CN113188819B - Rocket launching water spraying noise reduction effect evaluation method - Google Patents
Rocket launching water spraying noise reduction effect evaluation method Download PDFInfo
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Abstract
The invention relates to a rocket launching water spraying noise reduction effect evaluation method, which comprises the following steps: in the rocket launching process, the sound pressure level of the gas flow noise is detected through a noise sensor, and the takeoff height of the rocket is detected through a displacement sensor; in the same chart, drawing a sound pressure level curve of the change of the sound pressure level of the gas flow noise along with time and a height curve of the change of the takeoff height of the rocket along with time; according to the height curve, judging the corresponding time T when the takeoff height of the rocket is H ═ 30-40D; according to the sound pressure level curve, judging the sound pressure level SPL corresponding to T 02 And sound pressure level extreme value SPL before rocket takes off 01 And will Δ SPL 12 As the noise reduction amplitude of the combined work of primary water spraying and secondary water spraying, wherein, the delta SPL 12 ≥SPL 02 ‑SPL 01 And D represents the nozzle diameter of the rocket engine. The method has the advantages of simple process, easy realization and high reliability.
Description
Technical Field
The invention relates to a water spraying noise reduction technology, in particular to a rocket launching water spraying noise reduction effect evaluation method.
Background
In the aerospace field, high temperature, high velocity gas streams generated by rocket launches are accompanied by intense noise, which typically has sound pressure levels in excess of 160 dB. The device is influenced by the disturbance of the complex structure of the launching system, the gas flow noise can be transmitted to the space where the measuring, launching and controlling instrument is arranged due to the change of the transmission direction, electrical components of the measuring, launching and controlling instrument are sensitive to strong noise, the failure of the measuring, launching and controlling instrument is easily caused, and the safety of rocket launching is influenced. In order to control the noise of the gas flow generated by rocket launching, the water spraying noise reduction technology is mainly adopted in the field, a certain proportion of water flow is used for intervening in the high-temperature and high-speed gas flow, and the purposes of inhibiting the noise sound effect of the gas flow and blocking the gas flow noise from spreading to the periphery are achieved through mutual momentum and energy exchange. The effectiveness of water spray noise reduction is relatively easy to qualitatively analyze, but how to quantitatively evaluate the specific effect brought by water spray noise reduction, no reliable technical means exists in the field at present, and the main reasons are as follows: at the present stage, because the pneumatic noise theory and the water-spraying multiphase flow gas flow field theory are not mature, the specific water-spraying noise reduction effect is difficult to obtain through theoretical analysis; secondly, because the gas flow noise in the emission center area is strong, the existing noise sensor can detect data single deviation phenomenon in different degrees in the environment above 165dB, the sound intensity of the emission center area cannot be accurately detected, but the emission center area is just the main action area for water spraying and noise reduction; thirdly, water spraying and noise reduction are adopted as main technical means for guaranteeing rocket launching safety, launching tasks without water spraying and noise reduction cannot be carried out in the field without safety risks, a gas flow noise reference model without water spraying and noise reduction cannot be established, and a comparison basis cannot be provided for evaluating water spraying and noise reduction effects.
Disclosure of Invention
The invention aims to provide a rocket launching water spraying noise reduction effect evaluation method which has the advantages of simple process, easiness in realization, good safety and high reliability.
In order to solve the problems in the prior art, the invention provides a rocket launching water spraying noise reduction effect evaluation method, which comprises the following steps:
s1, in the rocket launching process, detecting the sound pressure level of gas flow noise through a noise sensor, and detecting the takeoff height of the rocket through a displacement sensor;
s2, drawing a sound pressure level curve of the gas flow noise with time variation and a height curve of the rocket takeoff height with time variation in the same graph;
s3, according to the height curve, judging the corresponding time T when the takeoff height of the rocket is H, wherein H is determined by calculation of a formula,
H＝(30～40)D ①
s4, judging the sound pressure level SPL corresponding to T according to the sound pressure level curve 02 And sound pressure level extreme value SPL before rocket takes off 01 And calculating the delta SPL according to a formula 2 12 Δ SPL 12 As the noise reduction amplitude when the primary water spraying and the secondary water spraying work together,
ΔSPL 12 ≥SPL 02 -SPL 01 ②
in the formula (I), D represents the diameter of a nozzle of the rocket engine.
