Solid rocket engine vertical test stand flow guide groove end exhaust structure

Abstract

This invention provides an exhaust structure at the end of a guide channel on a solid rocket motor upright test rig, comprising a guide channel body and a rectifier wall, longitudinal diaphragms, and transverse diaphragms disposed therein. The rectifier wall divides the horizontal section of the gas into three zones: left, middle, and right. The longitudinal diaphragms extend from the bend section to the vertical section, and the transverse diaphragms extend along the arc from the middle of the bend section to the vertical section, forming a nine-square grid structure within the bend and vertical sections. Each diaphragm has a conical steel structure at its flow-facing end, and the upper ends and sides of the transverse diaphragms are integrally cast and fixedly connected to the inner wall of the guide channel body. This structure combines gas rectification and deceleration, high-temperature particle interception, and structural support reinforcement functions, thereby improving exhaust safety and structural strength.

Description

Technical Field

[0001] This invention belongs to the field of solid rocket motor ground testing technology, specifically relating to an exhaust structure at the end of the guide channel of a solid rocket motor upright test rig. Background Technology

[0002] Compared to horizontal test rigs, upright solid rocket motor test rigs offer better vertical alignment, enabling the acquisition of more accurate key parameters such as thrust vector, main thrust eccentricity, and dynamic performance. They are a crucial means of evaluating the reliability and performance of solid rocket motors. The upright test rig is the only platform for achieving upright engine testing. The guide channel, as the core channel, directly determines the exhaust efficiency and test safety through its end exhaust structure, making it a critical component of the upright test rig.

[0003] Currently, there is some research on gas diversion and treatment devices for solid rocket engine ground tests. For example, Chinese patent application CN103406024A discloses a gas exhaust recovery and treatment device, which includes a flow-rectifying partition wall and a spray device installed in the gas diversion channel. The end of the channel is connected to a silencer tower. The diversion channel and the flow-rectifying partition wall are integral reinforced concrete structures, with steel plates covering the front and the partition wall. However, this solution is mainly used for exhaust gas environmental treatment, and its flow-rectifying partition wall has a relatively simple function. It does not consider the exhaust requirements of high-temperature gas under upright test conditions. Chinese patent CN105971769B proposes a small solid rocket engine upright test gas diverter, which uses a guide fluid with a combination of arc and straight lines to divert the gas from a vertical direction to a horizontal direction. Although this solution solves the problem of changing the gas direction, it focuses on the shape design of the guide fluid and does not involve the gas zoning of the exhaust section, deceleration, or strengthening of the exhaust channel structure.

[0004] In traditional upright test runs, engine combustion gases are diverted by a guide channel, becoming horizontal combustion gases that are then vertically discharged into the atmosphere. During this downward vertical impact, the combustion gases generate significant aerodynamic and thermal shocks to the guide channel. Furthermore, the high-temperature combustion gases within the channel, mixed with water vapor, create a typical two-phase flow. After being guided by the water-cooled guide channel, the combustion gases impact the exhaust section at high speed, generating substantial gas dynamic pressure. The highly concentrated high-temperature solid particles continuously erode the exhaust channel's baffles, severely impacting the channel's lifespan. The high-speed combustion gases can easily eject high-temperature clumps from the guide channel; if dispersed around the test bench, these clumps could easily ignite the surrounding environment, potentially causing wildfires and posing a safety hazard.

