Design method of water spraying diversion trench for rocket launching and test run

Abstract

The invention provides a design method of a water spray diversion trench for rocket launching and test run, which comprises the following steps: according to the requirements of rocket launching and test run, a water spray cooling water tank is attached to the upper surface of an inclined diversion trench foundation, and a plurality of water spray holes are formed in the upper surface of the water spray cooling water tank; carrying out fluid mechanics simulation analysis on the water spraying diversion trench, and simulating pressure distribution of water spraying holes when the tail flame is cooled by rocket launching and test run; the maximum pressure value of the simulation result is selected as an input condition, and water spraying holes with different numbers and different water flow intensities are formed in different positions of the water spraying cooling water tank. According to the design method, the temperature of the tail flame of the rocket can be effectively reduced under a low-cost construction scheme.

Description

Technical Field

[0001] This invention relates to the field of launch vehicle technology, specifically to a design method for a water jet guide channel used for rocket launch and testing. Background Art

[0002] The high-temperature, high-pressure exhaust gases generated during rocket engine hot-fire tests possess strong corrosive and impact forces, which existing launch sites typically employ dry-cooled exhaust channels to address. These channels are usually constructed from heavy cast iron blocks joined together, with steel pipes running through them forming a single integrated structure. However, in practical applications, it has been found that this type of channel is ill-suited to withstand the prolonged, high-intensity exhaust plume demands of frequent test launches in the commercial space industry. This could not only lead to project delays but also result in significant cost waste.

[0003] Therefore, there is an urgent need to design a water spray channel for rocket launches and tests that adds water spray functionality to the existing guide channel and is tailored to the rocket's exhaust plume. Summary of the Invention

[0004] The purpose of this invention is to overcome the shortcomings of the prior art and provide a design method for a water jet guide channel for rocket launch and testing.

[0005] This invention provides a design method for a water spray guide channel for rocket launch and test, comprising: according to the requirements of rocket launch and test, attaching a water spray cooling tank to the upper surface of an inclined guide channel, wherein multiple water spray holes are provided on the upper surface of the water spray cooling tank; performing fluid dynamics simulation analysis on the water spray guide channel to simulate the pressure distribution of the water spray holes when the rocket launches and tests cool the exhaust flame; selecting the maximum pressure value of the simulation result as the input condition, and setting different numbers of water spray holes with different water flow intensities at different positions of the water spray cooling tank.

[0006] According to an embodiment of the present invention, the step of performing fluid dynamics simulation analysis on the water spray guide channel includes: dividing the water spray cooling tank into three regions in the fluid dynamics simulation analysis, namely the core region, the peripheral region and the edge region.

[0007] According to an embodiment of the present invention, the pressure distribution step of the water jet holes during the simulated rocket launch and test includes: the water jet hole pressure in the core area is greater than the water jet hole pressure in the peripheral area, and the water jet pressure in the peripheral area is greater than the water jet hole pressure in the edge area.

[0008] According to one embodiment of the present invention, the water spray cooling tank is connected to the high-level water tank through a water supply pipeline, and the high-level water tank is used to supply water to the water spray cooling tank.

[0009] According to one embodiment of the present invention, the water supply pipeline includes a main pipeline and several branch pipelines connected to the main pipeline. The main pipeline is connected to an elevated water tank, and the several branch pipelines are all connected to a spray cooling water tank.

[0010] According to one embodiment of the present invention, the water spray cooling tank includes a bottom plate, a partition plate and a top plate, and a plurality of partition plates are spaced apart between the top plate and the bottom plate to divide the water spray cooling tank into a plurality of water storage spaces.

[0011] According to one embodiment of the present invention, through holes are provided on the baffle to ensure water flow in the spray cooling water tank. The baffle is arranged in a direction parallel to the branch pipe, and the baffle is arranged in a direction perpendicular to the branch pipe.

[0012] According to an embodiment of the present invention, the step of setting different numbers of water spray holes with different water flow intensities at different locations of the water spray cooling tank includes: the number density of water spray holes in the core area is greater than the number density of water spray holes in the surrounding area, and the number density of water spray holes in the surrounding area is greater than the number density of water spray holes in the edge area.

