includes the following steps: S10. Install the inclined column 2; Align the through holes on the wing plate I 2-1 at the bottom of the inclined column 2 with the inclined column installation threaded holes 1-2 on the bottom plate 1, and fixedly connect them with screw assemblies; S20. Install the tail cover 10; Align the through holes on the wing plate II 10-1 at the bottom of the tail cover 10 with the tail cover installation threaded holes 1-4 on the bottom plate 1, and fixedly connect them with screw assemblies; S30. Install the sealing plate 3 on the inclined column 2; Place a rubber strip in the sealing groove 2-3 of the inclined column 2, install the sealing plate 3 on the sealing plate installation threaded holes 2-4 on the rear end face of the inclined column 2 with screw assemblies, and press the fluororubber strip; S40. Install the left cross beam 5 and the right cross beam 6; A number of left crossbeams 5 are sequentially fixed from top to bottom on the left side of the rear end face of the inclined column 2 through the threaded holes 2-5 for crossbeam installation. Similarly, a number of right crossbeams 6 are sequentially fixed from top to bottom on the right side of the rear end face of the inclined column 2 through the threaded holes 2-5 for crossbeam installation; S40. Install the skin; On the outer side surfaces of the left crossbeams 5, the left skins 7 are covered from top to bottom. The left crossbeams 5 and the left skins 7 are fixed through screw assemblies. The lower end of the left skin 7 is fixed through a screw assembly on the threaded holes of the corresponding rib 1-3 on the bottom plate 1. Similarly, on the outer side surfaces of the right crossbeams 6, the right skins 8 are covered from top to bottom. The right crossbeams 6 and the right skins 8 are also fixed through screw assemblies. The lower end of the right skin 8 is fixed through a screw assembly on the threaded holes of the corresponding rib 1-3 on the bottom plate 1; Above the tail cover 10, on the end face formed by the rear ends of the left crossbeam 5 and the right crossbeam 6, the rear skin 9 is covered, and the rear skin 9 is fixed through a screw assembly on the inclined rib 10-3 of the front end face of the tail cover 10; The sealing plate 3 is covered above the topmost left crossbeam 5 and right crossbeam 6; S50. Install the test model; Using screw assemblies, the wind tunnel test model is installed on the sealing plate above the inclined column 2 through the threaded holes 2-6 for wind tunnel test model installation; S60. Install the bracket; Using screw assemblies, the bottom plate 1 of the bracket is fixed on the lower wall plate of the hypersonic wind tunnel test section through the through hole 1-1. Then, the measurement and control cables of the test model are bundled and passed through the cavity formed by the left crossbeam 5 and the left skin 7 and the right crossbeam 6 and the right skin 8, and pulled out from the wire outlet hole 10-2 of the tail cover 10 and connected to the measurement and control system of the hypersonic wind tunnel; S70. Conduct hypersonic wind tunnel tests; Before the hypersonic wind tunnel test, cooling water is injected into the water inlet 4 and discharged from the water outlet 11. During the process of the hypersonic wind tunnel, the cooling water is continuously fed in and drained. After the hypersonic wind tunnel test is completed, the cooling water is continuously fed in and drained within a predetermined time period. After reaching the predetermined time, the cooling water is turned off.

[0023] The above embodiments are only illustrative of the principles and effects of the present invention and are not used to limit the present invention. Any person familiar with this technology can modify or change the above embodiments without departing from the spirit and scope of the present invention. Therefore, all equivalent modifications or changes completed by those with ordinary knowledge in the technical field without departing from the spirit and technical ideas disclosed by the present invention should still be covered by the claims of the present invention.

Claims

1. A hypersonic wind tunnel test model support with active cooling, characterized in that The described bracket includes a bottom plate (1), inclined columns (2), a sealing plate (3), a water inlet (4), a left cross beam (5), a right cross beam (6), a left skin (7), a right skin (8), a rear skin (9), a tail cover (10) and a water outlet (11); At the front section of the upper surface of the bottom plate (1), a pointed wedge-shaped inclined column (2) is fixed; the inclined column (2) is inclined towards the oncoming flow of the hypersonic wind tunnel, and the central symmetry plane of the inclined column (2) is parallel to the axis of the hypersonic wind tunnel; a sealing plate (3) is covered on the rear end face of the inclined column (2), and on the sealing plate (3) of the rear end face, a water inlet (4) is sealed and welded at a position close to the top surface of the inclined column (2), and a water outlet (11) is sealed and welded at a position close to the bottom surface of the inclined column (2); On the left side of the rear end face of the inclined column (2), a number of left cross beams (5) with equal lengths, equal spacings and parallel to the axis of the hypersonic wind tunnel are fixed in sequence from top to bottom, and the outer side surfaces of the left cross beams (5) are covered with a left skin (7) from top to bottom; on the right side of the rear end face of the inclined column (2), a number of right cross beams (6) symmetrically distributed with the left cross beams (5) are fixed, and the outer side surfaces of the right cross beams (6) are covered with a right skin (8) from top to bottom; a sealing plate (3) is covered above the uppermost left cross beam (5) and right cross beam (6); At the rear section of the upper surface of the bottom plate (1), a tail cover (10) is fixed, the height of the tail cover (10) is less than the height of the inclined column (2), and the front end of the tail cover (10) is clamped and wrapped around the corresponding left cross beam (5) and right cross beam (6) from back to front; a rear skin (9) is covered on the end face formed by the rear ends of the remaining left cross beams (5) and right cross beams (6).