Further, the method for evaluating the water spraying and noise reducing effect of rocket launching further comprises the following steps:
s5, judging the maximum noise reduction amplitude delta SPL of the secondary water spray according to the opening time of the secondary water spray and the variation trend of the sound pressure level curve 2a And stabilizing the noise reduction amplitude Δ SPL 2b ，ΔSPL 2a The intercept of the sound pressure level curve variation trend of the initial stage of the two-stage water spraying work deviating from the sound pressure level curve variation trend of the first-stage water spraying independent work is Delta SPL 2a The intercept of the sound pressure level curve variation trend of the stable stage of the secondary water spraying work deviating from the sound pressure level curve variation trend of the independent work of the primary water spraying.
Further, the method for evaluating the water spraying and noise reducing effect of rocket launching further comprises the following steps:
s6, deducing the sound pressure level SPL corresponding to the T when the primary water spray works independently according to the sound pressure level curve change trend before the secondary water spray is started 03 And calculating the delta SPL according to a formula 1 Δ SPL 1 As the noise reduction amplitude of the primary water spray,
ΔSPL 1 ≥SPL 03 -SPL 01 -ΔSPL 2a ≥ΔSPL 12 +ΔSPL 23 -ΔSPL 2a ③
formula III, Δ SPL 23 Is SPL 03 And SPL 02 The difference of (c).
Furthermore, the rocket launching is carried out based on a launching system, the launching system comprises a launching platform, a launching tower, a primary water spraying device and a secondary water spraying device, the launching platform is used for bearing the rocket, the launching tower is arranged on one side of the launching platform, and the primary water spraying device and the secondary water spraying device are arranged around the launching platform.
Further, the invention relates to a rocket launching water spraying noise reduction effect evaluation method.
Further, the method for evaluating the water spraying and noise reducing effect of rocket launching is characterized in that an intersection point of an axis of a core-grade engine nozzle of the rocket and a launching platform is taken as a launching center, the noise sensor is arranged on a launching tower or the rocket, the distance from the noise sensor to the launching center is L, and L is not less than (30-40) D.
Compared with the prior art, the rocket launching water spraying noise reduction effect evaluation method has the following advantages: according to the invention, according to the different intensity of the reflection effect of the launching system on the gas flow noise at different stages of rocket launching, the relatively accurate water spraying noise reduction result can be obtained by combining the takeoff height of the rocket and the variation trend of the sound pressure level curve of the gas flow noise before and after water spraying noise reduction, and an effective technical means is provided for quantitatively evaluating the specific effect of the water spraying noise reduction. The method specifically comprises the following steps: the water-spraying noise reduction effect can be quantitatively evaluated relatively accurately according to the sound pressure level curve of the gas flow noise and the rocket takeoff height curve by utilizing the characteristic and according to the sound pressure level curve of the gas flow noise and the rocket takeoff height curve, and the water-spraying noise reduction effect has the advantages of simple method, easiness in realization, good safety and high credibility.
The following describes a method for evaluating the noise reduction effect of water injection during rocket launching in further detail with reference to the specific embodiments shown in the drawings.
Drawings
FIG. 1 is a flow chart of a rocket launching water-spraying noise reduction effect evaluation method according to the invention;
FIG. 2 is a schematic diagram of a rocket launch system;
FIG. 3 is a graph of rocket takeoff altitude and gas stream noise sound pressure level over time.
Detailed Description
First, it should be noted that, the directional terms such as up, down, left, right, front, rear, etc. described in the present invention are only described with reference to the accompanying drawings for easy understanding, and do not limit the technical solution and the claimed scope of the present invention.
As shown in fig. 1 to fig. 3, the specific implementation of the method for evaluating the noise reduction effect of water spraying during rocket launching of the invention comprises the following steps:
s1, in the rocket launching process, the sound pressure level of the gas flow noise is detected through the noise sensor, and the takeoff height of the rocket is detected through the displacement sensor.
And S2, drawing a sound pressure level curve of the gas flow noise sound pressure level along with the change of time and a height curve of the rocket takeoff height along with the change of time in the same chart.