[0005] Existing exhaust structures typically employ a single channel or simple partition wall for flow guidance, which has the following shortcomings in practical applications: First, a single channel is insufficient for effectively distinguishing and slowing down high-speed combustion gases. The large flow rate and high temperature of the combustion gases generate significant aerodynamic impact and thermal load on the guide channel. Highly concentrated high-temperature solid particles continuously scour the exhaust channel wall, exacerbating wall wear, shortening the service life of the guide channel, and imposing high design requirements on structural strength. Second, high-speed combustion gases have complex compositions, often containing insufficiently cooled high-temperature clumps carried out of the guide channel with the combustion gas flow. These high-temperature clumps have a high degree of thermal energy accumulation, posing a risk of igniting the surrounding environment. Third, the combustion gases inside the guide channel are prone to turbulence due to abrupt changes in the cross-section of the exhaust channel, which can easily lead to congestion within the guide channel, reducing exhaust efficiency and affecting the safety and data validity of the test process. Summary of the Invention

[0006] To overcome the shortcomings of existing upright test bench exhaust structures in terms of bearing the dynamic pressure and thermal load of combustion gas, resisting the erosion of solid particles, preventing the carry-out of high-temperature lumps, and ensuring smooth exhaust flow, this invention provides an exhaust structure at the end of the exhaust channel of an upright solid rocket motor test bench. This structure decelerates and guides the horizontal high-speed combustion gas in sections, allowing the engine combustion gas to be discharged vertically upwards and evenly within the exhaust duct, while also providing structural support for the interior of the exhaust channel. By setting an interception net at the end of the exhaust duct, the aerodynamic load and thermal shock inside the exhaust channel can be further improved, enhancing the safety of combustion gas emissions from the upright test bench.

[0007] To achieve the above objectives, the technical solution provided by this invention is:

[0008] An exhaust structure at the end of a guide channel on a solid rocket motor upright test rig includes a guide channel body, which has a horizontal section, a bend section and a vertical section connected in sequence; two flow straightening walls are arranged at intervals along the longitudinal direction of the horizontal section, and the flow straightening walls divide the internal space of the horizontal section into three first partition channels arranged in the transverse direction of the horizontal section;

[0009] Two longitudinal partition walls are installed at intervals along the longitudinal direction of the vertical section within the bend section and the vertical section. The longitudinal partition walls divide the internal space of the bend section and the vertical section into three second partition channels arranged in the first transverse direction of the vertical section. The longitudinal partition walls and the flow straightening wall are aligned in the longitudinal direction of the horizontal section.

[0010] Two transverse partitions are installed at intervals along the longitudinal direction of the vertical section within the bend and vertical sections. These partitions divide the internal space of the bend and vertical sections into three third-division channels arranged in the second transverse direction of the vertical section. The transverse partitions extend along the curvature of the bend. The first transverse direction of the vertical section is perpendicular to the second transverse direction of the vertical section.

[0011] The longitudinal and transverse partitions are arranged intersectingly in the bend and vertical sections, dividing the internal space of the bend and vertical sections into nine independent exhaust channels, which are arranged in a three-row, three-column array.

[0012] Furthermore, the upper end of the longitudinal partition wall extends to the exhaust port end face of the vertical section, and the lower end extends to the bottom of the vertical section; the lower end and both sides of the longitudinal partition wall are fixedly connected to the inner wall of the guide channel body; the flow-facing end of the longitudinal partition wall starts from the inlet area of ​​the bend section.

[0013] Furthermore, the upper end of the transverse partition extends to the exhaust port end face of the vertical section; the two sides of the transverse partition are fixedly connected to the inner walls of the two sides of the main body of the guide channel; the flow-facing end of the transverse partition starts after the junction of the bend section and the horizontal section, and extends along the arc of the bend section, in a suspended state.

[0014] Furthermore, the flow-facing ends of the rectifier wall, longitudinal diaphragm wall, and transverse diaphragm wall are all equipped with cone-shaped flow-guiding structures.

[0015] Furthermore, the longitudinal and transverse diaphragm walls are integrally cast at their intersections in the curved and vertical sections.

[0016] Furthermore, the interior of the rectifier wall, longitudinal partition wall, and transverse partition wall is equipped with a steel reinforcement skeleton, which is connected to the steel reinforcement skeleton of the main body of the guide channel.

