A large carrier rocket launch three-stage water spray cooling and noise reduction system
By designing a three-stage water spray system, a multi-layered water curtain is formed to suppress the ablation and noise of the gas flow at different stages of the large launch vehicle, solving the problem that the existing system cannot cope with the ablation of the gas flow and the expansion of noise, and achieving an effective cooling and noise reduction effect.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- BEIJING INST OF SPACE LAUNCH TECH
- Filing Date
- 2026-03-09
- Publication Date
- 2026-06-12
AI Technical Summary
Existing rocket launch water spray cooling and noise reduction systems cannot effectively address the problems of gas flow ablation and noise range expansion and superposition caused by the increased thrust of large launch vehicles during takeoff.
A three-stage water spray cooling and noise reduction system was designed, including primary, secondary and tertiary water spray subsystems, which form a multi-layer water curtain through guide hole nozzles, mushroom head nozzles and water spray pipes, respectively, to cover the gas flow at different stages and suppress ablation and noise.
It achieves effective cooling and noise reduction of gas flow at different stages, solves the problems of gas flow erosion and noise range expansion, and has a simple structure, low cost, convenient control, and safety and reliability.
Smart Images
Figure CN122192091A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to a rocket launch thermal protection technology, specifically a three-stage water spray cooling and noise reduction system for large launch vehicles. Background Technology
[0002] Launch vehicle launch water jet cooling and noise reduction systems have become standard equipment at launch sites, playing a comprehensive role in reducing the intensity of gas flow ablation, suppressing strong noise associated with gas flow, and eliminating pollutants associated with gas flow. With the development of the space industry, the demand for launch vehicle takeoff thrust is increasing. Currently, large launch vehicles with takeoff thrust exceeding 2000 tons are gradually being used. According to the rocket's working principle, takeoff thrust is directly proportional to the total displacement of the engine's gas flow; a significant increase in takeoff thrust will also increase the total displacement of the engine's gas flow. Under conditions of a significant increase in the total displacement of the gas flow, the impact and ablation effect of the gas flow on the launch pad and guide vanes, as well as the intensity of the accompanying gas flow noise, will increase accordingly. Launch vehicle launch water jet cooling and noise reduction systems need to address the gas flow ablation and noise suppression problems under these conditions of significantly increased launch vehicle size. The basic approach to solving this problem is to proportionally increase the launch vehicle launch water jet cooling and noise reduction system and the total water flow rate. Currently, limited by the development level of large-tonnage engines, the main development direction for increasing the takeoff thrust of large launch vehicles is to increase the number of engines. The increased number of engines leads to the expansion of multi-nozzle exhaust gases shortly after launch, affecting the launch pad structure and quickly covering the entire launch pad surface and even the surrounding area. This expanded impact results in increased ablation of the launch area, increased noise reflected from the launch pad surface and the launch site, and this increased noise is often superimposed on the noise reflected from the deflector outlet, further exacerbating the impact on launch control and safety. Existing rocket launch water jet cooling and noise reduction systems are no longer effective in addressing these issues. New control schemes need to be developed for large launch vehicle launch water jet cooling and noise reduction systems to address the problems of exhaust gas ablation and the expanding and superimposed effects of noise. Summary of the Invention
[0003] The purpose of this invention is to provide a three-stage water spray cooling and noise reduction system for large launch vehicles, which has the advantages of simple structure, low cost, convenient control, safety and reliability, and strong practicality.
[0004] To address the aforementioned technical problems in the existing technology, this invention provides a three-stage water spray cooling and noise reduction system for a large launch vehicle, comprising a first-stage water spray subsystem, a second-stage water spray subsystem, and a third-stage water spray subsystem. The first-stage water spray subsystem includes a guide hole water spray unit, a platform center water spray unit, and a platform periphery water spray unit. The guide hole water spray unit includes multiple guide hole nozzles arranged circumferentially on the inner wall of the guide hole. The platform center water spray unit includes multiple first mushroom-shaped nozzles arranged circumferentially on the launch platform. The platform periphery water spray unit includes multiple second mushroom-shaped nozzles arranged circumferentially on the launch platform. The guide hole nozzles, first mushroom-shaped nozzles, and second mushroom-shaped nozzles are respectively connected to the first-stage water spray pipe. The guide hole nozzles and second mushroom-shaped nozzles are offset from the first mushroom-shaped nozzles in both the lateral and longitudinal directions. The second-stage water spray subsystem… The system includes two secondary water spray devices corresponding to each other on both sides of the launch pad. Each secondary water spray device includes a secondary truss fixed on the launch pad and a secondary water spray pipe fixed on the secondary truss. A secondary water reservoir is provided at the upper end of the secondary water spray pipe. Multiple secondary nozzles are evenly distributed longitudinally on the secondary water reservoir. The secondary nozzles face the launch pad and are higher than the launch pad. The tertiary water spray subsystem includes multiple tertiary water spray devices. The multiple tertiary water spray devices are divided into two rows and evenly distributed longitudinally. The two rows of tertiary water spray devices are corresponding to each other on both sides of the launch pad. The distance from the tertiary water spray device to the launch pad is greater than the distance from the secondary water spray device to the launch pad. Each tertiary water spray device includes a tertiary truss fixed on the launch pad and a tertiary water spray pipe fixed on the tertiary truss. A tertiary nozzle is provided at the upper end of the tertiary water spray pipe. The tertiary nozzle faces the launch pad and is higher than the secondary water spray device.
