Rocket launching extrusion type water spray cooling and noise reduction system

Abstract

The present application relates to a kind of rocket launch extrusion type water spray cooling noise reduction system, including launching platform water spray subsystem and guide groove water spray subsystem, launching platform water spray subsystem includes first gas tank, first water tank and first end water spray device, first water tank is communicated with first gas tank, first water tank is connected with first water spray main pipe and first water spray main control valve, first end water spray device is equipped with two and is respectively connected with first water spray main pipe by first water spray dry pipe, first water spray dry pipe is equipped with first water spray sub-control valve, guide groove water spray subsystem includes second gas tank, second water tank and second end water spray device, second water tank is communicated with second gas tank, second water tank is connected with second water spray main pipe and second water spray main control valve, second end water spray device is equipped with two and is respectively connected with second water spray main pipe by second water spray dry pipe, second water spray dry pipe is equipped with second water spray sub-control valve.It has the advantages of simple structure, easy to adjust, safe and reliable.

Description

Technical Field

[0001] This invention relates to a thermal protection technology for rocket launches, specifically to a squeeze-type water spray cooling and noise reduction system for launch vehicles. Background Technology

[0002] In the field of aerospace and launch vehicle launch, water spray cooling and noise reduction systems play a comprehensive role in displacing momentum and energy with high-temperature and high-speed gas flow, reducing the heat transfer intensity and ablation temperature of gas flow, and suppressing the formation of strong noise sources and noise propagation paths. They have become standard equipment at various launch sites. Most existing water spray cooling and noise reduction systems are based on gravity-flow water spray schemes using high-level water tanks (or water towers), referred to in this field as high-level water tank type water spray cooling and noise reduction systems. This system is relatively simple and easy to implement, but it also has inherent defects: (1) The water spray pressure is difficult to adjust. Different types of launch vehicle engines have different gas flow impact pressures. When the same launch site has different launch requirements for different types of launch vehicles, the water spray pressure adjustment is very limited, making it difficult to achieve the optimal water spray cooling and noise reduction effect; (2) The water spray pressure is generally low. The construction height of the high-level water tank is generally no more than 90m. The total water spray pressure that the rocket launch water spray cooling and noise reduction system can utilize is difficult to reach 0.8MPa. The water spray pressure of the end water spray device is often within 0.5MPa, which seriously restricts the energy and momentum exchange efficiency between the water spray and the high-temperature and high-speed gas flow, affecting the water spray cooling and noise reduction performance. At present, the launch of new high-pressure launch vehicles, represented by high-pressure liquid oxygen kerosene engines and liquid oxygen methane engines, is gradually occupying the commercial field of rocket launch. The pressure of the gas flow impacting the launch pad and the guide channel is 3 to 5 times that of the gas flow impact pressure of traditional medium and low pressure launch vehicles. The problem of insufficient water pressure of the high-level water tank type spray cooling and noise reduction system is further highlighted; (3) The construction of high-level water tanks is difficult. High-level water tanks exceeding 90m are very sensitive to foundation settlement and earthquake safety. The construction of high-level water tanks not only needs to solve a series of problems such as geological exploration, foundation settlement, and overturning caused by typhoons or strong winds, but also faces the safety risks of high-altitude operations during assembly, debugging and maintenance. In some inland areas, there is also the risk of water spray freezing due to large-area heat dissipation in cold weather. Summary of the Invention

[0003] The purpose of this invention is to provide a rocket launch compression water spray cooling and noise reduction system, which has the advantages of simple structure, convenient adjustment, safety and reliability, and strong practicality.

[0004] To address the technical problems of low spray pressure and difficulty in adjustment in existing high-level water tank-type spray cooling and noise reduction systems, this invention provides a rocket launch squeeze-type spray cooling and noise reduction system, including a launch pad spray subsystem and a guide channel spray subsystem. The launch pad spray subsystem includes a first gas storage tank, a first water storage tank, and first end spray devices. Two first gas storage tanks are provided and interconnected. The first water storage tank is connected to the first gas storage tank. The first water storage tank is connected to a first spray manifold, which is equipped with a first spray manifold control valve. Two first end spray devices are provided and distributed on both sides of the launch pad. The end spray devices are connected to the first spray main pipe via the first spray trunk pipe. The first spray trunk pipe is equipped with a first spray water control valve. The guide channel spray subsystem includes a second air tank, a second water tank, and a second end spray device. There are two second air tanks connected to each other. The second water tank is connected to the second air tank. The second water tank is connected to the second spray main pipe. The second spray main pipe is equipped with a second spray water control valve. There are two second end spray devices distributed on both sides of the guide channel. The two second end spray devices are connected to the second spray main pipe via the second spray trunk pipe. The second spray trunk pipe is equipped with a second spray water control valve.

[0005] Furthermore, the present invention provides a rocket launch compression water spray cooling and noise reduction system, wherein the first gas storage tank and the second gas storage tank are connected to the gas source through a first air intake pipe and a second air intake pipe respectively, the first air intake pipe is provided with a first air intake control valve and a first air intake pressure reducing valve, and the second air intake pipe is provided with a second air intake control valve and a second air intake pressure reducing valve.

