阅读说明：本技术 一种跟随火箭尾焰高位自动喷水降噪系统 (Follow rocket tail flame high-order automatic water spray noise reduction system ) 是由 刘俊林 张志成 李玉良 宋道宏 陈丹 亢勇 唐小松 崔展鹏 季会媛 陈默 周云龙 于 2021-06-29 设计创作，主要内容包括：本发明公开了一种跟随火箭尾焰高位自动喷水降噪系统,属于火箭发射噪声防护技术领域。系统包括喷嘴、快速阀控系统、供气系统、供水系统以及排水系统；喷嘴通过喷水管路接至供水系统,喷嘴均匀布置发射工位前后两侧,喷嘴稳定喷水后喷水范围能够覆盖发射台；快速阀控系统设置在供水管路上,火箭发动机点火前实现系统近程喷水,火箭点火起飞后某一时刻实现系统远程喷水,近程喷水和远程喷水两种工况转换时间间隔在1s左右；供气系统为快速阀控系统提供压缩空气作为操纵气源；排水系统将大流量喷水及时收集并排到发射场外侧低洼处。本发明根据火箭发射工况进行喷水工况切换,能够保证箭体安全,同时抑制噪声辐射和传播。(The invention discloses a high-position automatic water spraying and noise reducing system following rocket tail flames, and belongs to the technical field of rocket launching noise protection. The system comprises a nozzle, a quick valve control system, an air supply system, a water supply system and a drainage system; the nozzles are connected to a water supply system through a water spraying pipeline, the nozzles are uniformly arranged on the front side and the rear side of the launching station, and the water spraying range can cover the launching platform after the nozzles stably spray water; the rapid valve control system is arranged on a water supply pipeline, the short-range water spraying of the system is realized before the rocket engine is ignited, the long-range water spraying of the system is realized at a certain moment after the rocket is ignited and takes off, and the conversion time interval of the short-range water spraying working condition and the long-range water spraying working condition is about 1 s; the air supply system provides compressed air for the quick valve control system to be used as an operation air source; the drainage system collects and discharges large-flow water to a low-lying position outside the launching field in time. The invention switches the water spraying working condition according to the rocket launching working condition, can ensure the rocket body safety and simultaneously inhibits noise radiation and propagation.)

1. A high-position automatic water spraying and noise reducing system following rocket tail flames is characterized by comprising a nozzle, a water spraying pipeline, a quick valve control system, an air supply system, a water supply system and a water drainage system;

the nozzles are connected to a water supply system through a water spraying pipeline, the water supply system is positioned at the upper part of the launching tower, the nozzles are uniformly arranged at the front side and the rear side of a launching station, and the water spraying range can cover the launching platform after the nozzles stably spray water;

the rapid valve control system is arranged on a water spraying pipeline, the system short-range water spraying is realized before the rocket engine is ignited, the system long-range water spraying is realized at a certain moment after the rocket is ignited and takes off, when the tail end of the rocket crosses a nozzle, the sprayed water reaches the jet flow tail flame of the engine, and the conversion time interval of the short-range water spraying working condition and the long-range water spraying working condition is about 1 s;

the air supply system provides compressed air for the quick valve control system to serve as an operating air source;

the drainage system collects and discharges large-flow water spray to a low-lying position outside the launching field.

2. A rocket-tailed flame following high-position automatic water spraying and noise reducing system as recited in claim 1, wherein said nozzle has a flat structure with a uniform thickness, the nozzle inlet is a square cavity where the water flow makes a filling turn, the end of the square cavity is an initial rectangular hole, then the rectangular hole is gradually deformed to a more flat rectangular hole, the sectional area of the flat rectangular hole at the nozzle outlet is smaller than that of the initial rectangular hole; the nozzle outlet has two deformation directions, one is that the both sides wall in square chamber expands to both sides on the plane of nozzle, is the sector and sprays out, and another deformation direction is that the upper and lower bottom surface in square chamber contracts to the center in the thickness direction of nozzle, and the rectangular hole width narrows.