[0005] Furthermore, the present invention provides a three-stage water spray cooling and noise reduction system for a large launch vehicle, wherein the first-stage, second-stage, and third-stage water spray pipes are respectively equipped with a first-stage water spray control valve, a second-stage water spray control valve, and a third-stage water spray control valve; the water spray nozzles of the guide hole nozzle, the first mushroom head nozzle, the second mushroom head nozzle, the second-stage nozzle, and the third-stage nozzle are all fan-shaped; and the first mushroom head nozzle and the second mushroom head nozzle each have four water spray nozzles that are evenly distributed circumferentially.
[0006] Furthermore, the present invention provides a three-stage water spray cooling and noise reduction system for a large launch vehicle, wherein the spatial arrangement and water spray diffusion angle of the guide hole nozzle, the first mushroom nozzle, and the second mushroom nozzle in the first-stage water spray subsystem are set according to formulas (1) to (5). (1) (2) (3) (4) (5) In formulas (1) to (5), The water spray diffusion angles of the first and second mushroom-shaped nozzles are given. The spray diffusion angle of the guide orifice nozzle. and These represent the lateral and longitudinal spans of the first mushroom-shaped nozzle relative to the guide hole nozzle, respectively. and These represent the lateral span and longitudinal span of the second mushroom nozzle relative to the first mushroom nozzle, respectively. The distance between adjacent guide orifice nozzles. This is the span coefficient, with a value ranging from 1.0 to 2.5.
[0007] Furthermore, in the present invention, a three-stage water spray cooling and noise reduction system for a large launch vehicle is provided, wherein the spatial arrangement of the guide orifice nozzles and the water spray diffusion angle in the first-stage water spray subsystem shall also satisfy formulas (6) to (8). (6) (7) (8) In formulas (6) to (8), The threshold value for the water spray diffusion angle of the guide orifice nozzle is 40°. o ~75 o , The water spray angle of the guide orifice nozzle. The threshold value for the water jet intervention angle of the guide orifice nozzle is 25°. o ~90 o , The height of the guide orifice nozzle relative to the launch pad surface or engine nozzle is... The height threshold of the guide orifice nozzle relative to the launch pad surface or engine nozzle is 0.05 to 0.50 meters.
[0008] Furthermore, the present invention provides a three-stage water-jet cooling and noise reduction system for a large launch vehicle, wherein the spacing between the second-stage nozzles in the second-stage water-jet subsystem is... Horizontal distance of the second-stage nozzle relative to the launch center and the water spray diffusion angle of the secondary nozzle It should satisfy formula (9). (9) In formula (9), This refers to the number of secondary nozzles in a single secondary water spray system. This refers to the longitudinal span of the launch pad.
[0009] Furthermore, the present invention provides a three-stage water-jet cooling and noise reduction system for a large launch vehicle, wherein the spacing between the second-stage nozzles in the second-stage water-jet subsystem is... and secondary water curtain leakage space gap It should also satisfy formula (10). (10) In formula (10), The minimum leakage threshold for a secondary water curtain is 0.2 to 1.0 meters.
[0010] Furthermore, the present invention provides a three-stage water-jet cooling and noise reduction system for a large launch vehicle, wherein the water jet velocity of the second-stage nozzle in the second-stage water-jet subsystem is... Horizontal distance of the second-stage nozzle relative to the launch center The height of the second-stage nozzle relative to the launch center Set according to formulas (11) and (12), (11) (12) In formulas (11) and (12), The density of water, It is the acceleration due to gravity. The water pressure of the secondary nozzle. This refers to the water spraying angle of the secondary nozzle.
[0011] Furthermore, the present invention provides a three-stage water-jet cooling and noise reduction system for a large launch vehicle, wherein the spacing between the three-stage water-jet devices in the three-stage water-jet subsystem is... Horizontal distance of the third-stage nozzle relative to the launch center The water spray diffusion angle of the three-stage nozzle Set it according to formula (13), (13) In formula (13), This is the span coefficient, with a value ranging from 1.1 to 2.0. This refers to the number of single-row, three-stage water spray devices.