[0006] Furthermore, the present invention provides a rocket launch compression spray water cooling and noise reduction system, wherein the first water storage tank is connected to a water source through a first water inlet pipe and a first water inlet control valve is provided on the first water inlet pipe, and the second water storage tank is connected to a water source through a second water inlet pipe and a second water inlet control valve is provided on the second water inlet pipe.

[0007] Furthermore, the present invention provides a rocket launch compression water spray cooling and noise reduction system, wherein the first water spray main pipe between the two first end water spray devices and the corresponding first water spray control valve is connected to the first drainage main pipe leading to the drainage pool through the first drainage main pipe, and the first drainage main pipe is provided with a first drainage control valve.

[0008] Furthermore, the present invention provides a rocket launch compression water spray cooling and noise reduction system, wherein the second water spray main pipe between the two second end water spray devices and the corresponding second water spray control valve is connected to the second drainage main pipe leading to the drainage pool through the second drainage main pipe, and the second drainage main pipe is provided with a second drainage control valve.

[0009] Furthermore, this invention provides a rocket launch compression-type water spray cooling and noise reduction system, wherein the first water spray master control valve is a butterfly valve and is equipped with a first pneumatic actuator. The first pneumatic actuator is a double-acting pneumatic actuator and is connected to a first energy storage device through a first valve group and a first air supply pipeline. The first energy storage device is connected to an air source through a first energy storage pipeline, which is equipped with a first energy storage shut-off valve and a first energy storage pressure reducing valve. The first valve group includes a first solenoid valve, a second solenoid valve, a first pneumatic control valve, a second pneumatic control valve, a third pneumatic control valve, and a fourth pneumatic control valve, all with their inlets interconnected and connected to the first air supply pipeline. The first solenoid valve is a two-position, three-position normally closed solenoid valve. The valves are as follows: the second solenoid valve is a two-position, three-normally open solenoid valve; the first, second, third, and fourth pneumatic control valves are two-position, three-normally closed pneumatic control valves; a first check valve is provided on the pipeline connected to the inlet of the first solenoid valve; the outlet of the first solenoid valve is connected to the control ports of the first and third pneumatic control valves; a second check valve is provided on the pipeline connected to the inlet of the second solenoid valve; the outlet of the second solenoid valve is connected to the control ports of the second and fourth pneumatic control valves; and the outlets of the first, second, third, and fourth pneumatic control valves are connected to ports one, two, three, and four of the first pneumatic actuator, respectively.

[0010] Furthermore, the present invention provides a rocket launch compression-type water spray cooling and noise reduction system, wherein the second water spray master control valve is a butterfly valve and is equipped with a second pneumatic actuator. The second pneumatic actuator is a double-acting pneumatic actuator and is connected to a second energy storage device through a second valve group and a second air supply pipeline. The second energy storage device is connected to an air source through a second energy storage pipeline. The second energy storage pipeline is equipped with a second energy storage shut-off valve and a second energy storage pressure reducing valve. The second valve group has the same structure as the first valve group.

[0011] Furthermore, the present invention provides a rocket launch compression-type water spray cooling and noise reduction system, wherein the first water spray control valve is a butterfly valve and is equipped with a third pneumatic actuator. The third pneumatic actuator is a double-acting pneumatic actuator and is connected to a third energy storage device through a third valve group and a third air supply pipeline. The third energy storage device is connected to an air source through a third energy storage pipeline, and the third energy storage pipeline is equipped with a third energy storage shut-off valve and a third energy storage pressure reducing valve. The third valve group has the same structure as the first valve group.

[0012] Furthermore, the present invention provides a rocket launch compression-type water spray cooling and noise reduction system, wherein the second water spray control valve is a butterfly valve and is equipped with a fourth pneumatic actuator. The fourth pneumatic actuator is a double-acting pneumatic actuator and is connected to a fourth energy storage device through a fourth valve group and a fourth air supply pipeline. The fourth energy storage device is connected to an air source through a fourth energy storage pipeline, and the fourth energy storage pipeline is equipped with a fourth energy storage shut-off valve and a fourth energy storage pressure reducing valve. The fourth valve group has the same structure as the first valve group.

[0013] Furthermore, in the rocket launch compression water spray cooling and noise reduction system of the present invention, the first air intake control valve, the second air intake control valve, the first water intake control valve, the second water intake control valve, the first drainage control valve and the second drainage control valve are all shut-off valves.