[0017] Furthermore, the end of the rectifier wall terminates before the inlet of the bend section, and the upstream end of the longitudinal diaphragm wall begins at the inlet area of ​​the bend section. The rectifier wall and the longitudinal diaphragm wall are aligned longitudinally in the horizontal section, and the rectifier wall and the longitudinal diaphragm wall are spatially separated and do not contact each other.

[0018] Furthermore, the outlet ends of the nine independent exhaust channels are equipped with connection structures for installing interception nets.

[0019] The advantages of this invention are:

[0020] 1. To address the issue of the main structure of the flow channel bearing significant dynamic pressure and thermal load under high-speed gas impact, traditional solutions involve increasing the wall thickness of the flow channel, adding external support structures, or covering the exterior with soil. These methods result in high structural design costs. In contrast, this invention employs a nine-grid structure formed by combining longitudinal and transverse partitions in the exhaust channel of the flow channel. Each partition is rigidly connected to the main body of the flow channel, forming an integrated load-bearing structure. This disperses the concentrated impact load of the gas to multiple partitions, effectively enhancing the rigidity and stability of the flow channel, extending its service life, and reducing structural costs by approximately 50% compared to traditional methods.

[0021] 2. The present invention provides a steel structure protective layer with a cone angle at the flow-facing end of each partition wall, which guides the impact of high-temperature and high-speed gas and solid particles to the erosion-resistant steel structure surface, reducing direct wear on the reinforced concrete main structure and lowering the maintenance frequency.

[0022] 3. This invention uses a nine-grid partitioned channel to collect high-temperature solid particles in the gas, causing high-temperature particles to deposit or slow down inside the channel, making them less likely to be directly discharged from the exhaust port with the high-speed airflow, thus reducing the risk of igniting the surrounding environment and improving the safety of gas emissions.

[0023] 4. This invention achieves continuous zoned flow guidance of gas from the horizontal section to the vertical section by aligning the flow straightening wall with the vertical section longitudinal partition wall. The gas flow is further subdivided by the transverse partition wall, and each channel exhausts independently. This helps to improve the uniformity of the flow field, and it is not easy to generate large eddies during exhaust. Even if the streamlines in the incoming flow direction are turbulent, it can still achieve a good flow straightening effect, and the exhaust smoothness is guaranteed to a certain extent, thus improving the exhaust efficiency.

[0024] 5. To address the issue that a single exhaust port channel is not conducive to functional expansion, the nine-grid structure formed by this invention provides nine independent channels on the exhaust port end face. Compared with a single large channel, it is convenient to add additional devices such as interception nets to each channel outlet individually or as a whole as needed, which facilitates further interception of flying objects or reduction of exhaust section height. Attached Figure Description

[0025] The above and / or additional aspects and advantages of the present invention will become apparent and readily understood from the description of the embodiments taken in conjunction with the following drawings, in which:

[0026] Figure 1 This is an overall diagram containing the exhaust channel structure at the end of the guide groove of the present invention;

[0027] Figure 2 It is along Figure 1 A vertical three-dimensional sectional view of the center;

[0028] Figure 3 yes Figure 2 Longitudinal sectional plan view;

[0029] Figure 4 yes Figure 2 Top view of the cross section of AA;

[0030] Figure 5 yes Figure 2 Side view of the vertical section of BB;

[0031] Figure 6 yes Figure 2 Side view of the vertical section of the CC section;

[0032] Figure 7This is a schematic diagram of adding an interception net to an independent channel in this invention.

[0033] In the diagram: 1-main body of the flow guide channel, 2-first transverse partition wall, 3-second transverse partition wall, 4-rectifying wall, 5-first longitudinal partition wall, 6-second longitudinal partition wall, 7-interception net. Detailed Implementation

[0034] The embodiments of the present invention are described in detail below. These embodiments are exemplary and intended to explain the present invention, and should not be construed as limiting the present invention.