[0012] Furthermore, the present invention provides a three-stage water-jet cooling and noise reduction system for a large launch vehicle, wherein the spacing between the three-stage water-jet devices in the three-stage water-jet subsystem is... and the three-stage water curtain leakage space gap It should satisfy formula (14). (14) In formula (14), The minimum leakage threshold for a three-stage water curtain is 1.0 to 2.5 meters.
[0013] Furthermore, the present invention provides a three-stage water-jet cooling and noise reduction system for a large launch vehicle, wherein the water jet velocity of the three-stage nozzles in the three-stage water-jet subsystem is... Horizontal distance of the third-stage nozzle relative to the launch center The height of the third-stage nozzle relative to the launch center Set according to formulas (15) and (16); the horizontal distance of the three-stage nozzle relative to the launch center The height of the third-stage nozzle relative to the launch center Horizontal distance of the second-stage nozzle relative to the launch center The height of the second-stage nozzle relative to the launch center It should satisfy formula (17). (15) (16) (17) In formulas (15) to (17), The water pressure of the three-stage sprinkler head. This refers to the water spraying angle of the three-stage sprinkler head.
[0014] Compared with existing technologies, the present invention provides a three-stage water spray cooling and noise reduction system for large launch vehicles, which has the following advantages: The present invention establishes a first-stage, second-stage, and third-stage water spray subsystem. The first-stage water spray subsystem includes a guide hole spray unit, a platform center spray unit, and a platform periphery spray unit. The guide hole spray unit has multiple guide hole nozzles distributed circumferentially on the inner wall of the guide hole. The platform center spray unit has multiple first mushroom-shaped nozzles distributed circumferentially on the launch platform. The platform periphery spray unit has multiple second mushroom-shaped nozzles distributed circumferentially on the launch platform. The guide hole nozzles, first mushroom-shaped nozzles, and second mushroom-shaped nozzles are connected to the first-stage water spray pipe, and the guide hole nozzles and second mushroom-shaped nozzles are staggered from the first mushroom-shaped nozzles in both the lateral and longitudinal directions. The second-stage water spray subsystem has two corresponding distribution... The secondary water spray system is located on both sides of the launch pad. Specifically, the secondary water spray system includes a secondary truss fixed to the launch pad and secondary water spray pipes fixed to the secondary truss. A secondary water reservoir is located at the upper end of the secondary water spray pipe, and multiple secondary nozzles are evenly distributed longitudinally on the secondary water reservoir. These secondary nozzles face the launch pad and are higher than the launch pad. The tertiary water spray subsystem is equipped with multiple tertiary water spray systems, arranged in two rows evenly distributed longitudinally. These two rows of tertiary water spray systems are positioned on both sides of the launch pad, with the distance from the tertiary water spray system to the launch pad greater than the distance from the secondary water spray system to the launch pad. The tertiary water spray system also includes a tertiary truss fixed to the launch pad and tertiary water spray pipes fixed to the tertiary truss. Tertiary nozzles are located at the upper end of the tertiary water spray pipes, facing the launch pad and higher than the secondary water spray system. This constitutes a simple, low-cost, easy-to-control, safe, reliable, and highly practical three-stage water jet cooling and noise reduction system for large launch vehicles. During the launch of a large launch vehicle, the first-stage, second-stage, and third-stage water jet subsystems are activated sequentially according to the control sequence. The platform protective water curtain formed by the first-stage water jet subsystem (first-stage water curtain) can suppress the ablation intensity and noise intensity of the exhaust gas flow during the rocket ignition stage and the initial stage of liftoff. The middle-layer protective water curtain formed by the second-stage water jet subsystem (second-stage water curtain) can suppress the ablation intensity and noise intensity when the exhaust gas flow is relatively concentrated and affects the space near the launch pad during the initial stage of liftoff. The high-level protective water curtain formed by the third-stage water jet subsystem (third-stage water curtain) can suppress the ablation intensity and noise intensity when the rocket reaches a certain height and the exhaust gas flow covers the entire launch pad surface and affects the nearby field space. This invention solves the problems of gas flow erosion and noise expansion and superposition effects caused by multi-nozzle gas flow by setting up a primary water spray subsystem, a secondary water spray subsystem, and a tertiary water spray subsystem, respectively undertaking the cooling and noise reduction of the gas flow at different stages of the launch process of a large carrier rocket.