[0014] Compared with existing technologies, the rocket launch compression-type water spray cooling and noise reduction system of the present invention has the following advantages: The present invention sets up a launch pad water spray subsystem and a guide channel water spray subsystem. The launch pad water spray subsystem includes a first gas storage tank, a first water storage tank, and first end-spray devices. Two first gas storage tanks are provided and interconnected. The first water storage tank is connected to the first gas storage tank. The first water storage tank is connected to a first water spray main pipe. A first water spray main control valve is installed on the first water spray main pipe. Two first end-spray devices are provided and distributed on both sides of the launch pad. The two first end-spray devices are connected to the first water spray main pipe respectively. The first main water spray pipe is connected, and a first water spray control valve is installed on the first main water spray pipe. Similarly, the guide channel water spray subsystem is equipped with a second air tank, a second water tank, and a second end water spray device. There are two second air tanks connected to each other. The second water tank is connected to the second air tank. The second water tank is connected to the second main water spray pipe. A second main water spray control valve is installed on the second main water spray pipe. Two second end water spray devices are installed and distributed on both sides of the guide channel. The two second end water spray devices are connected to the second main water spray pipe through the second main water spray pipe. A second water spray control valve is installed on the second main water spray pipe. This constitutes a rocket launch compression-type water spray cooling and noise reduction system that is simple in structure, easy to adjust, safe, reliable, and highly practical. During rocket launch, the first main water spray control valve and the first water spray control valve are opened according to the control sequence. Water in the first water storage tank is sprayed onto the corresponding area of ​​the launch pad through the first main water spray pipe, the first main water spray pipe, and the first terminal water spray device under the compression action of the air pressure in the first gas storage tank. It exchanges energy and momentum with the gas flow, reducing the heat transfer intensity and ablation temperature of the gas flow, and suppressing the formation of strong noise sources and the noise propagation path. The second main water spray control valve and the second water spray control valve are opened according to the control sequence. Water in the second water storage tank is sprayed onto the corresponding area of ​​the guide channel through the second main water spray pipe, the second main water spray pipe, and the second terminal water spray device under the compression action of the air pressure in the second gas storage tank. It exchanges energy and momentum with the gas flow, reducing the heat transfer intensity and ablation temperature of the gas flow, and suppressing the formation of strong noise sources and the noise propagation path. This invention achieves the technical objective of configuring different spray pressures for the launch pad and guide channel water spray subsystems by setting up relatively independent launch pad water spray subsystems and guide channel water spray subsystems, and filling the first and second gas storage tanks with different gas pressures. On the one hand, it can well adapt to the situation where the impact pressure of the gas flow on the launch pad and guide channel is significantly different. On the other hand, by setting up separate gas storage tanks, the volume of the higher pressure gas storage tank is reduced, which helps to reduce gas supply waste and reduces the manufacturing difficulty of the gas storage tanks as well as the production, transportation, installation, commissioning and maintenance costs.Meanwhile, this invention, by correspondingly installing a first main water spray control valve and a first water spray control valve on the first main water spray pipe and the first water spray branch pipe, and correspondingly installing a second main water spray control valve and a second water spray control valve on the second main water spray pipe and the second water spray branch pipe, ensures that before the rocket launch countdown begins, all three valves are closed. The redundancy between the first main water spray control valve and the first water spray control valve effectively prevents malfunctions or premature actions of the launch pad water spray subsystem from affecting the safe launch of the rocket. Similarly, the redundancy between the second main water spray control valve and the second water spray control valve effectively prevents malfunctions or premature actions of the guide channel water spray subsystem from affecting the safe launch of the rocket. After the rocket launch countdown begins, the first and second main water spray control valves are opened relatively early, gradually releasing the water spray pressure to them. This effectively avoids the strong water hammer effect caused by the simultaneous action of the main water spray control valve and the water spray control valves, which could lead to severe damage during the launch, thus improving safety and reliability. Compared with existing high-level water tank-type water spray cooling and noise reduction systems, this invention adopts a squeeze-type water spray method with water pressure provided by a gas storage tank. This not only increases the water spray pressure, making the high pressure of the water spray unrestricted, but also allows for flexible adjustment of the water spray pressure to adapt to the launch requirements of different types of launch vehicles. It is only necessary to fill the gas storage tanks (first gas storage tank and second gas storage tank) with different gas pressures according to actual needs. At the same time, this invention does not require the construction of a high-level water tank. It only requires the placement of commonly used vertical column tanks or horizontal tanks on the ground as gas storage tanks and water storage tanks. The difficulty of infrastructure design, wind load safety design, and thermal insulation design is greatly reduced.

[0015] The following detailed description of a rocket launch compression water jet cooling and noise reduction system according to the present invention, with reference to the accompanying drawings, illustrates the specific embodiments. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of the structure of a rocket launch compression water jet cooling and noise reduction system according to the present invention; Figure 2 This is a schematic diagram of the structure of the first pneumatic actuator and the first valve group in this invention. 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 Figure 1 and Figure 2The present invention illustrates a specific embodiment of a rocket launch compression-type water spray cooling and noise reduction system, comprising a launch pad water spray subsystem and a guide channel water spray subsystem. The launch pad water spray subsystem includes a first gas storage tank 1, a first water storage tank 2, and first end water spray devices 3. Two first gas storage tanks 1 are provided and interconnected. The first water storage tank 2 is connected to the first gas storage tank 1 and connected to a first water spray main pipe 4, on which a first water spray main control valve 41 is installed. Two first end water spray devices 3 are provided and distributed on both sides of the launch pad. Each of the two first end water spray devices 3 is connected to the first water spray main pipe 4 via a first water spray branch pipe 5, on which a first water spray main control valve 51 is installed. Similarly, the guide channel water spray subsystem is equipped with a second air tank 1', a second water tank 2', and a second end water spray device 3'. There are two second air tanks 1' connected to each other. The second water tank 2' is connected to the second air tank 1'. The second water tank 2' is connected to the second water spray main pipe 4', and a second water spray main control valve 41' is installed on the second water spray main pipe 4'. There are two second end water spray devices 3', which are distributed on both sides of the guide channel. The two second end water spray devices 3' are respectively connected to the second water spray main pipe 4' through the second water spray branch pipe 5', and a second water spray control valve 51' is installed on the second water spray branch pipe 5'.