3. A high-level automatic water spraying and noise reducing system for a follow rocket tail flame according to claim 1 or 2, wherein the rapid valve control system is positioned on a water spraying pipeline in a comprehensive pipe gallery, and the system comprises two pneumatic butterfly valves and a manual butterfly valve from top to bottom in sequence; the manual butterfly valve is used for overhauling the pneumatic butterfly valve, and the system is in an open state before running; before the rocket engine is ignited, starting one pneumatic butterfly valve to an opening a, then starting the other pneumatic butterfly valve to be fully opened, realizing short-range water spraying of the system, starting the first pneumatic butterfly valve from the opening a to the opening b at a certain moment after the rocket is ignited and takes off, realizing long-range water spraying of the system, and after the tail end of the rocket crosses a nozzle, spraying water to reach jet flow tail flames of the engine; the two pneumatic butterfly valves are flexibly bound according to different rocket launching time sequences through remote control and control time sequences.

4. A high-level automatic water spraying and noise reducing system for a follow rocket tail flame according to claim 1 or 2, wherein the air supply system supplies air for a pneumatic butterfly valve in an online manner.

5. A high-level automatic water spraying and noise reducing system for a follow-up rocket tail flame according to claim 1 or 2, wherein the water supply system comprises a noise reducing water tank and water supply main pipes, the water quantity is supplied to the comprehensive pipe gallery of the launching station through the two water supply main pipes, and the water spraying pipelines are led out from the two water supply main pipes and finally connected to the nozzles.

6. A rocket-following tail flame high-level automatic water-spraying noise-reducing system as recited in claim 3, wherein said gas-supplying system supplies gas for pneumatic butterfly valve in an on-line manner.

7. A rocket-trailing tail flame high-level automatic water spraying and noise reducing system as recited in claim 3, wherein said water supply system comprises a noise reducing water tank and water supply main pipes, the water quantity is supplied to the launching station comprehensive pipe gallery through two water supply main pipes, and the water spraying pipeline is led out from two water supply main pipes and finally connected to the nozzle.

8. A follow rocket tail flame high level automatic water spray noise reduction system according to claim 5, wherein a bellows is provided outside the water spray pipeline after the water spray pipeline exits the ground.

9. The high-level automatic water spraying and noise reducing system for the trailing rocket tail flame according to claim 5, wherein the drainage system comprises a terrace drainage part and a pipeline residual water drainage part; the method is characterized in that the cut-off ditch around the launching station is utilized for drainage of the field, the bottom of the cut-off ditch is connected with a vertical drainage pipe, a cut-off ditch cover plate is arranged on the cut-off ditch, the cut-off ditch cover plate covers the cut-off ditch at ordinary times, the cut-off ditch cover plate is removed after the cut-off ditch cover plate enters the launching process, and the large-flow water spraying is timely collected; the surplus water of pipeline discharges and utilizes the drain pipe, arranges the escape canal to utility tunnel in through the pneumatic butterfly valve on the control drain pipe, and then arranges the outside low-lying department of launching site.

10. A follow rocket tail flame high level automatic water spray noise reduction system as recited in claim 7, wherein said drainage system comprises a terrace drainage and a pipeline residual water drainage; the method is characterized in that the cut-off ditch around the launching station is utilized for drainage of the field, the bottom of the cut-off ditch is connected with a vertical drainage pipe, a cut-off ditch cover plate is arranged on the cut-off ditch, the cut-off ditch cover plate covers the cut-off ditch at ordinary times, the cut-off ditch cover plate is removed after the cut-off ditch cover plate enters the launching process, and the large-flow water spraying is timely collected; the surplus water of pipeline discharges and utilizes the drain pipe, arranges the escape canal to utility tunnel in through the pneumatic butterfly valve on the control drain pipe, and then arranges the outside low-lying department of launching site.

Technical Field

The invention relates to a high-position automatic water spraying and noise reducing system following rocket tail flames, and belongs to the technical field of rocket launching noise protection.

Background

When the medium-large bundled carrier rocket is launched, the primary and boosting engine jet flow can generate pneumatic noise of more than 170dB, and sound-induced vibration can be generated on the rocket, weak structural members of a launching system and sound-sensitive electrical elements, so that destructive influence is caused, and the surrounding environment of a launching site and testing personnel can be injured. When the rocket is ignited, water is sprayed into the engine gas jet flow field, a noise generation mechanism is changed, noise propagation is inhibited, and the peripheral noise value of the rocket can be effectively reduced. At present, high-level water spraying lags behind the takeoff time of a rocket, in the initial stage of the takeoff of the rocket, the water spraying and noise reducing system cannot be started due to the fact that mistaken spraying influences rocket bodies, noise reducing water cannot reach an engine jet flow region in time, and when the water spraying and noise reducing system is started, the rocket bodies fly far away from the ground, so that the noise reducing effect of the high-level water spraying is influenced.