[0015] The following detailed description of a three-stage water jet cooling and noise reduction system for a large launch vehicle, with reference to the accompanying drawings, illustrates the specific embodiments of the present invention. Attached Figure Description
[0016] Figure 1 This is a top view schematic diagram of a three-stage water jet cooling and noise reduction system for a large launch vehicle according to the present invention. Figure 2 This is a schematic diagram of the working state of a three-stage water spray cooling and noise reduction system for a large launch vehicle according to the present invention. Figure 3 This is a head-up view of the structure of a three-stage water jet cooling and noise reduction system for a large launch vehicle according to the present invention. Figure 4 This is a partial structural schematic diagram of a three-stage water jet cooling and noise reduction system for a large launch vehicle according to the present invention. Figure 5 This is a schematic diagram of the arrangement of the three-stage nozzles in this invention; Figure 6 This is a schematic diagram of the arrangement of the secondary nozzles in this invention; Figure 7 This is a schematic diagram showing the arrangement of the guide hole nozzle, the first mushroom head nozzle, and the second mushroom head nozzle in this invention; The components include: 1. Guide hole nozzle; 11. Guide hole water curtain; 2. First mushroom head nozzle; 21. Water curtain in the center area of the platform; 3. Second mushroom head nozzle; 31. Water curtain in the outer area of the platform; 4. Primary water spray pipe; 5. Secondary water spray device; 51. Secondary truss; 52. Secondary water spray pipe; 53. Secondary water reservoir; 54. Secondary nozzle; 55. Secondary water curtain; 6. Tertiary water spray device; 61. Tertiary truss; 62. Tertiary water spray pipe; 63. Tertiary nozzle; 64. Tertiary water curtain; 100. Launch pad; 200. Guide hole; 300. Launch pad; 301. Launch pad foundation; 400. Core stage rocket body; 401. Core stage engine nozzle; 500. Booster rocket body; 501. Booster engine nozzle. Detailed Implementation
[0017] First, it should be noted that the directional terms such as up, down, left, right, front, and back used in this invention are merely descriptions based on the accompanying drawings for ease of understanding, and are not intended to limit the technical solution or the scope of protection claimed in this invention.
[0018] like Figures 1 to 7The present invention illustrates a specific embodiment of a three-stage water spray cooling and noise reduction system for a large launch vehicle, comprising a first-stage water spray subsystem, a second-stage water spray subsystem, and a third-stage water spray subsystem. The first-stage water spray subsystem includes a guide hole spray unit, a platform center spray unit, and a platform periphery spray unit. The guide hole spray unit has multiple guide hole nozzles 1 arranged circumferentially on the inner wall of the guide hole 200. The platform center spray unit has multiple first mushroom-shaped nozzles 2 arranged circumferentially on the launch platform 100. The platform periphery spray unit has multiple second mushroom-shaped nozzles 3 arranged circumferentially on the launch platform 100. The guide hole nozzles 1, first mushroom-shaped nozzles 2, and second mushroom-shaped nozzles 3 are connected to the first-stage water spray pipe 4, and the guide hole nozzles 1 and second mushroom-shaped nozzles 3 are offset from the first mushroom-shaped nozzles 2 in both the lateral and longitudinal directions. The secondary water spray subsystem is equipped with two secondary water spray devices 5 correspondingly distributed on both sides of the launch pad 100. The secondary water spray device 5 is equipped with a secondary truss 51 fixed on the launch pad 300 and a secondary water spray pipe 52 fixed on the secondary truss 51. A secondary water storage tank 53 is installed at the upper end of the secondary water spray pipe 52, and multiple secondary nozzles 54 are evenly distributed longitudinally on the secondary water storage tank 53. The secondary nozzles 54 face the launch pad 100 and are higher than the launch pad 100. The three-stage water spray subsystem is equipped with multiple three-stage water spray devices 6, which are arranged in two rows and evenly distributed longitudinally. The two rows of three-stage water spray devices 6 are distributed on both sides of the launch pad 100. The distance from the three-stage water spray device 6 to the launch pad 100 is greater than the distance from the two-stage water spray device 5 to the launch pad 100. The three-stage water spray device 6 is equipped with a three-stage truss 61 fixed on the launch pad 300 and a three-stage water spray pipe 62 fixed on the three-stage truss 61. A three-stage nozzle 63 is installed at the upper end of the three-stage water spray pipe 62. The three-stage nozzle 63 faces the launch pad 100 and is higher than the two-stage water spray device 5.