[0013] According to an embodiment of the present invention, the step of setting different numbers of spray holes with different water flow intensities at different positions of the spray cooling water tank includes: adjusting the cooling water flow rate by setting a baffle plate in the spray cooling water tank so that the water flow intensity in the core area is greater than the water flow intensity in the surrounding area, the water flow intensity in the surrounding area is greater than the water flow intensity in the edge area, and the larger the diameter of the spray hole, the greater the water flow intensity.

[0014] On the other hand, the present invention also provides a water jet guide channel for rocket launch and testing, which is designed using the above-mentioned design method for a water jet guide channel for rocket launch and testing.

[0015] This invention provides a design method for a water jet guide channel for rocket launch and testing. By designing a water jet cooling tank that matches the foundation of the guide channel, and designing water jet holes of different densities and numbers on the water jet cooling tank according to the rocket exhaust flame simulation, it can not only effectively cope with the long-term, high-intensity exhaust flame impact generated by multiple engine combinations, reducing the problems of extended project cycle and significantly increased cost caused by traditional guide channel solutions, but also indirectly achieve the purpose of noise reduction by changing the direction of the gas flow at the outlet of the guide channel through the guide surface of the water jet cooling tank.

[0016] It should be understood that the above general description and the following specific embodiments are merely exemplary and illustrative, and do not limit the scope of the invention. Attached Figure Description

[0017] The accompanying drawings, which are part of the specification of this invention, illustrate exemplary embodiments of the invention. The drawings, together with the description in the specification, serve to illustrate the principles of the invention.

[0018] Figure 1 This is a schematic diagram of a water jet guide channel design method for rocket launch and testing according to an embodiment of the present invention;

[0019] Figure 2 This is a side view of a water jet guide channel for rocket launch and testing according to an embodiment of the present invention;

[0020] Figure 3 This is a schematic diagram of the water supply pipeline for a water jet guide channel used in rocket launch and testing according to an embodiment of the present invention;

[0021] Figure 4 This is a front view of a water jet guide channel for rocket launch and testing according to an embodiment of the present invention;

[0022] Figure 5 This is a cross-sectional view of the water spray cooling tank in the water spray guide channel for rocket launch and test according to an embodiment of the present invention;

[0023] Figure 6 This is a simulation diagram of a water jet guide channel design method for rocket launch and testing according to an embodiment of the present invention;

[0024] Figure 7 This is a regional distribution diagram of the water spray cooling water tank of the water spray guide channel used for rocket launch and test firing according to an embodiment of the present invention.

[0025] Figure label:

[0026] 101-Guide channel foundation, 102-Spray cooling water tank, 103-Spray hole, 104-High-level water tank, 105-Water supply pipeline, 1051-Main pipeline, 1052-Branch pipeline, 106-Ablative concrete, 201-Main valve, 202-Filter, 203-Branch valve, 301-Base plate, 302-Partition plate, 303-Top plate, 304-Through hole. DETAILED DESCRIPTION

[0027] The features and exemplary embodiments of various aspects of the present invention will now be described in detail. To make the objectives, technical solutions, and advantages of the present invention clearer, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only configured to explain the present invention and to exemplify the principles of the present invention, and are not configured to limit the present invention. In addition, the structural components in the drawings are not necessarily drawn to scale. For example, the dimensions of some structural components or regions in the drawings may be enlarged for other structural components or regions to aid in the understanding of the embodiments of the present invention.

[0028] The directional terms used in the following description refer to the directions shown in the figures and are not intended to limit the specific structure of the embodiments of the present invention. In the description of the present invention, it should be noted that, unless otherwise stated, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in the present invention according to the specific circumstances.

[0029] Furthermore, the terms "comprising," "including," "having," or any other variations thereof are intended to cover non-exclusive inclusion, such that a structure or component that includes a list of elements includes not only those elements but also other structural elements that are not expressly listed or inherent to the structure or component. Without further limitations, an element defined by the phrase "comprising..." does not exclude the presence of other identical elements in the article or apparatus that includes the element.