[0035] Reference Figures 1-3 This invention provides an exhaust structure at the end of a guide channel on a solid rocket motor upright test rig, comprising a guide channel body 1, a first transverse partition wall 2, a second transverse partition wall 3, a flow straightening wall 4, a first longitudinal partition wall 5, and a second longitudinal partition wall 6. The guide channel of the guide channel body includes a horizontal section, a curved section, and a vertical section connected in sequence. The flow straightening wall and each partition wall are located inside the guide channel body 1. All the above structural components are integrally cast with reinforced concrete to ensure the overall stability and load-bearing capacity of the structure. The guide channel body 1 serves as the outer shell of the entire exhaust structure. Its ventilation cross-sectional dimensions are determined based on the engine's gas flow rate and temperature parameters, combined with two-phase flow simulation calculations after cooling water spraying. The basic design principle is to ensure that the gas does not become congested within the guide channel. The dimensions and wall thickness of the guide channel body also need to be determined based on the actual conditions of the test rig site and the calculation results of gas impact dynamic pressure and thermal load to meet structural strength and service life requirements.

[0036] See Figures 2-5 Two rectifier walls 4 are arranged at intervals within the horizontal section of the flow guide channel, extending longitudinally (i.e., in the direction of gas flow). The two rectifier walls 4 divide the horizontal section into three independent first-zone channels laterally (i.e., in the width direction of the horizontal section). The main body of the rectifier wall 4 is a reinforced concrete structure with an internal steel frame. Its flow-facing end (i.e., the wall facing the direction of gas flow) is equipped with a steel structure protective layer with a conical angle. This steel structure protective layer is fixedly connected to the concrete wall of the rectifier wall by bolts. Its conical angle is determined based on streamline simulation results to reduce interference with the gas flow lines. Simultaneously, the erosion resistance of the steel structure resists the wear of high-temperature solid particles, increasing the structural strength of the horizontal section of the flow guide channel.

[0037] See Figure 2 , Figure 4 and Figure 6The first longitudinal partition wall 5 and the second longitudinal partition wall 6 are spaced apart within the bend and vertical sections of the exhaust channel of the guide trough, extending longitudinally along the vertical section (i.e., the direction of gas flow). Specifically, the upper ends of the first longitudinal partition wall 5 and the second longitudinal partition wall 6 extend to the exhaust port of the vertical section, and the lower ends extend to the bottom of the vertical section; the lower ends and side walls of the two longitudinal partition walls are fixedly connected to the inner wall of the guide trough body by integral casting of reinforced concrete, forming a wall structure supported at both the lower end and the sides. The longitudinal partition walls divide the bend and vertical sections into three independent second-zone channels along the first transverse direction of the vertical section. Figure 2 It can be seen that the projection positions of the first longitudinal partition wall 5 and the second longitudinal partition wall 6 on the horizontal plane are aligned with the arrangement position of the flow straightener 4 in the longitudinal direction of the horizontal section. This ensures that the gas flow remains continuous when entering the vertical section from the horizontal section, avoiding abrupt changes in the streamline that could generate additional eddies. In this embodiment, the longitudinal partition walls are aligned with the flow straightener 4 but do not contact each other. This is to balance the flow field in each region within the main flow guiding body and to facilitate construction and maintenance. The main body of the two longitudinal partition walls is a reinforced concrete structure. The flow-facing end (i.e., the sidewall aligned with the flow straightener) is provided with a steel structure protective layer with a cone angle. This is also used to reduce interference with the gas flow trajectory streamline, while relying on the erosion resistance of the steel structure to resist the wear of high-temperature solid particles and increase the structural strength of the longitudinal partition walls.