[0019] The above configuration constitutes a simple, easy-to-adjust, safe, reliable, and highly practical rocket launch compression-type water spray cooling and noise reduction system. During rocket launch, the first main water spray control valve 41 and the first water spray control valve 51 are opened according to the control sequence. Water in the first water storage tank 2 is then sprayed through the first main water spray pipe 4, the first main water spray pipe 5, and the first terminal water spray device 3 into the corresponding area of ​​the launch pad under the compression action of the air pressure in the first gas storage tank 1. This water exchanges energy and momentum with the gas flow, reducing heat transfer from the gas flow. Intensity, ablation temperature, and suppression of strong noise source formation and noise propagation path; according to the control sequence, the second water spray main control valve 41' and the second water spray control valve 51' are opened, and the water in the second water storage tank 2' will be sprayed into the corresponding area of ​​the guide channel through the second water spray main pipe 4', the second water spray main pipe 5' and the second end water spray device 3' under the squeezing action of the air pressure in the second air storage tank 1', and exchange energy and momentum with the gas flow, reducing the heat transfer intensity and ablation temperature of the gas flow, and suppressing the formation of strong noise source and noise propagation path. This invention achieves the technical objective of configuring different spray pressures for the launch pad and guide channel spray subsystems by setting up relatively independent launch pad spray subsystems and guide channel spray subsystems, and filling the first gas storage tank 1 and the second gas storage tank 1' with different gas pressures. On the one hand, it can well adapt to the situation where the impact pressure of the gas flow on the launch pad and the guide channel is significantly different. On the other hand, by setting up separate gas storage tanks (first gas storage tank 1 and second gas storage tank 1'), the volume of the higher pressure gas storage tank is reduced, which helps to reduce gas supply waste and reduces the manufacturing difficulty of the gas storage tanks as well as the production, transportation, installation, commissioning and maintenance costs. Meanwhile, this invention, by correspondingly installing a first main water spray control valve 41 and a first water spray control valve 51 on the first main water spray pipe 4 and the first water spray branch pipe 5, and correspondingly installing a second main water spray control valve 41' and a second water spray control valve 51' on the second main water spray pipe 4' and the second water spray branch pipe 5', ensures that before the rocket launch countdown begins, the first main water spray control valve 41, the first water spray control valve 51, the second main water spray control valve 41', and the second water spray control valve 51' are all in a closed state. The redundancy between the first main water spray control valve 41 and the first water spray control valve 51 effectively prevents the launch pad water spray subsystem from malfunctioning or prematurely activating, thus avoiding any impact on the safe launch of the rocket. The second main water spray control valve... The redundancy between valve 41' and the second water spray control valve 51' effectively prevents the water spray subsystem of the guide channel from malfunctioning or acting prematurely, thus affecting the safe launch of the rocket. After the rocket launch countdown begins, opening the first water spray master control valve 41 and the second water spray master control valve 41' relatively early, and gradually releasing the water spray pressure to the first water spray control valve 51 and the second water spray control valve 51', can effectively avoid the strong water hammer effect caused by the synchronous operation of the water spray master control valve (first water spray master control valve 41 and the second water spray master control valve 41') and the water spray control valve (first water spray control valve 51 and the second water spray control valve 51'), which would cause strong damage to the escort and improve safety and reliability.Compared with existing high-level water tank type spray cooling and noise reduction systems, this invention adopts a squeeze-type spray method in which the spray pressure is provided by the gas storage tanks (first gas storage tank 1 and second gas storage tank 1'). This can not only increase the spray pressure and make the high pressure of the spray unrestricted, but also flexibly adjust the spray pressure to adapt to the launch requirements of different types of launch vehicles. It is only necessary to fill the gas storage tanks (first gas storage tank 1 and second gas storage tank 1') with different gas pressures according to actual needs. At the same time, this invention does not require the setting of a high-level water tank. It can simply place commonly used vertical column tanks or horizontal tanks on the ground as gas storage tanks and water storage tanks. The difficulty of infrastructure design, wind load safety design and thermal insulation design is greatly reduced. It should be noted that, to avoid excessively rapid pressure drop in the spray, this invention employs a design combining a large-capacity air tank group with a smaller-capacity water tank in both the launch pad water spray subsystem and the guide channel water spray subsystem. Typically, the volume ratio of the air tank to the water tank should be no less than 1.5:1, that is, the volume ratio of the two first air tanks 1 to the first water tank 2, and the volume ratio of the two second air tanks 1' to the second water tank 2', should both be no less than 1.5:1. This arrangement offers two potential advantages: firstly, it ensures that the end spray devices (first end spray device 3 and second end spray device 3') completely deplete the water stored in the water tanks (first water tank 2 and second water tank 2'). The water spray pressure drop does not exceed 40%, ensuring that the water spray pressure remains at a high level throughout the rocket launch and takeoff phase. This allows for effective intervention in the high-temperature, high-speed gas flow throughout the entire process. Secondly, after rocket takeoff, the residual gas pressure in the gas storage tanks (first gas storage tank 1 and second gas storage tank 1') is sufficient to blow away residual water from the water storage tanks (first water storage tank 2 and second water storage tank 2'), the main water spray pipes (first main water spray pipe 4 and second main water spray pipe 4'), the main water spray pipes (first main water spray pipe 5 and second main water spray pipe 5'), and the end water spray devices (first end water spray device 3 and second end water spray device 3'). This effectively prevents residual water from freezing during non-mission periods and avoids rusting of the water spray cooling and noise reduction system structure caused by residual water. It should also be noted that the first end water spray device 3 and the second end water spray device 3' mentioned in this article are existing technologies in the field, typically employing an array nozzle configuration, the structure, principle, and arrangement of which are well known to those skilled in the art.