[0030] Spatial relation terms such as "below," "under," "under," "low," "above," "on," and "high" are used for descriptive convenience to explain the positioning of one element relative to a second element, indicating that these terms are intended to cover different orientations of the device, in addition to those different from those shown in the figure. Furthermore, phrases such as "one element on / below another element" can indicate that two elements are in direct contact, or that there are other elements between the two elements. In addition, terms such as "first" and "second" are also used to describe individual elements, areas, parts, etc., and should not be considered limiting. Similar terms are used throughout the description to refer to similar elements.

[0031] It will be apparent to those skilled in the art that the present invention can be practiced without requiring some of these specific details. The following description of embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention.

[0032] Figure 1 This is a schematic diagram of a water jet guide channel design method for rocket launch and testing according to an embodiment of the present invention; Figure 2 This is a side view of a water jet guide channel for rocket launch and testing according to an embodiment of the present invention; Figure 3 This is a schematic diagram of the water supply pipeline for a water jet guide channel used in rocket launch and testing according to an embodiment of the present invention; Figure 4 This is a front view of a water jet guide channel for rocket launch and testing according to an embodiment of the present invention; Figure 5 This is a cross-sectional view of the water spray cooling tank in the water spray guide channel for rocket launch and test according to an embodiment of the present invention; Figure 6This is a simulation diagram of a water jet guide channel design method for rocket launch and testing according to an embodiment of the present invention; Figure 7 This is a regional distribution diagram of the water spray cooling water tank of the water spray guide channel used for rocket launch and test firing according to an embodiment of the present invention.

[0033] like Figure 1 and Figure 2 As shown, this invention provides a design method for a water jet guide channel for rocket launch and testing, comprising:

[0034] Step S100: According to the requirements of rocket launch and test, a water spray cooling tank 102 is attached to the upper surface of the inclined guide channel base 101, and multiple water spray holes 103 are provided on the upper surface of the water spray cooling tank 102.

[0035] Step S200: Perform fluid dynamics simulation analysis on the water spray guide channel to simulate the pressure distribution of the water spray hole 103 when the rocket launch and test run cools the exhaust flame.

[0036] Step S300: Select the maximum pressure value of the simulation result as the input condition, and set different numbers of water spray holes 103 with different water flow intensities at different positions of the water spray cooling water tank 102.

[0037] According to one embodiment of the present invention, the water spray cooling tank 102 is connected to the high-level water tank 104 through the water supply pipeline 105, and the high-level water tank 104 is used to supply water to the water spray cooling tank 102.

[0038] Specifically, the guide channel foundation 101 is designed according to the traditional dry guide channel standard, serving as the foundation of the launch site and the basis for the inclined guide channel profile. The elevated water tank 104 can be installed at a high level of the auxiliary service tower of the launch site, used for water storage and providing gravitational potential energy. Water is transported through the water supply pipeline 105 to the spray cooling water tank 102, which matches the guide channel foundation 101. The water is then evenly sprayed out through the spray holes 103 on the upper surface of the spray cooling water tank 102 to reduce the scouring force and corrosion of the high-temperature exhaust gas flow during rocket launch or test firing. Furthermore, the inclined spray cooling water tank 102 includes interconnected inclined sections, arc-shaped sections, and flat sections. The inclined section has a guide surface inclination angle of 27°, and the arc-shaped section smoothly connects the inclined section and the flat section through a circular arc structure. The water jet cooling tank 102 mainly releases cooling water through the water jet holes 103 on the inclined surface, which can smoothly adjust the direction of the jet tail flame, reduce the temperature of the rocket tail flame, prevent the tail flame from scouring the water jet guide channel, and avoid the sudden increase in local pressure caused by structural changes.

[0039] In this embodiment, simulation calculations are performed, for example, using ANSYS or ABAQUS software to conduct fluid dynamics simulation analysis on the water jet guide channel, simulating the vertical pressure on the guide surface of the water jet guide channel caused by the rocket's exhaust plume impacting the channel during launch and testing. Figure 6 As shown. In step S100, multiple spray holes can be uniformly arranged on the upper surface of the spray cooling water tank. After the rocket exhaust flame simulation analysis in step S200, some areas of the spray cooling water tank fail to meet the vertical pressure requirements of the guide surface. Therefore, in step S300, the maximum pressure value is used as the input condition to reset the spray holes in this area to meet the vertical pressure of the guide surface, including the density of the spray holes and the water flow intensity.