[0038] See Figure 2 , Figure 4 and Figure 6 The first transverse partition 2 and the second transverse partition 3 are arranged within the bend section and the vertical section, along the longitudinal direction of the vertical section (i.e., the direction of gas flow). The flow-facing ends of the first transverse partition 2 and the second transverse partition 3 begin at the junction of the bend section and the horizontal section of the guide channel. Their walls extend along the arc of the inner wall of the bend section. After turning at the bend section, they enter the vertical section of the guide channel and are arranged in a vertically layered manner. This cuts the bend section and the vertical section channel into three independent third-zone channels in the second transverse direction of the vertical section. The first transverse direction and the second transverse direction of the vertical section are two mutually perpendicular directions. As the first transverse diaphragm 2 and the second transverse diaphragm 3 extend along the curvature of the bend section, they begin to guide the gas flow in layers during the turning process within the bend section. The first transverse diaphragm 2 and the second transverse diaphragm 3 are spatially perpendicular to the first longitudinal diaphragm 5 and the second longitudinal diaphragm 6 within the bend section and the vertical section. Within the bend section, the first longitudinal diaphragm 5 and the second longitudinal diaphragm 6 are longitudinally divided along the vertical section, while the first transverse diaphragm 2 and the second transverse diaphragm 3 are divided along the curvature direction, together forming a continuous zoned guiding structure within the range from the bend to the vertical section. Ultimately, a complete nine-square grid configuration is formed within the vertical section of the guide channel. The main body of the transverse diaphragm is a reinforced concrete structure, with a high-temperature resistant and erosion-resistant protective layer on its flow-facing surface. In this embodiment, a steel structure protective layer with a tapered angle is preferred, which improves the heat resistance and erosion resistance of the horizontal section of the guide channel on the one hand, and rectifies the gas flow on the other.

[0039] Specifically, the upper ends of the first transverse partition wall 2 and the second transverse partition wall 3 also extend to the outlet end (i.e., the exhaust port end), and the outer sides on both sides are fixedly connected to the front and rear inner walls of the main body 1 of the guide channel by integral casting of reinforced concrete. The bend section below the first transverse partition wall 2 and the second transverse partition wall 3 starts in the middle or starting area of ​​the bend section of the guide channel and extends along the curvature of the bend. The windward end of this bend section does not directly contact the outer wall of the bend section of the main body 1 and the end of the straightening wall 4, and is in a suspended state. Similarly, a steel structure protective layer with a cone angle is set at the windward end of the bend section. The first longitudinal partition wall 5, the second longitudinal partition wall 6, the first transverse partition wall 2, and the second transverse partition wall 3 are rigidly connected at the spatial intersection nodes in the bend section and the vertical section of the guide channel by integral casting to ensure the continuity and integrity of the concrete structure. Since the upper ends of the first longitudinal partition wall 5 and the second longitudinal partition wall 6, as well as the first transverse partition wall 2 and the second transverse partition wall 3, all extend to the exhaust port end face, they ultimately form a structure in the vertical section as follows: Figure 5 The diagram shows a 3x3 grid layout.

[0040] The thickness and spacing of the aforementioned partition walls, as well as the cross-sectional area of ​​each cell in the nine-square grid channel, need to be calculated and determined based on engine parameters such as engine combustion gas flow rate, exhaust velocity, and cooling water spray volume. As an example, for a certain type of solid rocket motor upright test bench, the cross-sectional area of ​​its exhaust channel in the guide groove is approximately 270. The thickness of each partition wall in the nine-grid structure is approximately 500mm. The cross-section of a single channel is a rectangle with dimensions of approximately 5m x 6m, but this can be adjusted based on the flow field and load distribution. If the load exceeds the strength of the partition wall structure, it can be designed as a 16-grid, 25-grid, or 36-grid structure with cross-sectional dimensions of 4*4, 5*5, or 6*6. The cone angle of the steel structure facing the airflow should not exceed 30°; the smaller the angle, the better. This implementation uses a 30° angle, with a cone apex rounded by R50mm. It should be noted that the above numerical ranges or values ​​are exemplary; the actual design should be based on specific engine parameters and simulation calculation results.