S3, according to the height curve, judging the corresponding time T when the takeoff height of the rocket is H, wherein H is determined by calculation of a formula,
H＝(30～40)D ①
s4, judging the sound pressure level SPL corresponding to the T according to the sound pressure level curve 02 And sound pressure level extreme value SPL before rocket takes off 01 And calculating the delta SPL according to a formula 2 12 Δ SPL 12 As the noise reduction amplitude when the primary water spraying and the secondary water spraying work together,
ΔSPL 12 ≥SPL 02 -SPL 01 ②
in the formula (I), D represents the diameter of a nozzle of the rocket engine.
According to the invention, according to the different intensity of the reflection effect of the launching system on the gas flow noise at different stages of rocket launching, the relatively accurate water spraying noise reduction result can be obtained by combining the takeoff height of the rocket and the variation trend of the sound pressure level curve of the gas flow noise before and after water spraying noise reduction, and an effective technical means is provided for quantitatively evaluating the specific effect of the water spraying noise reduction. The method specifically comprises the following steps: the water-spraying noise reduction effect can be quantitatively evaluated relatively accurately according to the sound pressure level curve of the gas flow noise and the rocket takeoff height curve by utilizing the characteristic and according to the sound pressure level curve of the gas flow noise and the rocket takeoff height curve, and the water-spraying noise reduction effect has the advantages of simple method, easiness in implementation, good safety and high reliability. It should be noted that the initial stage of rocket launching refers to the stage before the rocket flies freely, and includes the stage without taking off and the stage taking off to the height H. Practical application shows that according to different rocket launching systems, the takeoff height of the rocket starts to gradually approach to a free flight state when reaching (30-40) D, the reflection of the launching system to the gas flow noise is weak, the rocket free flight state refers to a state that the gas flow noise is not influenced by the reflection of the launching system, and the value of H is determined according to the specific rocket launching system. For a single nozzle rocket, D represents the diameter of the engine nozzle, while for a multi-nozzle rocket, D represents the diameter of the largest nozzle in the core stage engine and the booster engine.
As an optimization scheme, the method for evaluating the water spraying and noise reducing effect of rocket launching further comprises the following steps:
s5, judging the maximum noise reduction amplitude delta SPL of the secondary water spray according to the opening time of the secondary water spray and the variation trend of the sound pressure level curve 2a And stabilizing the noise reduction amplitude Δ SPL 2b ，ΔSPL 2a The intercept of the sound pressure level curve variation trend of the initial stage of the two-stage water spraying work deviating from the sound pressure level curve variation trend of the first-stage water spraying independent work is Delta SPL 2a The intercept of the sound pressure level curve variation trend of the stable stage of the secondary water spraying work deviating from the sound pressure level curve variation trend of the independent work of the primary water spraying.
The opening time of the secondary water spraying is earlier than the time when the takeoff height of the rocket reaches H, after the secondary water spraying starts to inhibit the gas flow noise, the sound pressure level curve of the gas flow noise can deviate from the original variation trend, and the amplitude intercept of the deviation of the original variation trend is the noise reduction amplitude of the secondary water spraying. Since the fluctuation of the initial stage of the two-stage water spraying work is large, the delta SPL is adjusted 2a As the maximum noise reduction amplitude of the secondary water spraying, when the secondary water spraying works relatively stably and continuously takes off and lands noise, the noise reduction amplitude can gradually recover the original variation trend, so that the delta SPL is adjusted 2b As the stable noise reduction amplitude of the secondary water spray. It should be noted that the ignition of the rocket and the primary water injection are simultaneously started to ensure the safe and reliable launching of the rocket, and the starting time of the primary water injection and the secondary water injection is set conventionally in the field.
As an optimization scheme, the method for evaluating the water spraying and noise reducing effect of rocket launching further comprises the following steps:
s6, changing according to the sound pressure level curve before the secondary water spray is startedTrend is changed, and the sound pressure level SPL corresponding to the T when the first-level water spray works independently is deduced 03 And calculating the delta SPL according to a formula 1 Δ SPL 1 As the noise reduction amplitude of the primary water spray,
ΔSPL 1 ≥SPL 03 -SPL 01 -ΔSPL 2a ≥ΔSPL 12 +ΔSPL 23 -ΔSPL 2a ③
formula III, Δ SPL 23 Is SPL 03 And SPL 02 The difference of (a).