[0040] Correspondingly, the pressure distribution of the spray nozzles during cooling in the water jet guide channel also corresponds to the vertical pressure distribution on the guide surface. Next, the maximum pressure value from the simulation results was selected as the input condition. Different numbers of spray nozzles with varying flow intensities were set at different locations within the water jet cooling tank. High-density, high-flow-intensity spray nozzles were placed in areas of high pressure, while low-density, low-flow-intensity spray nozzles were placed in areas of low pressure. After multiple cooling tests, the water jet cooling tank 102, adapted to the guide channel foundation 101, demonstrated significant cooling effects in different areas, effectively reducing the rocket exhaust temperature.

[0041] In addressing the limitations of existing dry-cooled guide channel foundations 101 in meeting the requirements of frequent test launches in the commercial aerospace field, as well as the delays and high costs caused by prolonged and intense exhaust plume testing, this invention provides a novel water-jet guide channel design method that balances rocket launch and testing. The water-jet guide channel designed using this method combines the guide channel foundation 101 with a water-jet cooling tank 102, utilizing a complete water supply system consisting of a high-level water tank 104 and water supply pipelines 105. This effectively reduces the risk of heat and damage to the guide channel during rocket engine hot testing or launch, while simultaneously improving system cooling efficiency, extending the guide channel's service life, and solving the problem that traditional guide channels cannot withstand long-term high-temperature and high-pressure gas erosion.

[0042] In this embodiment, the water jet deflector for rocket launch and testing integrates the flame impact center of the existing launch deflector at the launch site into the water jet cooling tank 102 system. This allows the deflector's size and structure to meet the requirements for rocket first-stage propulsion system testing, rocket launch, and static ignition without significant changes. The water jet deflector has a relatively simple structure, low requirements for surrounding terrain, and a short construction period.

[0043] like Figure 7 As shown, according to an embodiment of the present invention, the steps of performing fluid dynamics simulation analysis on the water spray guide channel include: dividing the water spray cooling water tank 102 into three regions in the fluid dynamics simulation analysis, namely the core region, the peripheral region and the edge region.

[0044] According to an embodiment of the present invention, the step of simulating the pressure distribution of the water jets during rocket launch and test includes: the pressure of the water jets in the core area is greater than the pressure of the water jets in the peripheral area, and the water jet pressure in the peripheral area is greater than the pressure of the water jets in the edge area.

[0045] like Figure 3 and Figure 4 As shown, according to one embodiment of the present invention, the water supply pipeline 105 includes a main pipeline 1051 and a plurality of branch pipelines 1052 connected to the main pipeline 1051. The main pipeline 1051 is connected to a high-level water tank 104, and the plurality of branch pipelines 1052 are all connected to a spray cooling water tank 102.

[0046] like Figure 5 As shown, according to an embodiment of the present invention, the water spray cooling tank 102 includes a bottom plate 301, a partition plate 302 and a top plate 303. A plurality of partition plates 302 are spaced apart between the top plate 303 and the bottom plate 301 to divide the water spray cooling tank 102 into a plurality of water storage spaces.

[0047] According to one embodiment of the present invention, a through hole 304 is provided on the partition 302 to ensure that water flows in the spray cooling water tank 102. The arrangement direction of part of the partition 302 is parallel to the branch pipe 1052, and the arrangement direction of part of the partition 302 is perpendicular to the branch pipe 1052.

[0048] According to an embodiment of the present invention, the step of setting different numbers of water spray holes with different water flow intensities at different positions of the water spray cooling tank 102 includes: the number density of water spray holes in the core area is greater than the number density of water spray holes in the surrounding area, and the number density of water spray holes in the surrounding area is greater than the number density of water spray holes in the edge area.