[0020] As an optimized solution, this specific embodiment employs the following inflation method for the first gas storage tank 1 and the second gas storage tank 1': the first gas storage tank 1 and the second gas storage tank 1' are connected to the gas source via the first air intake pipe 6 and the second air intake pipe 6', respectively. A first air intake control valve 61 and a first air intake pressure reducing valve 62 are installed on the first air intake pipe 6, and a second air intake control valve 61' and a second air intake pressure reducing valve 62' are installed on the second air intake pipe 6'. This configuration features simple structure, convenient inflation, and precise control. By adopting relatively independent inflation schemes for the launch pad water spray subsystem and the guide channel water spray subsystem, the inflation pressure of the first gas storage tank 1 and the second gas storage tank 1' can be arbitrarily controlled according to actual needs, improving the system's adaptability and practicality. When filling the first gas tank 1, simply adjust the first intake pressure reducing valve 62 and open the first intake control valve 61. The high-pressure gas from the gas source will automatically fill the first gas tank 1 through the first intake pipe 6. After filling, the first intake pressure reducing valve 62 will automatically close. At this time, closing the first intake control valve 61 prepares for the subsequent water spraying action of the launch pad water spray subsystem. Similarly, when filling the second gas tank 1', simply adjust the second intake pressure reducing valve 62' and open the second intake control valve 61'. The high-pressure gas from the gas source will automatically fill the second gas tank 1' through the second intake pipe 6'. After filling, the second intake pressure reducing valve 62' will automatically close. At this time, closing the second intake control valve 61' prepares for the subsequent water spraying action of the guide channel water spray subsystem. In practical applications, this invention typically connects the first intake pipe 6 and the second intake pipe 6' to a main intake pipe, and connects the main intake pipe to the gas source to simplify the structure and pipe layout.

[0021] As an optimized solution, this specific embodiment employs the following water filling method for the first water storage tank 2 and the second water storage tank 2': the first water storage tank 2 is connected to a water source via a first inlet pipe 7, and a first inlet control valve 7 is installed on the first inlet pipe 7; the second water storage tank 2' is connected to a water source via a second inlet pipe 7', and a second inlet control valve 7' is installed on the second inlet pipe 7'. This configuration also features a simple structure and convenient water filling. When filling the first water storage tank 2, the first inlet control valve 7 is opened, and the water pump installed at the water source is started. Water from the water source will then flow into the first water storage tank 2 through the first inlet pipe 7. After filling is complete, the water pump is stopped, and the first inlet control valve 7 is closed. Similarly, when filling the second water storage tank 2', the second inlet control valve 7' is opened, and the water pump installed at the water source is started. Water from the water source will then flow into the second water storage tank 2' through the second inlet pipe 7'. After filling is complete, the water pump is stopped, and the second inlet control valve 7' is closed. It should be noted that in practical applications, the present invention typically connects the first water inlet pipe 7 to the second water inlet control valve 7' and the second water storage tank 2', and connects the second water inlet pipe 7' to the water source through the main water inlet pipe. A water pump is installed on the main water inlet pipe to simplify the structure and pipeline layout. In this way, only one water pump is needed to simultaneously meet the water filling needs of the first water storage tank 2 and the second water storage tank 2', and the amount of the first water inlet pipe 7 is reduced. However, when filling the first water storage tank 2, the first water inlet control valve 7 and the second water inlet control valve 7' must be opened simultaneously. In addition, it should be pointed out that when preparing for water spraying in the launch pad water spray subsystem and the guide channel water spray subsystem, water should be filled first and then air should be added. That is, water should be added to the first water storage tank 2 and the second water storage tank 2' first, and then air should be added to the first air storage tank 1 and the second air storage tank 1' after the water filling is completed.