[0041] All partition walls and the main body 1 of the guide channel, as well as the joints between the partition walls, are rigidly connected by integral cast-in-place reinforced concrete. Reinforcing ribs are installed at the joints to improve the overall structural integrity and impact resistance, ensuring that no cracking or damage occurs under high-speed gas impact and thermal stress. It should be noted that the nine-grid structure referred to in this invention refers to a spatial configuration of nine independent exhaust channels formed by the intersection of two longitudinal partition walls and two transverse partition walls within the vertical and curved sections of the guide channel. The cross-sectional areas of each channel can be equal, or unequal depending on the distribution characteristics of the gas flow rate in the horizontal and vertical directions of the vertical section. Those skilled in the art can flexibly adjust the proportional relationships of each channel based on simulation results.

[0042] To further improve exhaust safety, such as Figure 7As shown, in this embodiment, interception nets are installed at the outlets of each independent channel on the exhaust port end face to intercept large-sized high-temperature blocks. The interception nets are fixed by a connecting structure pre-installed on the inner wall of the channel. This connecting structure can be a slot and snap-fit ​​structure, or the interception net can be fixed to the corresponding independent channel outlet in the following way: a thick steel plate is pre-embedded at the end of the exhaust port, an opening matching the channel opening is made on the thick steel plate, and threaded mounting holes are made around the steel plate. The threaded holes are treated for corrosion resistance. An interception net matching the opening on the steel plate is prepared, and the interception net is fixedly connected to the steel plate around the perimeter using threaded fasteners. Preferably, the interception net is treated for corrosion resistance. The mesh diameter of the protective net can be designed according to actual needs. In this embodiment, the steel plate thickness is 30mm, and the mesh size is 50mm × 50mm.

[0043] The working principle of this invention is as follows:

[0044] In the upright test, the high-temperature, high-speed combustion gas generated by the solid rocket motor impacts the bottom of the guide channel vertically downwards. After being cooled by water, it flows backwards along the horizontal section of the guide channel. The combustion gas first passes through the straightener wall 4, where it is cut into three independent airflows—left, center, and right—before entering the vertical section of the guide channel. After entering the vertical section, the three gas flow streams maintain zoned flow under the guidance of the first longitudinal partition wall 5 and the second longitudinal partition wall 6, and are further divided into three sub-regions by the first transverse partition wall 2 and the second transverse partition wall 3. Through the combined action of the aforementioned longitudinal and transverse partition walls, the combustion gas is divided into nine independent channels throughout the exhaust section.

[0045] As the gas flows through the nine-grid channel, its velocity decreases due to the division and expansion of the channel's cross-sectional area, reducing noise. Simultaneously, each partition wall intercepts and collects high-temperature solid particles in the gas, minimizing their high-speed emission with the airflow. Finally, guided by the nine-grid channel, the gas changes from a horizontal to a vertical direction and is discharged into the atmosphere through the exhaust port.

[0046] In this process, the partition wall structure plays multiple roles. On the one hand, it rectifies and guides the gas flow to improve the uniformity of the gas flow field. On the other hand, as a supporting frame, it shares the dynamic and thermal loads brought by the impact of high temperature and high pressure gas with the main body of the guide channel, which significantly improves the safety and reliability of the exhaust structure.

[0047] It should be further explained that under the high-speed impact of engine combustion gases, the side walls, transverse diaphragms, and longitudinal diaphragms of the main body 1 of the guide channel all bear the dynamic pressure load of the high-pressure, high-temperature combustion gases. This load is transferred to the first longitudinal diaphragm 5 and the second longitudinal diaphragm 6, where it is borne by the longitudinal diaphragm in a planar force distribution manner and transmitted vertically upwards. At the same time, the first transverse diaphragm 2 and the second transverse diaphragm 3 exert a restraining and dispersing effect on the pressure pulsation of the high-temperature combustion gas flow in the vertical direction, reducing the lifting force on the top structure. The longitudinal and transverse diaphragms form a spatial force-bearing structure at their intersection nodes, thereby enhancing the overall stiffness of the exhaust section structure in the longitudinal, transverse, and vertical directions.