Disclosure of Invention

In view of the above, the invention provides a high-position automatic water spraying and noise reducing system following rocket tail flames, which has two working conditions of short-range water spraying and long-range water spraying, and can switch the water spraying working conditions according to the rocket launching working conditions, thereby ensuring the safety of a rocket body and inhibiting noise radiation and propagation.

A high-position automatic water spraying and noise reducing system following rocket tail flames comprises a nozzle, a water spraying pipeline, a quick valve control system, an air supply system, a water supply system and a water drainage system;

the nozzles are connected to a water supply system through a water spraying pipeline, the water supply system is positioned at the upper part of the launching tower, the nozzles are uniformly arranged at the front side and the rear side of a launching station, and the water spraying range can cover the launching platform after the nozzles stably spray water;

the rapid valve control system is arranged on a water supply pipeline, the system short-range water spraying is realized before the rocket engine is ignited, the system long-range water spraying is realized at a certain moment after the rocket is ignited and takes off, when the tail end of the rocket crosses a nozzle, the sprayed water reaches the jet flow tail flame of the engine, and the conversion time interval of the short-range water spraying working condition and the long-range water spraying working condition is about 1 s;

the air supply system provides compressed air for the quick valve control system to serve as an operating air source;

the drainage system collects large-flow water spray in time and discharges the water spray to a low-lying position outside the launching field.

Furthermore, the shape of the nozzle is a flat structure with equal thickness, the inlet of the nozzle is a square cavity, the water flow realizes filling and turning at the position, the tail end of the square cavity is an initial rectangular hole, then the rectangular hole is gradually deformed to a more flat rectangular hole, and the sectional area of the flat rectangular hole at the outlet of the nozzle is smaller than that of the initial rectangular hole; the nozzle outlet has two deformation directions, one is that the both sides wall in square chamber expands to both sides on the plane of nozzle, is the sector and sprays out, and another deformation direction is that the upper and lower bottom surface in square chamber contracts to the center in the thickness direction of nozzle, and the rectangular hole width narrows.

Furthermore, the rapid valve control system is positioned in the comprehensive pipe gallery and arranged on a water spray pipeline below the nozzle, and the system comprises two large-caliber two-section pneumatic butterfly valves and a manual butterfly valve from top to bottom in sequence; the manual butterfly valve is used for overhauling the pneumatic butterfly valve and is in an open state before the system runs; before the rocket engine is ignited, one pneumatic butterfly valve is started to the opening degree a, then the other pneumatic butterfly valve is started to be fully opened, short-range water spraying of the system is achieved, at a certain moment after the rocket is ignited and takes off, the first pneumatic butterfly valve is started to spray water from the opening degree a to the opening degree b, long-range water spraying of the system is achieved, and after the tail end of the rocket crosses a nozzle, the sprayed water reaches jet flow tail flames of the engine. The pneumatic butterfly valve is flexibly bound according to different rocket launching time sequences through remote control and control time sequences.

Furthermore, the air supply system supplies air for the pneumatic butterfly valve in an online mode so as to adapt to the stability of air source pressure and the filling of flow during the control action of the pneumatic valve.

Furthermore, water supply system includes and makes an uproar the water tank and supplies water the main, and the water yield supplies to launch station utility tunnel in through two water supply main, and high-order water spray pipeline draws forth from two water supply main, finally connects to the nozzle, and water supply main end has the steady voltage function of retaining concurrently.

Furthermore, a corrugated pipe is arranged outside the water spraying pipeline after the water spraying pipeline is discharged out of the ground.

Further, the drainage system comprises a terrace drainage part and a pipeline residual water drainage part. The method is characterized in that the cut-off ditch is arranged on the periphery of the launching station for drainage of the field, the bottom of the cut-off ditch is connected with a vertical drainage pipe, a cut-off ditch cover plate is arranged on the cut-off ditch, the cut-off ditch cover plate covers the cut-off ditch at ordinary times, so that the daily operation is convenient, after the launching process is carried out, all the cut-off ditch cover plates are automatically removed by an automatic paving and removing vehicle, the large-flow water spraying and timely collection are realized, and the accumulated water on the field and the large-scale freezing in winter are avoided; the surplus water of pipeline discharges and utilizes the drain pipe, arranges the escape canal to utility tunnel in through the pneumatic butterfly valve on the control drain pipe, and then arranges the outside low-lying department of launching site.