[0019] The above configuration constitutes a simple, low-cost, easy-to-control, safe, reliable, and highly practical three-stage water jet cooling and noise reduction system for large launch vehicles. During the launch of a large launch vehicle, the first-stage, second-stage, and third-stage water jet subsystems are activated sequentially according to the control sequence. The platform protective water curtain formed by the first-stage water jet subsystem (first-stage water curtain) can suppress the ablation intensity and noise intensity of the exhaust gas flow during the rocket ignition stage and the initial liftoff phase. The intermediate protective water curtain formed by the second-stage water jet subsystem (second-stage water curtain) can suppress the ablation intensity and noise intensity when the exhaust gas flow is relatively concentrated and affects the space near the launch pad during the initial liftoff phase. The high-level protective water curtain formed by the third-stage water jet subsystem (third-stage water curtain) can suppress the ablation intensity and noise intensity when the rocket reaches a certain height and the exhaust gas flow covers the entire launch pad surface and affects the nearby field space. This invention solves the problems of gas flow erosion and noise expansion and superposition caused by multiple nozzles by setting up a primary, secondary, and tertiary water spray subsystem, which are respectively responsible for cooling and noise reduction of the gas flow at different stages of the launch process of large launch vehicles. By combining the three-stage water spray subsystem with independent three-stage water spray devices, this invention can better adapt to the water spray cooling and noise reduction requirements of rockets of different sizes launching from the same launch site. For example, if only the core stage of the rocket is being launched, the number of three-stage water spray devices can be appropriately reduced to decrease the area of the three-stage water curtain, improving the adaptability and flexibility of the system. It should be noted that, for ease of control in practical applications, this invention provides primary, secondary, and tertiary spray control valves on the primary spray pipe 4, secondary spray pipe 52, and tertiary spray pipe 62, respectively. Furthermore, the nozzles of the guide nozzle 1, the first mushroom-shaped nozzle 2, the second mushroom-shaped nozzle 3, the secondary nozzle 54, and the tertiary nozzle 63 all employ a fan-shaped structure to control the spray diffusion angle of each nozzle and improve water cooling and noise reduction. Specifically, the first mushroom-shaped nozzle 2 and the second mushroom-shaped nozzle 3 each have four nozzles evenly distributed circumferentially. However, it should be pointed out that the mushroom-shaped nozzle is an existing device in the art, and its structure is well known to those skilled in the art.
[0020] As an optimization scheme, due to the large area of the launch pad and the large area of the guide hole, the nozzle outlets of the booster rocket and core stage rocket engines are close to the guide hole. At the moment of launch and ignition of the large launch vehicle, the exhaust gas flows of many engines of the booster rocket and core stage rocket are discharged simultaneously. The exhaust gas flow velocity at the engine nozzle outlet generally exceeds 3000m / s, and the stagnation temperature exceeds 3500K. The first-stage water spray subsystem must ensure a sufficient flow of water spray to carry out efficient energy and momentum exchange with the high-temperature and high-speed exhaust gas flow, thereby reducing the ablation intensity and noise intensity of the exhaust gas flow. In order to cut off the noise propagation path to the rocket body during the rocket ignition stage and the initial stage of takeoff, this specific implementation scheme sets the spatial arrangement of the guide hole nozzle 1, the first mushroom head nozzle 2 and the second mushroom head nozzle 3 and the water spray diffusion angle according to the constraints of formulas (1) to (5). (1) (2) (3) (4) (5) In formulas (1) to (5), The water spray diffusion angle of the first mushroom nozzle 2 and the second mushroom nozzle 3. The water spray diffusion angle of nozzle 1 is the guide hole. and These represent the lateral and longitudinal spans of the first mushroom-shaped nozzle 2 relative to the guide hole nozzle 1, respectively. and These refer to the lateral span and longitudinal span of the second mushroom nozzle 3 relative to the first mushroom nozzle 2, respectively. The distance between adjacent guide nozzles 1 This is the span coefficient, with a value ranging from 1.0 to 2.5.
[0021] Meanwhile, this specific embodiment also ensures that the spatial arrangement of the guide nozzle 1 and the water spray diffusion angle satisfy the constraints of formulas (6) to (8). (6) (7) (8) In formulas (6) to (8), The threshold value for the water spray diffusion angle of nozzle 1 is 40°. o ~75 o , The water spraying angle of the guide orifice nozzle 1, The water spray intervention angle threshold for nozzle 1 of the guide hole is set to 25°.o ~90 o , The height of the guide nozzle 1 relative to the launch pad surface or engine nozzle is... The height threshold of the guide orifice nozzle 1 relative to the launch pad surface or engine nozzle is set to 0.05~0.50 meters. In practical applications, the water spray diffusion angle threshold, water spray intervention angle threshold, and height threshold of the guide orifice nozzle 1 should be specifically set according to the launch pad size and the scale of the launch vehicle.