[0049] According to an embodiment of the present invention, the step of setting different numbers of spray holes with different water flow intensities at different positions of the spray cooling water tank 102 includes: adjusting the cooling water flow rate by setting a baffle plate in the spray cooling water tank so that the water flow intensity in the core area is greater than the water flow intensity in the surrounding area, the water flow intensity in the surrounding area is greater than the water flow intensity in the edge area, and the larger the diameter of the spray hole, the greater the water flow intensity.

[0050] On the other hand, the present invention also provides a water jet guide channel for rocket launch and testing, which is designed using the above-mentioned design method for a water jet guide channel for rocket launch and testing.

[0051] Specifically, the water supply pipeline 105 connects the elevated water tank 104 and the spray cooling water tank 102 via the main pipeline 1051 and branch pipelines 1052. A main valve 201 is installed on the main pipeline 1051 for controlling the water flow from the main pipeline 1051. One end of the branch pipeline 1052 connects to the main pipeline 1051, and the other end connects to the spray cooling water tank 102. Each branch pipeline 1052 is equipped with a branch valve 203 to control the water pressure. The main pipeline 1051 and branch pipelines 1052 can be made of low-carbon steel pipes. The connection between the main pipeline 1051, branch pipelines 1052, and spray cooling water tank 102 is a flange connection, which is convenient to install and provides good sealing performance. The elevated water tank 104 can be placed on the upper level of the auxiliary service tower at the rocket launch site. It is constructed of atmospheric pressure stainless steel shaped water tank and is used for water storage and providing gravitational potential energy.

[0052] In one embodiment, the bottom plate 301, partitions 302, and top plate 303 of the water spray cooling tank 102 can be formed by welding steel plates. The water spray cooling tank 102 is mounted on the guide channel foundation 101 via the bottom plate 301. Water spray holes 103 evenly arranged on the top plate 303 cool the tank by spraying water into contact with the exhaust flame. Several partitions 302 are spaced between the top plate 303 and the bottom plate 301, dividing the water spray cooling tank 102 into several water storage spaces. Experimental data shows that this design can evenly distribute cooling water, improve cooling efficiency, and ensure cooling effect. As an example, the water spray cooling tank 102 has a width of 7 meters, a length of 15 meters, and a thickness of 0.3 meters. Furthermore, by optimizing the structural design of the water spray guide channel and employing specific materials and manufacturing processes, such as using a non-standard stainless steel water tank for water storage in the water spray cooling water tank 102 and selecting a water supply pipeline 105 made of low carbon steel, the present invention can further improve the corrosion resistance and operational reliability of the system, ensuring the safety and economy of the guide channel in frequent launch test scenarios.

[0053] Furthermore, each baffle 302 is uniformly provided with through holes 304 with a diameter of 120-180mm to ensure that cooling water can flow inside the spray cooling water tank 102. Some baffles 302 are arranged parallel to the branch pipe 1052, while others are arranged perpendicular to it. In one embodiment, the baffles 302 uniformly divide the flow guiding surface into multiple square regions. Experimental results show that this layout promotes water circulation, avoids stagnant water zones, and improves the utilization efficiency of cooling water.

[0054] In practical engineering, pre-installed anchor bolts or embedded parts can be pre-set on the upper surface of the guide channel foundation 101. Then, the water jet cooling tank 102 is welded and fixed to the pre-installed anchor bolts or embedded parts, thus welding the water jet cooling tank 102 onto the guide channel foundation 101. Finally, concrete is filled between the water jet cooling tank 102 and the guide channel foundation 101 for reinforcement, further securing the water jet cooling tank 102. The non-cooling tank covered portion of the guide channel foundation 101 is covered with ablation-resistant concrete 106 to ensure that the guide channel foundation 101 is not affected by the exhaust flame temperature. Experiments have shown that even under extreme conditions, the temperature of the guide channel foundation 101 can be maintained within a safe range. This fixing method ensures the sealing and strength of the overall structure of the water jet guide channel, effectively preventing the exhaust flame from penetrating the gaps and adversely affecting the rocket body during rocket launch or test runs, and ensuring that the water jet cooling tank 102 will not be overturned by the exhaust flame during rocket launch or test runs.