Has the advantages that:

1. the invention adopts an action mode of automatically spraying water at a high position along with the tail flame of the rocket, before the rocket is ignited, the water spraying noise reduction system starts to spray water at a short range, when the thrust of the engine is built and the rocket takes off, the water spraying noise reduction system starts to spray water at a long range, and when the rocket engine flies over the height of the nozzle, the sprayed water reaches the tail flame of the engine. The scheme has the advantages of early water spraying starting time, long acting time and better noise reduction performance.

2. The invention adopts a large-flow special-shaped nozzle, the outlet of the nozzle is provided with two deformation directions, one deformation direction is that two side walls of a square cavity expand to two sides on the plane of the nozzle and are ejected out in a sector mode, the other deformation direction is that the upper bottom surface and the lower bottom surface of the square cavity contract to the center in the thickness direction of the nozzle, and the width of a rectangular hole is narrowed. The single nozzle flow of this scheme is big, and coverage is big, and structural style is simple, and occupation space is few, can not take place to interfere with other facilities.

3. The invention adopts a combined valve control mode of a double pneumatic butterfly valve and a manual butterfly valve, and the double pneumatic valves are combined to control to realize a short-range water spraying working condition and a long-range water spraying working condition. The scheme has high reliability and short working condition conversion time, and the valve control time sequence can be flexibly bound according to different rocket launching time sequences and can adapt to various rocket launching working conditions.

4. The rapid valve control system adopted by the invention is arranged in the comprehensive pipe gallery, so that the pneumatic butterfly valve positioner and the amplifier are prevented from directly bearing the low-frequency vibration effect of the unsteady jet flow of the rocket; meanwhile, the corrugated pipe is arranged between the rapid valve control system and the external space arrangement nozzle pipeline, so that on one hand, the water hammer effect is reduced, and on the other hand, the vibration of the external nozzle pipeline can be reduced to be transmitted to the valve. The design method reduces the risk of failure of the pneumatic butterfly valve positioner and the amplifier.

5. The drainage system adopted by the invention can quickly drain, reduce noise and use large-flow water, effectively reduce accumulated water on the field and prevent freezing in winter; the trench cover board that dams adopts automatic the car of removing of mating formation to remove to mat formation and remove and receive, can practice thrift the manpower raise the efficiency.

Drawings

FIG. 1 is a sectional view of a high-position automatic water spraying and noise reducing system following the tail flame of a rocket;

FIG. 2 is a schematic diagram illustrating a transition between operating conditions of the water spray noise reduction system;

FIG. 3 is a block diagram of a nozzle;

FIG. 4 is a schematic diagram of the gas supply system;

FIG. 5 is a diagram of a water jet noise reduction system;

FIG. 6 is a view of the launch pad catch basin layout;

wherein: 1-high automatic water spraying noise reduction system, 2-nozzle, 3-water spraying pipeline, 4-water spraying pipeline bracket, 5-pneumatic butterfly valve I, 6-pneumatic butterfly valve II, 7-manual butterfly valve, 8-water supply main pipe, 9-diversion trench, 10-water spraying branch pipe drain pipe, 11-drain pipe, 12-rocket, 13-engine, 14-tail flame boundary, 15-launching platform, 16-launching tower, 17-noise reduction water tank, 18-drainage channel, 19-square cavity, 20-rectangular hole, 21-rectangular hole, 22-drainage cut-off ditch, 23-vertical drain pipe, 24-diversion trench outlet, 25-launching field level ground, 26-drain pipe pneumatic butterfly valve, 27-high pressure gas bottle group, 28-pneumatic electric valve box, 29-shut-off valve, 30-corrugated pipe and 31-underground comprehensive pipe gallery.

Detailed Description

The invention is described in detail below by way of example with reference to the accompanying drawings.

As shown in attached figures 1 and 2, the invention provides a high-position automatic water spraying and noise reducing system following rocket tail flames, which comprises a nozzle 2, a water spraying pipeline 3, a quick valve control system, an air supply system, a water supply system and a water drainage system.