[0022] Through the above structural design, the staggered water spraying of the guide hole nozzle 1, the first mushroom head nozzle 2, and the second mushroom head nozzle 3 is achieved, which can cut off the flow noise of the high temperature and high speed gas flow to the rocket body through the guide hole to the greatest extent, as well as the strong noise caused by the gas flow impacting the guide hole and the platform to the rocket body.
[0023] As an optimization scheme, during the launch test mission of a large carrier rocket, after the rocket takes off and leaves the launch pad at a certain height, the secondary water spray subsystem receives the action timing signal, and the secondary water spray control valve on the secondary water spray pipe 52 performs the opening action. High-pressure water quickly enters the secondary water storage tank 53 through the secondary water spray pipe 52 and is sprayed out through the secondary nozzle 54. The water jets from the nozzles of the two secondary water spray devices 5 quickly converge, forming a water curtain covering the launch pad surface and the space above the adjacent launch pad. The water curtains from the two secondary water spray devices 5 finally converge directly above the center of the launch pad, forming a larger water curtain covering the entire launch pad and enveloping the multi-nozzle exhaust flow of the large rocket during its initial launch phase—this is the secondary water curtain. The residual velocity of the water droplets within the secondary water curtain is relatively high. When the multi-nozzle exhaust flow from above the water curtain passes through the secondary water curtain, the energy and momentum of the exhaust flow are exchanged before reaching the launch pad surface and nearby equipment (such as the rocket support arm). The residual energy and momentum are insufficient to splash back through the secondary water curtain, thus enabling the secondary water curtain to achieve its technical objectives of reducing the ablation intensity and noise intensity of the exhaust flow and masking reflected noise. To ensure that the secondary water curtain can fully cover the launch pad surface and envelop the multi-nozzle exhaust flow during the initial launch phase of the rocket, thus guaranteeing its cooling and noise reduction effect, this specific embodiment adjusts the spacing of the secondary nozzles 54... Horizontal distance of the second-stage nozzle 54 relative to the launch center The water spray diffusion angle of the secondary nozzle 54 The constraints were set according to formula (9). (9) And adjust the spacing of the secondary nozzles 54. and secondary water curtain leakage space gap The constraints of formula (10) are satisfied. (10) In formula (9), The number of secondary nozzles 54 in a single secondary water spray device 5. This represents the longitudinal span of the launch pad, i.e., the longitudinal dimension of the launch pad. In formula (10), This is the minimum leakage threshold for the second-stage water curtain, ranging from 0.2 to 1.0 meters. In practical applications, the minimum leakage threshold for the second-stage water curtain should be specifically set according to the size of the launch pad and the scale of the launch vehicle.
[0024] Meanwhile, this specific embodiment also addresses the water spraying speed of the secondary nozzle 54. (Actual control of water spray pressure) Effective control was achieved, specifically, the water spray speed of the secondary nozzle 54 was controlled. Horizontal distance of the second-stage nozzle 54 relative to the launch center The height of the second-stage nozzle 54 relative to the launch center Set according to the constraints of formulas (11) and (12), (11) (12) In formulas (11) and (12), The density of water, It is the acceleration due to gravity. The water pressure of the secondary nozzle is 54. The water spraying angle of the secondary nozzle 54.
[0025] As an optimization scheme, during the launch test mission of a large carrier rocket, after the rocket takes off and leaves the launch pad at a certain height, the three-stage water spray subsystem receives the action timing signal, and the three-stage water spray control valves on each three-stage water spray pipe 62 are opened. High-pressure water flows rapidly upward through the three-stage water spray pipe 62 and is sprayed out through the three-stage nozzle 63. The water jets from the nozzles of each row of three-stage water spray devices 6 quickly converge, forming a water curtain covering the launch pad surface, the secondary water spray devices 5, and the space above the launch pad. The water curtains from the two rows of three-stage water spray devices 6 finally converge directly above the center of the launch pad, forming a larger water curtain covering the entire launch pad, the secondary water spray subsystem, and the space above the nearby launch pad—the three-stage water curtain. The residual velocity of the water droplets within the three-stage water curtain remains relatively high. When the gas flow from above the water curtain passes through the three-stage water curtain, energy and momentum are initially exchanged before reaching the launch pad surface, the secondary water spray system, and the launch pad near the launch pad. The residual energy and momentum are insufficient to splash back or pass through the three-stage water curtain, thus achieving the technical objectives of reducing the ablation intensity of the gas flow and the intensity of strong noise, and masking reflected noise. To ensure that the three-stage water spray subsystem can form a large-area three-stage water curtain to cover the entire launch pad, the secondary water spray subsystem, and the space above the nearby launch pad, this specific embodiment sets the spacing between the three-stage water spray devices 6... The horizontal distance of the third-stage nozzle 63 relative to the launch center The water spray diffusion angle of the three-stage nozzle is 63. The constraints were set according to formula (13), and the spacing of the three-stage water spray device 6 was adjusted. and the three-stage water curtain leakage space gap The constraints were set according to formula (14). (13) (14) In formula (13), This is the span coefficient, with a value ranging from 1.1 to 2.0. The number of single-row three-stage water spray devices 6; in formula (14), The minimum leakage threshold for the three-stage water curtain is set between 1.0 and 2.5 meters. In practical applications, the minimum leakage threshold for the three-stage water curtain should be specifically set according to the size of the launch pad and the scale of the launch vehicle.