[0022] As an optimization, to facilitate the drainage of residual water in the launch pad water spray subsystem and the guide channel water spray subsystem after the rocket launch mission, thereby reducing the corrosion of the system and valves during non-mission periods, this specific embodiment connects the first water spray mains 5 between the two first end water spray devices 3 and their corresponding first water spray control valves 51 to the first drainage main 31, which in turn connects to the first drainage main 32 leading to the drainage pool. A first drainage control valve 33 is installed on the first drainage main 32. Similarly, the second water spray mains 5' between the two second end water spray devices 3' and their corresponding second water spray control valves 51' are connected to the second drainage main 32' leading to the drainage pool via the second drainage main 31'. A second drainage control valve 33' is installed on the second drainage main 32'. This configuration features a simple structure and convenient drainage. After the rocket launch mission is completed, keep the first water spray master control valve 41 and the first water spray control valve 51 open. At this time, open the first drainage control valve 33. Under the action of the residual gas pressure in the first gas storage tank 1, the residual water in the launch pad water spray subsystem will enter the drainage pool through the first drainage main pipe 31 and the first drainage main pipe 32. After drainage is completed, close the first water spray master control valve 41, the first water spray control valve 51, and the first drainage control valve 33. Similarly, keep the second water spray master control valve 41' and the second water spray control valve 51' open. At this time, open the second drainage control valve 33'. Under the action of the residual gas pressure in the second gas storage tank 1', the residual water in the guide channel water spray subsystem will enter the drainage pool through the second drainage main pipe 31' and the second drainage main pipe 32'. After drainage is completed, close the second water spray master control valve 41', the second water spray control valve 51', and the second drainage control valve 33'.

[0023] In practical applications, to facilitate control and improve safety and reliability, the present invention employs shut-off valves for the first air intake control valve 61, the second air intake control valve 61', the first water intake control valve 7, the second water intake control valve 7', the first drain control valve 33, and the second drain control valve 33'.

[0024] Because the system operates at relatively high water pressure, as an optimization solution, such as Figure 2As shown, in this specific embodiment, the first water spray master control valve 41 adopts a butterfly valve and is pneumatically controlled to improve its load-bearing capacity and enable rapid opening and closing. Specifically, a first pneumatic actuator 411 that drives the valve shaft is installed on the first water spray master control valve 41. The first pneumatic actuator 411 is a double-acting pneumatic actuator and is connected to the first energy storage device 43 through the first valve group and the first air supply line 42. The first energy storage device 43 is connected to the air source through the first energy storage line 44. The first energy storage line 44 is equipped with a first energy storage shut-off valve 45 and a first energy storage pressure reducing valve 46. In a specific implementation, the present invention employs the following structure and connection method for the first valve group: A first solenoid valve 412, a second solenoid valve 413, a first pneumatic control valve 414, a second pneumatic control valve 415, a third pneumatic control valve 416, and a fourth pneumatic control valve 417 are provided, with their air inlets interconnected and connected to the first air supply pipeline 42. Specifically, the first solenoid valve 412 is a two-position, three-position normally closed solenoid valve; the second solenoid valve 413 is a two-position, three-position normally open solenoid valve; and the first pneumatic control valve 414, the second pneumatic control valve 415, the third pneumatic control valve 416, and the fourth pneumatic control valve 417 are two-position, three-position normally closed pneumatic control valves. The first solenoid valve 412, the second solenoid valve 413, the first pneumatic control valve 414, the second pneumatic control valve 415, the third pneumatic control valve 416, and the fourth pneumatic control valve 417 are all two-position, three-position normally closed pneumatic control valves. A first check valve 418 is installed on the pipeline connected to the 12 air inlets, and the outlet of the first solenoid valve 412 is connected to the control ports of the first pneumatic control valve 414 and the third pneumatic control valve 416. A second check valve 419 is installed on the pipeline connected to the air inlet of the second solenoid valve 413, and the outlet of the second solenoid valve 413 is connected to the control ports of the second pneumatic control valve 415 and the fourth pneumatic control valve 417. The outlets of the first pneumatic control valve 414, the second pneumatic control valve 415, the third pneumatic control valve 416, and the fourth pneumatic control valve 417 are connected to the air ports one, two, three, and four of the first pneumatic actuator 411, respectively. This configuration features simple structure, convenient control, sensitive action, and reliable safety. Before the water spraying action, the first energy storage pressure reducing valve 46 should be adjusted and the first energy storage shut-off valve 45 should be opened to charge the first energy storage device 43 with gas at a certain pressure. After charging is completed, the first energy storage shut-off valve 45 can be closed.The operation of the first water spray master control valve 41 and the first pneumatic actuator 411 is as follows: When the first solenoid valve 412 and the second solenoid valve 413 are de-energized, the first solenoid valve 412 closes and the second solenoid valve 413 opens. At this time, the gas in the first accumulator 43 enters the cylinder cavity corresponding to the second and fourth air ports through the second air control valve 415 and the fourth air control valve 417. The gas in the cylinder cavity corresponding to the first and third air ports is discharged through the first air control valve 414 and the third air control valve 416. The first pneumatic actuator 411 drives the first water spray master control valve 411. The valve shaft of control valve 41 rotates to close it; when the first solenoid valve 412 and the second solenoid valve 413 are energized, the first solenoid valve 412 opens and the second solenoid valve 413 closes. At this time, the gas in the first accumulator 43 enters the cylinder cavity corresponding to air port one and air port three through the first pneumatic control valve 414 and the third pneumatic control valve 416, while the gas in the cylinder cavity corresponding to air port two and air port four is discharged through the second pneumatic control valve 415 and the fourth pneumatic control valve 417. The first pneumatic actuator 411 drives the valve shaft of the first water spray master control valve 41 to rotate and open it. By using a double-acting pneumatic actuator 411, the first pneumatic actuator ensures that only when both cylinders are supplied with air simultaneously can sufficient power be provided to open the first water spray master control valve 41, thus guaranteeing the safety of opening the first water spray master control valve 41.