[0055] In one embodiment of this application, the Y-type filter 202 used on the main pipeline 1051 can effectively remove impurities from the water, preventing blockage of the outlet orifice and damage to the valve. The main valve 201 and branch valves 203 are pneumatic butterfly valves, which can precisely control the water flow, ensuring cooling effect while reducing system maintenance costs. This achieves effective protection of the guide channel, as well as reducing noise and improving safety, thus solving the problems in the prior art. In one embodiment, a pneumatic butterfly valve can be optionally connected in parallel on the main pipeline 1051 of the main valve 201, which can effectively balance the water pressure in the main pipeline 1051 and ensure the smooth pre-filling of the system.

[0056] During the simulation calculation, the cooling water flow rate of the spray cooling water tank is calculated according to the following formula.

[0057] q m ≥{[q+εσ(T f 4-T w0 4)]At-c w m w (T wf -T w0 )} / {[c c (373K-T C0 )+γ]t}

[0058] The meanings and values ​​of the parameters in the formula are as follows:

[0059] q m - Cooling water flow rate in the spray cooling tank; q - Peak heat flux near the center of the rocket tail; A - Outer wall area of ​​the spray cooling tank; ε - Emissivity, approximately 0.28 for carbon steel; σ - Blackbody radiation constant, approximately 5.67 × 10⁻⁶. -8 W / (m 2 K 4);T f - Gas temperature: Based on simulation results, the initial gas temperature is approximately 3000K, and the recovery temperature is approximately 3800K. The calculation uses the recovery temperature of 3800K as the reference value. w0 - Initial temperature of the water jet cooling tank wall, approximately 293K; t - Rocket engine test run time; c w -Specific heat of the water spray cooling tank material, taken as 0.5*10 3 J / kg℃;m w - The outer wall mass of the water spray cooling tank, with a density calculated based on carbon steel, is approximately 7.85*10. 3 Kg / m 3 ;T wf - Water spray cooling tank wall temperature (during testing), calculated based on the goal of the cooling water completely absorbing the heat from the exhaust flame, is taken as 393K; c c - Specific heat capacity of cooling water, taken as 4.2*10 3 J / Kg℃;T C0 - Initial cooling water temperature, approximately 293 K; γ-Latent heat of vaporization of water, approximately 2.1 × 10⁻⁶ at 0.55 MPa. 6 J / kg.

[0060] Based on fluid dynamics simulation analysis, the water spray cooling tank is divided into three regions: the core region, the peripheral region, and the edge region, as detailed below. Figure 7 As shown in the figure. According to the calculation, the core area of ​​Q needs ≥660.6kg / s; the surrounding area of ​​Q needs ≥210.54kg / s; the edge area of ​​Q needs ≥221.64kg / s; and the total water supply demand is ≥1092.78kg / s.

[0061] The pressure of the spray nozzles in different areas can be calculated using the following formula.

[0062]

[0063] Q - Cooling water flow rate of the spray nozzle; μ - Flow coefficient, which is related to the shape, size, roughness, and other factors of the spray nozzle and is generally determined experimentally; A - Cross-sectional area of ​​the spray nozzle; ΔP - Pressure of the spray nozzle.

[0064] Calculations show that the spray nozzle pressure in the core area is greater than that in the surrounding area, and the spray nozzle pressure in the surrounding area is greater than that in the edge area. For example, the calculated pressure in the rocket engine's cooling water tank is 0.769 MPa, the spray nozzle pressure in the core area is 0.45 MPa, the spray nozzle pressure in the surrounding area is 0.225 MPa, and the spray nozzle pressure in the edge area is 0.1 MPa.

[0065] Specifically, the number density of water jets in the core area is greater than that in the surrounding area, and the number density of water jets in the surrounding area is greater than that in the edge area. As one example, the core area is 43㎡ with a jet density of 108 jets / ㎡, the surrounding area is 23.5㎡ with a jet density of 52 jets / ㎡, and the edge area is 38.5㎡ with a jet density of 32 jets / ㎡.