[0026] Meanwhile, this specific embodiment also addresses the water spraying speed of the three-stage nozzle 63. (Actual control of water spray pressure) Effective control was achieved, specifically, the water spray speed of the three-stage sprinkler head 63 was controlled. The horizontal distance of the third-stage nozzle 63 relative to the launch center The height of the third-stage nozzle 63 relative to the launch center The settings are configured according to the constraints of formulas (15) and (16). The horizontal distance between the third-stage nozzle 63 and the launch center is also set. The height of the third-stage nozzle 63 relative to the launch center Horizontal distance of the second-stage nozzle 54 relative to the launch center The height of the second-stage nozzle 54 relative to the launch center The constraints of formula (17) are set so that the water curtain formed when the three-stage water spray subsystem is working can cover the two-stage water spray subsystem.
[0027] (15) (16) (17) In formulas (15) to (17), The water pressure of the three-stage sprinkler head is 63. The water spraying angle of the three-stage nozzle is 63.
[0028] The above embodiments are merely descriptions of preferred embodiments of the present invention and are not intended to limit the scope of protection of the present invention. Various modifications made by those skilled in the art based on the technical solutions of the present invention without departing from the design concept of the present invention should fall within the scope of protection defined by the claims of the present invention.
Claims
1. A three-stage water-jet cooling and noise reduction system for a large launch vehicle, characterized in that, The system includes a primary water spray subsystem, a secondary water spray subsystem, and a tertiary water spray subsystem. The primary water spray subsystem includes a guide hole water spray unit, a platform center water spray unit, and a platform periphery water spray unit. The guide hole water spray unit includes multiple guide hole nozzles (1) arranged on the inner wall of the guide hole and distributed circumferentially. The platform center water spray unit includes multiple first mushroom head nozzles (2) arranged on the launch platform and distributed circumferentially. The platform periphery water spray unit includes multiple second mushroom head nozzles (3) arranged on the launch platform and distributed circumferentially. The guide hole nozzles (1), first mushroom head nozzles (2), and second mushroom head nozzles (3) are respectively connected to the primary water spray pipe (4). The guide hole nozzles (1) and second mushroom head nozzles (3) are offset from the first mushroom head nozzles (2) in both the horizontal and vertical directions. The secondary water spray subsystem includes two secondary water spray devices (5) corresponding to the horizontal sides of the launch platform. The secondary water spray devices (5) include two nozzles fixed on the launch pad. The system comprises a primary truss (51) and a secondary water spray pipe (52) fixed on the secondary truss (51). A secondary water reservoir (53) is provided at the upper end of the secondary water spray pipe (52). Multiple secondary nozzles (54) are evenly distributed longitudinally on the secondary water reservoir (53). The secondary nozzles (54) face the launch pad and are higher than the launch pad. The tertiary water spray subsystem includes multiple tertiary water spray devices (6), which are arranged in two rows and evenly distributed longitudinally. The three-stage water spray device (6) is set on both sides of the launch pad. The distance from the three-stage water spray device (6) to the launch pad is greater than the distance from the two-stage water spray device (5) to the launch pad. The three-stage water spray device (6) includes a three-stage truss (61) fixed on the launch pad and a three-stage water spray pipe (62) fixed on the three-stage truss (61). The upper end of the three-stage water spray pipe (62) is provided with a three-stage nozzle (63). The three-stage nozzle (63) faces the launch pad and is higher than the two-stage water spray device (5).
2. The large launch vehicle launch three-stage water jet cooling and noise reduction system according to claim 1, characterized in that, The first-stage water spray pipe (4), the second-stage water spray pipe (52) and the third-stage water spray pipe (62) are respectively equipped with a first-stage water spray control valve, a second-stage water spray control valve and a third-stage water spray control valve. The water spray nozzles of the guide hole nozzle (1), the first mushroom head nozzle (2), the second mushroom head nozzle (3), the second-stage nozzle (54) and the third-stage nozzle (63) are all fan-shaped. The first mushroom head nozzle (2) and the second mushroom head nozzle (3) are respectively provided with four water spray nozzles and are evenly distributed along the circumference.