[0025] Similarly, this invention also employs butterfly valves for the second main water spray control valve 41', the first water spray control valve 51, and the second water spray control valve 51', and uses pneumatic control to improve their load-bearing capacity and enable rapid opening and closing. Specifically: a second pneumatic actuator is installed on the second main water spray control valve 41' to drive its valve shaft. The second pneumatic actuator is a double-acting pneumatic actuator and is connected to the second energy storage device 43' through the second valve group and the second air supply line 42'. The second energy storage device 43' is connected to the air source through the second energy storage line 44', and a second energy storage shut-off valve 45' and a second energy storage pressure reducing valve 46' are installed on the second energy storage line 44'. A third pneumatic actuator is installed on the first water spray control valve 51 to drive its valve shaft. The third pneumatic actuator is a double-acting pneumatic actuator and is connected to the third valve group and the third air supply line 52'. The third energy accumulator 53 is connected to the air source via the third energy storage pipeline 54, and a third energy storage shut-off valve 55 and a third energy storage pressure reducing valve 56 are installed on the third energy storage pipeline 54. A fourth pneumatic actuator, which drives the valve shaft of the second water spray control valve 51', is installed on the second valve 51'. This fourth pneumatic actuator is a double-acting pneumatic actuator and is connected to the fourth energy accumulator 53' via the fourth valve group and the fourth air supply pipeline 52'. The fourth energy accumulator 53' is connected to the air source via the fourth energy storage pipeline 54', and a fourth energy storage shut-off valve 55' and a fourth energy storage pressure reducing valve 56' are installed on the fourth energy storage pipeline 54'. The structure and connection method of the second, third, and fourth valve groups are the same as those of the first valve group. This invention employs relatively independent air-charging schemes for the accumulators (first energy storage unit 43, second energy storage unit 43', third energy storage unit 53, and fourth energy storage unit 53') that drive the first water jet master control valve 41, the second water jet master control valve 41', the first water jet control valve 51, and the second water jet control valve 51'. Each accumulator's pressure can be independently matched and has a certain degree of adjustability, meeting the requirements for adjusting the action response speed of the water jet master control valve and the water jet control valve according to different rocket ignition sequences and takeoff speeds. To simplify the structure and piping layout, this specific embodiment also includes an energy storage master pipeline connected to the air intake master pipeline, with the first energy storage pipeline 44, the second energy storage pipeline 44', the third energy storage pipeline 54, and the fourth energy storage pipeline 54' respectively connected to the energy storage master pipeline.

[0026] 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 rocket launch compression-type water spray cooling and noise reduction system, characterized in that, The system includes a launch pad water spray subsystem and a guide channel water spray subsystem. The launch pad water spray subsystem includes a first air tank (1), a first water tank (2), and a first end water spray device (3). There are two first air tanks (1) connected to each other. The first water tank (2) is connected to the first air tank (1). The first water tank (2) is connected to a first water spray main pipe (4). A first water spray main control valve (41) is provided on the first water spray main pipe (4). There are two first end water spray devices (3) distributed on both sides of the launch pad. The two first end water spray devices (3) are respectively connected to the first water spray main pipe (4) through a first water spray trunk pipe (5). A first water spray main control valve (51) is provided on the first water spray trunk pipe (5). The guide channel water spray subsystem includes a second air tank (1'), a second water tank (2'), and a second end water spray device (3'). There are two second air tanks (1') connected to each other. The second water tank (2') is connected to the second air tank (1'). The second water tank (2') is connected to a second water spray main pipe (4'). A second water spray main control valve (41') is provided on the second water spray main pipe (4'). There are two second end water spray devices (3') distributed on both sides of the guide channel. The two second end water spray devices (3') are respectively connected to the second water spray main pipe (4') through a second water spray branch pipe (5'). A second water spray control valve (51') is provided on the second water spray branch pipe (5').

2. The rocket launch squeeze-type water jet cooling and noise reduction system according to claim 1, characterized in that, The first gas storage tank (1) and the second gas storage tank (1') are connected to the gas source through the first air intake pipe (6) and the second air intake pipe (6'), respectively. The first air intake pipe (6) is provided with a first air intake control valve (61) and a first air intake pressure reducing valve (62), and the second air intake pipe (6') is provided with a second air intake control valve (61') and a second air intake pressure reducing valve (62').