[0066] The water jet cooling tank is equipped with horizontal baffles to adjust the diameter of the spray nozzles. A larger nozzle diameter results in a stronger water flow; the core area has a higher flow intensity than the surrounding area, and the surrounding area has a higher flow intensity than the edge area. The nozzle size is directly proportional to the flow velocity of the cooling water within it. A higher flow velocity allows for a larger nozzle size, while a lower flow velocity allows for a smaller nozzle size. This ensures that all the heat flux generated during rocket operation is absorbed, guaranteeing that the heat absorbed by the cooling medium in the nozzles equals the heat flux generated during rocket operation.

[0067] The water jet guide channel designed using the method described in this embodiment for rocket launch and test can meet the needs of commercial aerospace platforms for cost reduction, structural simplification, and coverage of multiple operating conditions. It can also comprehensively prevent high-temperature flames, smoke, and debris from reflecting back and impacting the test stand, as well as damaging engines and equipment, thus contributing to the rapid development of commercial aerospace.

[0068] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A design method for a water jet guide channel for rocket launch and testing, characterized in that, include: According to the requirements of rocket launch and test, a water spray cooling tank is attached to the upper surface of the inclined guide channel, and multiple water spray holes are provided on the upper surface of the water spray cooling tank. Fluid dynamics simulation analysis was performed on the water jet guide channel to simulate the pressure distribution of the water jet holes during rocket launch and test to cool the exhaust flame. The maximum pressure value from the simulation results was selected as the input condition, and spray holes with different numbers and water flow intensities were set at different locations in the water-spraying cooling water tank.

2. The design method for a water jet guide channel for rocket launch and testing according to claim 1, characterized in that, The steps for performing fluid dynamics simulation analysis on the water spray guide channel include: dividing the water spray cooling tank into three regions in the fluid dynamics simulation analysis, namely the core region, the peripheral region, and the edge region.

3. The design method for a water jet guide channel for rocket launch and testing according to claim 2, characterized in that, The pressure distribution steps of the water jet holes during the simulated rocket launch and test to cool the exhaust flame include: the water jet hole pressure in the core area is greater than the water jet hole pressure in the peripheral area, and the water jet pressure in the peripheral area is greater than the water jet hole pressure in the edge area.

4. The design method for a water jet guide channel for rocket launch and testing according to claim 3, characterized in that, The water spray cooling tank is connected to the elevated water tank via a water supply pipeline. The elevated water tank is used to supply water to the water spray cooling tank.

5. The design method for a water jet guide channel for rocket launch and testing according to claim 4, characterized in that, The water supply pipeline includes a main pipeline and several branch pipelines connected to the main pipeline. The main pipeline is connected to an elevated water tank, and the branch pipelines are all connected to a spray cooling water tank.

6. The design method for a water jet guide channel for rocket launch and testing according to claim 5, characterized in that, The water spray cooling tank includes a bottom plate, partitions, and a top plate. Several partitions are spaced between the top plate and the bottom plate to divide the water spray cooling tank into several water storage spaces.

7. The design method of the water jet guide channel for rocket launch and test firing according to claim 6, characterized in that, Through holes are provided on the baffles to ensure water flow within the spray cooling water tank. Some baffles are set parallel to the branch pipes, while others are set perpendicular to the branch pipes.

8. The design method for a water jet guide channel for rocket launch and testing according to claim 7, characterized in that, The step of setting different numbers of spray holes with different water flow intensities at different locations in the spray cooling water tank includes: making the number density of spray holes in the core area greater than that in the surrounding area, and the number density of spray holes in the surrounding area greater than that in the edge area.

9. The design method for a water jet guide channel for rocket launch and testing according to claim 7, characterized in that, The step of setting different numbers of spray holes with different water flow intensities at different locations in the spray cooling water tank includes: adjusting the cooling water flow rate by setting a baffle plate in the spray cooling water tank so that the water flow intensity in the core area is greater than that in the surrounding area, and the water flow intensity in the surrounding area is greater than that in the edge area, wherein the larger the diameter of the spray hole, the greater the water flow intensity.

10. A water jet guide channel for rocket launch and testing, characterized in that, The design adopts the water jet guide channel design method for rocket launch and test as described in any one of claims 1-9.

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