3. The large launch vehicle launch three-stage water jet cooling and noise reduction system according to claim 2, characterized in that, The spatial arrangement and spray diffusion angle of the guide hole nozzle (1), the first mushroom head nozzle (2), and the second mushroom head nozzle (3) in the primary water spray subsystem are set according to formulas (1) to (5). （1） （2） （3） （4） （5） In formulas (1) to (5), The water spray diffusion angle of the first mushroom nozzle (2) and the second mushroom nozzle (3) is... The spray diffusion angle of the guide orifice nozzle (1) is... and These are the lateral and longitudinal spans of the first mushroom-shaped nozzle (2) relative to the guide hole nozzle (1), respectively. and These are the lateral span and longitudinal span of the second mushroom nozzle (3) relative to the first mushroom nozzle (2), respectively. The distance between adjacent guide orifice nozzles (1) This is the span coefficient, with a value ranging from 1.0 to 2.
5.
4. The large launch vehicle launch three-stage water jet cooling and noise reduction system according to claim 3, characterized in that, The spatial arrangement of the guide nozzles (1) and the water spray diffusion angle in the primary water spray subsystem should also satisfy formulas (6) to (8). （6） （7） （8） In formulas (6) to (8), The water spray diffusion angle threshold of the guide orifice nozzle (1) is set to 40°. o ~75 o , The water spraying angle of the guide orifice nozzle (1) is... The water injection angle threshold for the guide orifice nozzle (1) is set to 25°. o ~90 o , The height of the guide nozzle (1) relative to the launch pad surface or engine nozzle is... The height threshold of the guide hole nozzle (1) relative to the launch pad or engine nozzle is 0.05~0.50 meters.
5. The large launch vehicle launch three-stage water jet cooling and noise reduction system according to claim 2, characterized in that, The spacing of the secondary nozzles (54) in the secondary water spray subsystem Horizontal distance of the secondary nozzle (54) relative to the launch center and the water spray diffusion angle of the secondary nozzle (54) It should satisfy formula (9). （9） In formula (9), The number of secondary nozzles (54) in a single secondary water spray device (5), This refers to the longitudinal span of the launch pad.
6. The large launch vehicle launch three-stage water jet cooling and noise reduction system according to claim 5, characterized in that, The spacing of the secondary nozzles (54) in the secondary water spray subsystem and secondary water curtain leakage space gap It should also satisfy formula (10). （10） In formula (10), The minimum leakage threshold for a secondary water curtain is 0.2 to 1.0 meters.
7. The large launch vehicle launch three-stage water jet cooling and noise reduction system according to claim 6, characterized in that, The water spray speed of the secondary nozzle (54) in the secondary water spray subsystem Horizontal distance of the secondary nozzle (54) relative to the launch center The height of the secondary nozzle (54) relative to the launch center Set according to formulas (11) and (12), （11） （12） In formulas (11) and (12), The density of water, It is the acceleration due to gravity. The water spray pressure of the secondary nozzle (54) is... The water spraying angle of the secondary nozzle (54).
8. The large launch vehicle launch three-stage water jet cooling and noise reduction system according to claim 2, characterized in that, The spacing between the three-stage water spray devices (6) in the three-stage water spray subsystem The horizontal distance between the third-stage nozzle (63) and the launch center The water spray diffusion angle of the three-stage nozzle (63) Set it according to formula (13), （13） In formula (13), This is the span coefficient, with a value ranging from 1.1 to 2.
0. The number of single-row three-stage water spray devices (6).
9. The large launch vehicle launch three-stage water jet cooling and noise reduction system according to claim 8, characterized in that, The spacing between the three-stage water spray devices (6) in the three-stage water spray subsystem and the three-stage water curtain leakage space gap It should satisfy formula (14). （14） In formula (14), The minimum leakage threshold for a three-stage water curtain is 1.0 to 2.5 meters.
10. The large launch vehicle launch three-stage water jet cooling and noise reduction system according to claim 9, characterized in that, The water spray speed of the three-stage nozzles (63) in the three-stage water spray subsystem The horizontal distance between the third-stage nozzle (63) and the launch center The height of the third-stage nozzle (63) relative to the launch center Set according to formulas (15) and (16); the horizontal distance of the three-stage nozzle (63) relative to the emission center The height of the third-stage nozzle (63) relative to the launch center Horizontal distance of the secondary nozzle (54) relative to the launch center The height of the secondary nozzle (54) relative to the launch center It should satisfy formula (17). （15） （16） （17） In formulas (15) to (17), The water pressure of the three-stage nozzle (63) is... The water spraying angle of the three-stage nozzle (63).