2. The hypersonic wind tunnel test model support with active cooling according to claim 1, characterized in that The described bottom plate (1) is a long strip-shaped flat plate; On the outer circle of the bottom plate (1), a number of through holes (1-1) matching the lower wall plate of the hypersonic wind tunnel test section are arranged along the circumferential direction; In the inner circle of the bottom plate (1), a number of threaded holes (1-2) for installing the inclined columns are arranged at the front section for matching with the inclined columns (2); two rib strips (1-3) parallel to the central axis of the wind tunnel are arranged at the middle section, and a number of threaded holes corresponding to the left skin (7) and the right skin (8) are respectively arranged on the outer sides of the two rib strips (1-3); a number of threaded holes (1-4) for installing the tail cover are arranged at the rear section for matching with the tail cover (10).

3. The hypersonic wind tunnel test model support with active cooling according to claim 2, characterized in that The inner cavity of the described inclined column (2) is a cavity (2-2), and the horizontal cross section of the cavity (2-2) is a pointed wedge shape; A circle of protruding wing plate I (2-1) is arranged at the bottom of the inclined column (2), and the wing plate I (2-1) is provided with through holes matching the threaded holes (1-2) for installing the inclined columns of the bottom plate (1); On the rear end face of the inclined column (2), a sealing groove (2-3), a set of threaded holes (2-4) for installing the sealing plate and a set of threaded holes (2-5) for installing the cross beam are arranged in sequence from inside to outside, and a fluororubber strip is placed in the sealing groove (2-3); A sealing plate is arranged on the top surface of the inclined column (2), and a set of threaded holes (2-6) for installing the wind tunnel test model are arranged on the sealing plate.

4. The hypersonic wind tunnel test model support with active cooling according to claim 3, characterized in that, The sealing plate (3) on the rear end face of the inclined column (2) is fixed to the rear end face of the inclined column (2) by screws. The sealing plate (3) presses the fluororubber strip to seal the cooling water.

5. The hypersonic wind tunnel test model support with active cooling according to claim 4, characterized in that, A protruding wing plate (10-1) II is provided at the bottom of the tail cover (10). A set of through holes matching the threaded holes (1-4) for installing the tail cover on the bottom plate (1) are distributed on the wing plate (10-1) II. On the front end face of the tail cover (10), an inclined rib (10-3) is provided above. Threaded holes for fixing the rear skin (9) are provided on the inclined rib (10-3). On both sides of the tail cover (10), threaded holes for fixing the corresponding left cross beam (5) and right cross beam (6) are provided respectively. On the rear end face of the tail cover (10), an outlet hole (10-2) is provided.

6. Test method for a hypersonic wind tunnel test model support with active cooling, which is used for the hypersonic wind tunnel test model support with active cooling described in claim 5, characterized in that, It includes the following steps: S10. Install the inclined column (2); Align the through holes on the wing plate I (2-1) at the bottom of the inclined column (2) with the threaded holes (1-2) for installing the inclined column on the bottom plate (1), and fixedly connect them with a screw assembly. S20. Install the tail cover (10); Align the through holes on the wing plate II (10-1) at the bottom of the tail cover (10) with the threaded holes (1-4) for installing the tail cover on the bottom plate (1), and fixedly connect them with a screw assembly. S30. Install the sealing plate (3) on the inclined column (2); Place a rubber strip in the sealing groove (2-3) of the inclined column (2). Install the sealing plate (3) on the threaded holes (2-4) for installing the sealing plate on the rear end face of the inclined column (2) with a screw assembly, and press the fluororubber strip. S40. Install the left cross beam (5) and the right cross beam (6); Fix several left cross beams (5) on the left side of the rear end face of the inclined column (2) from top to bottom in sequence through the threaded holes (2-5) for installing the cross beam. Similarly, fix several right cross beams (6) on the right side of the rear end face of the inclined column (2) from top to bottom in sequence through the threaded holes (2-5) for installing the cross beam. S40. Install the skin; Cover the left skin (7) from top to bottom on the outer side of each left cross beam (5). Each left cross beam (5) and the left skin (7) are fixedly connected by a screw assembly. The lower end of the left skin (7) is fixedly connected to the threaded holes of the corresponding rib (1-3) on the bottom plate (1) by a screw assembly. Similarly, cover the right skin (8) from top to bottom on the outer side of each right cross beam (6). Each right cross beam (6) and the right skin (8) are also fixedly connected by a screw assembly. The lower end of the right skin (8) is fixedly connected to the threaded holes of the corresponding rib (1-3) on the bottom plate (1) by a screw assembly. Cover the rear skin (9) on the end face formed by the rear ends of the left cross beam (5) and the right cross beam (6) above the tail cover (10). Fix the rear skin (9) to the inclined rib (10-3) on the front end face of the tail cover (10) by a screw assembly. Cover the sealing plate (3) above the topmost left cross beam (5) and right cross beam (6). S50. Install the test model; Use a screw assembly to install the wind tunnel test model on the sealing plate above the inclined column (2) through the threaded holes (2-6) for installing the wind tunnel test model. S60. Install the bracket; Use a screw assembly to fix the bottom plate (1) of the bracket to the lower wall panel of the hypersonic wind tunnel test section through the through hole (1-1). Then, bundle up the measurement and control cables of the test model and pass them through the cavity formed by the left cross beam (5), the left skin (7), the right cross beam (6) and the right skin (8), and pull them out from the wire outlet hole (10-2) of the tail cover (10) and connect them to the measurement and control system of the hypersonic wind tunnel; S70. Conduct hypersonic wind tunnel tests; Before the hypersonic wind tunnel test, inject cooling water into the water inlet (4) and discharge the cooling water from the water outlet (11); during the hypersonic wind tunnel test, continuously carry out the intake and discharge of cooling water; after the hypersonic wind tunnel test is completed, continuously carry out the intake and discharge of cooling water within a pre-determined time period, and close the cooling water after reaching the pre-determined time.

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