Wherein, water supply system is located launching tower 16 upper portion, and nozzle 2 connects to water supply system through water spray pipe 3, and nozzle 2 evenly arranges both sides around the launching station, and the nozzle 2 is stable after spraying water the water spray scope can cover launching pad 15, is used for arranging the guiding gutter 9 that leads the gas efflux and cool the steam of making an uproar that falls under launching pad 15, and gas efflux and steam lead out launching terrace 25 through guiding gutter export 24, as shown in figure 6.

The quick valve control system is arranged on the water spraying pipeline 3, the system short-range water spraying is realized before the engine 13 of the rocket 12 is ignited, the system long-range water spraying is realized at a certain moment after the rocket 12 is ignited and takes off, when the tail end of the rocket 12 crosses the nozzle 2, the sprayed water reaches the jet flow tail flame boundary 14 of the engine, and the conversion time interval of the short-range water spraying working condition and the long-range water spraying working condition is 1 s.

As shown in fig. 3, the nozzle 2 is placed at the end of the water spray pipe 3, the nozzle inlet is a square chamber 19 ending in an initially rectangular hole 20 which is then gradually deformed to a more flat rectangular hole 21. The nozzle outlet flat rectangular aperture 21 has a smaller cross-sectional area than the original rectangular aperture 20. The nozzle outlet has two deformation directions, one is that the both sides wall in square chamber expands to both sides on the plane of nozzle 2, is the sector and sprays out, and another deformation direction is that the upper and lower bottom surface in square chamber contracts to the center in the thickness direction of nozzle, and the rectangular hole width narrows.

The quick valve control system comprises a pneumatic butterfly valve I5, a pneumatic butterfly valve II 6, a manual butterfly valve 7 and an air supply system, wherein the manual butterfly valve 7 is used when the pneumatic butterfly valve is overhauled, and the system is in an open state before running. Before the rocket engine ignites, start I5 to aperture a of pneumatic butterfly valve, then start II 6 of pneumatic butterfly valve to opening entirely, realize the short range water injection of system, the rocket ignites a certain moment after taking off, starts I5 of pneumatic butterfly valve from aperture a to aperture b, realizes the long-range water injection of system. The control system realizes the remote control of the pneumatic butterfly valve I5 and the pneumatic butterfly valve II 6, and the control time sequence can be flexibly bound according to different rocket launching time sequences.

As shown in fig. 4, the air supply system includes an air distribution plate, a high pressure air bottle group 27, an air-electric valve box 28 and a shut-off valve 29, and supplies compressed air as an operation air source to the pneumatic butterfly valve i 5, the pneumatic butterfly valve ii 6 and the drain pipe pneumatic butterfly valve 26 in the rapid valve control system, and supplies air to the pneumatic butterfly valve i 5, the pneumatic butterfly valve ii 6 and the drain pipe pneumatic butterfly valve 26 in an online manner.

As shown in fig. 1 and 5, the water supply system is a noise reduction water tank 17 and a water supply main pipe 8 which are positioned on the upper part of the launching tower, the water amount is supplied to an underground comprehensive pipe gallery 31 of a launching station through the two water supply main pipes 8, a water spray pipeline 3 is led from the water supply main pipes 8, a corrugated pipe 30 is arranged after the water spray pipeline 3 goes out of the ground, a water spray pipeline support 4 is arranged on the ground to support the water spray pipeline 3, the corrugated pipe 30 is used for inhibiting the pipeline vibration caused by water attack effect and jet impact, and the tail end of the water supply main pipe 8 is connected with a drain pipe 11.

The drainage system comprises a terrace drainage part and a pipeline residual water drainage part. As shown in fig. 6, the drainage of the field is realized by using the intercepting ditch 22 located at the periphery of the launching station, the bottom of the intercepting ditch is connected with the vertical drainage pipe 23, the intercepting ditch cover plate is arranged above the intercepting ditch cover plate, the intercepting ditch cover plate covers the intercepting ditch at ordinary times, the daily operation is convenient, after the launching process is carried out, all the intercepting ditch cover plates are automatically removed by the automatic paving and removing vehicle, the large-flow water spraying and timely collection are realized, and the field is prevented from being accumulated with water and being frozen in a large range in winter. The residual water in the pipeline is discharged to the drainage channel 18 in the underground comprehensive pipe gallery 31 by using the water spraying branch pipe drainage pipe 10 connected to the water spraying pipeline 3 and the drainage pipe 11 at the bottom of the water supply main pipe 8 and controlling the pneumatic butterfly valve 26 of the drainage pipe, and then is discharged to the low-lying position outside the launching field ground 25.

In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.