3. The rocket launch squeeze-type water jet cooling and noise reduction system according to claim 2, characterized in that, The first water storage tank (2) is connected to the water source through the first water inlet pipe (7), and the first water inlet pipe (7) is equipped with a first water inlet control valve (71). The second water storage tank (2') is connected to the water source through the second water inlet pipe (7'), and the second water inlet pipe (7') is equipped with a second water inlet control valve (71').

4. The rocket launch squeeze-type water jet cooling and noise reduction system according to claim 3, characterized in that, The first water spraying main pipe (5) between the two first end water spraying devices (3) and the corresponding first water spraying control valve (51) is connected to the first drainage main pipe (32) leading to the drainage pool through the first drainage main pipe (31), and the first drainage main pipe (32) is provided with a first drainage control valve (33).

5. The rocket launch squeeze-type water jet cooling and noise reduction system according to claim 4, characterized in that, The two second end water spray devices (3') and the corresponding second water spray control valve (51') are connected to the second drainage main pipe (32') leading to the drainage pool through the second drainage main pipe (31'). The second drainage main pipe (32') is equipped with a second drainage control valve (33').

6. The rocket launch squeeze-type water jet cooling and noise reduction system according to claim 5, characterized in that, The first water spray master control valve (41) is a butterfly valve and is equipped with a first pneumatic actuator (411). The first pneumatic actuator (411) is a double-acting pneumatic actuator and is connected to the first energy storage device (43) through the first valve group and the first air supply line (42). The first energy storage device (43) is connected to the air source through the first energy storage line (44). The first energy storage line (44) is equipped with a first energy storage shut-off valve (45) and a first energy storage pressure reducing valve (46). The first valve group includes a first solenoid valve (412), a second solenoid valve (413), a first pneumatic control valve (414), a second pneumatic control valve (415), a third pneumatic control valve (416), and a fourth pneumatic control valve (417) whose air inlets are interconnected and connected to the first air supply line (42). The first solenoid valve (412) is a two-position three-normally closed solenoid valve, and the second solenoid valve (413) is a two-position three-normally open solenoid valve. The first pneumatic control valve (414), the second pneumatic control valve (415), the third pneumatic control valve (416), and the fourth pneumatic control valve (417) are two-position three-normally closed pneumatic control valves. A first check valve (418) is provided on the pipeline connected to the inlet of the first solenoid valve (412). The outlet of the first solenoid valve (412) is connected to the control ports of the first pneumatic control valve (414) and the third pneumatic control valve (416). A second check valve (419) is provided on the pipeline connected to the inlet of the second solenoid valve (413). The outlet of the second solenoid valve (413) is connected to the control ports of the second pneumatic control valve (415) and the fourth pneumatic control valve (417). The outlets of the first pneumatic control valve (414), the second pneumatic control valve (415), the third pneumatic control valve (416), and the fourth pneumatic control valve (417) are connected to the first, second, third, and fourth ports of the first pneumatic actuator (411).

7. The rocket launch squeeze-type water jet cooling and noise reduction system according to claim 6, characterized in that, The second water spray master control valve (41') is a butterfly valve and is equipped with a second pneumatic actuator. The second pneumatic actuator is a double-acting pneumatic actuator and is connected to the second energy storage device (43') through the second valve group and the second air supply line (42'). The second energy storage device (43') is connected to the air source through the second energy storage line (44'). The second energy storage line (44') is equipped with a second energy storage shut-off valve (45') and a second energy storage pressure reducing valve (46'). The second valve group has the same structure as the first valve group.

8. The rocket launch squeeze-type water jet cooling and noise reduction system according to claim 6, characterized in that, The first spray water control valve (51) is a butterfly valve and is equipped with a third pneumatic actuator. The third pneumatic actuator is a double-acting pneumatic actuator and is connected to the third energy storage device (53) through the third valve group and the third air supply line (52). The third energy storage device (53) is connected to the air source through the third energy storage line (54). The third energy storage line (54) is equipped with a third energy storage shut-off valve (55) and a third energy storage pressure reducing valve (56). The third valve group has the same structure as the first valve group.

9. The rocket launch squeeze-type water jet cooling and noise reduction system according to claim 6, characterized in that, The second water spray control valve (51') is a butterfly valve and is equipped with a fourth pneumatic actuator. The fourth pneumatic actuator is a double-acting pneumatic actuator and is connected to the fourth energy storage device (53') through the fourth valve group and the fourth air supply line (52'). The fourth energy storage device (53') is connected to the air source through the fourth energy storage line (54'). The fourth energy storage line (54') is equipped with a fourth energy storage shut-off valve (55') and a fourth energy storage pressure reducing valve (56'). The fourth valve group has the same structure as the first valve group.

10. The rocket launch squeeze-type water jet cooling and noise reduction system according to claim 6, characterized in that, The first air intake control valve (61), the second air intake control valve (61'), the first water intake control valve (7), the second water intake control valve (7'), the first drain control valve (33), and the second drain control valve (33') are all shut-off valves.

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