[0048] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any person skilled in the art can easily conceive of various equivalent modifications or substitutions within the scope of the technology disclosed in the present invention, and such modifications or substitutions should all be covered within the scope of protection of the present invention.

Claims

1. An exhaust structure at the end of a guide channel on a solid rocket motor upright test rig, comprising a guide channel body, wherein the guide channel body has a horizontal section, a curved section, and a vertical section connected in sequence, characterized in that: Two rectifier walls are arranged at longitudinal intervals within the horizontal segment, and the rectifier walls divide the internal space of the horizontal segment into three first partition channels arranged in the transverse direction of the horizontal segment. Two longitudinal partition walls are provided at intervals along the longitudinal direction of the vertical section within the bent pipe section and the vertical section. The longitudinal partition walls divide the internal space of the bent pipe section and the vertical section into three second partition channels arranged in the first transverse direction of the vertical section. The longitudinal partition walls and the flow rectifier wall are aligned in the longitudinal direction of the horizontal section. The curved section and the vertical section are provided with two transverse partitions spaced at intervals along the longitudinal direction of the vertical section. The transverse partitions divide the internal space of the curved section and the vertical section into three third partition channels arranged in the second transverse direction of the vertical section. The transverse partitions extend along the curvature of the curved section. The first transverse direction of the vertical section is perpendicular to the second transverse direction of the vertical section. The longitudinal partition wall and the transverse partition wall are arranged intersectingly in the bend section and the vertical section, dividing the internal space of the bend section and the vertical section into nine independent exhaust channels, which are arranged in a three-row, three-column array.

2. The exhaust structure at the end of the guide channel of the solid rocket motor upright test rig according to claim 1, characterized in that: The upper end of the longitudinal partition wall extends to the exhaust port end face of the vertical section, and the lower end extends to the bottom of the vertical section; the lower end and both sides of the longitudinal partition wall are fixedly connected to the inner wall of the guide channel body; the flow-facing end of the longitudinal partition wall starts at the inlet area of ​​the bend section.

3. The exhaust structure at the end of the guide channel of the solid rocket motor upright test rig according to claim 1, characterized in that: The upper end of the transverse partition extends to the exhaust port end face of the vertical section; the two sides of the transverse partition are respectively fixedly connected to the inner walls of the two sides of the main body of the guide channel; the flow-facing end of the transverse partition starts after the junction of the bend section and the horizontal section, and extends along the arc of the bend section, in a suspended state.

4. The exhaust structure at the end of the guide channel of a solid rocket motor upright test rig according to claim 2 or 3, characterized in that: The flow-facing ends of the rectifier wall, longitudinal diaphragm wall, and transverse diaphragm wall are all equipped with cone-shaped flow-guiding structures.

5. The exhaust structure at the end of the guide channel of the solid rocket motor upright test rig according to claim 2, characterized in that: The longitudinal diaphragm and the transverse diaphragm are integrally cast at their intersection points in the curved and vertical sections.

6. The exhaust structure at the end of the guide channel of the solid rocket motor upright test rig according to claim 5, characterized in that: The interior of the rectifier wall, longitudinal partition wall and transverse partition wall are all equipped with steel reinforcement skeletons, which are connected to the steel reinforcement skeleton of the main body of the guide channel as a whole.

7. The exhaust structure at the end of the guide channel of the solid rocket motor upright test rig according to claim 1, characterized in that: The end of the rectifier wall terminates before the inlet of the bend section, and the upstream end of the longitudinal diaphragm wall begins at the inlet area of ​​the bend section. The rectifier wall and the longitudinal diaphragm wall are aligned longitudinally in the horizontal section, and the rectifier wall and the longitudinal diaphragm wall are spatially separated and do not contact each other.

8. The exhaust structure at the end of the guide channel of the solid rocket motor upright test rig according to claim 1, characterized in that: The outlet ends of the nine independent exhaust channels are equipped with connection structures for installing interception nets.

Images