And deducing the sound pressure level corresponding to the T when the primary water spray works independently based on the sound pressure level curve change trend before the secondary water spray is started, and deducing the noise reduction amplitude of the primary water spray by combining the noise reduction amplitude when the primary water spray and the secondary water spray work jointly and the noise reduction amplitude of the secondary water spray.
It should be noted that, for a launching system provided with three-stage water spraying, the noise reduction amplitude of the three-stage water spraying can be deduced according to the method. In practical application, rocket launching is carried out based on a launching system, the launching system specifically comprises a launching platform 1, a launching tower 2, a primary water spraying device 3 and a secondary water spraying device 4, wherein the launching platform 1 is used for bearing a rocket 5, the launching tower 2 is arranged on one side of the launching platform 1, and the primary water spraying device 3 and the secondary water spraying device 4 are arranged around the launching platform 1. To facilitate the arrangement of the devices and the diversion of the fuel gas flow, the invention generally provides the launch platform 1 and the launch tower 2 on the launch pad 6, with the launch pad 6 being provided with a diversion trench 7 on the underside of the launch platform 1. If the intersection point of the core-level engine nozzle axis of the rocket and the launching platform is taken as the launching center, the noise sensor is usually arranged on the launching tower or the rocket, the distance L between the noise sensor and the launching center is larger than or equal to (30-40) D, so that the phenomenon that the noise sensor is affected by gas flow to cause data detection single deviation is avoided, and the phenomenon that the noise sensor with a large range is used as far as possible to cause data detection overranging is avoided.
The core of the method is to evaluate the water spraying noise reduction effect according to the difference between the noise intensity in the free flight state of the rocket and the noise intensity in the initial launching stage (water spraying noise reduction action time period), and the evaluation method has wide application range without loss of generality. Although the invention only provides the noise reduction effect evaluation method of the two-stage water spraying, the invention is also applicable to the emission system which is only provided with the one-stage water spraying or is provided with more than three stages.
The above examples are only for describing the preferred embodiments of the present invention, and do not limit the scope of the claimed invention, and various modifications made by those skilled in the art according to the technical solutions of the present invention should fall within the scope of the invention defined by the claims without departing from the design concept of the present invention.
Claims (4)
1. A rocket launching water spraying noise reduction effect evaluation method is characterized by comprising the following steps:
s1, in the rocket launching process, detecting the sound pressure level of gas flow noise through a noise sensor, and detecting the takeoff height of the rocket through a displacement sensor;
s2, drawing a sound pressure level curve of the gas flow noise with time variation and a height curve of the rocket takeoff height with time variation in the same graph;
s3, according to the height curve, judging the corresponding time T when the takeoff height of the rocket is H, wherein H is determined by formula I,
H＝(30～40)D ①
s4, judging the sound pressure level SPL corresponding to the T according to the sound pressure level curve 02 And sound pressure level extreme value SPL before rocket takes off 01 And calculating the delta SPL according to a formula 2 12 Δ SPL 12 As the noise reduction amplitude when the primary water spraying and the secondary water spraying work together,
ΔSPL 12 ≥SPL 02 -SPL 01 ②
in the formula I, D represents the diameter of a nozzle of the rocket engine;
further comprising the steps of:
s5, judging the maximum noise reduction amplitude delta SPL of the secondary water spray according to the opening time of the secondary water spray and the variation trend of the sound pressure level curve 2a And stabilizing the noise reduction amplitude Δ SPL 2b ，ΔSPL 2a The intercept of the sound pressure level curve variation trend of the initial stage of the two-stage water spraying work deviating from the sound pressure level curve variation trend of the first-stage water spraying independent work is Delta SPL 2a The intercept of the sound pressure level curve variation trend deviating from the sound pressure level curve variation trend of the first-stage water spraying independent work in the second-stage water spraying work stable stage;
s6, deducing the sound pressure level SPL corresponding to the T when the primary water spray works independently according to the sound pressure level curve change trend before the secondary water spray is started 03 And calculating the delta SPL according to a formula 1 Δ SPL 1 As the noise reduction amplitude of the primary water spray,
ΔSPL 1 ≥SPL 03 -SPL 01 -ΔSPL 2a ≥ΔSPL 12 +ΔSPL 23 -ΔSPL 2a ③
formula III, Δ SPL 23 Is SPL 03 And SPL 02 The difference of (a).
2. A rocket launching water spraying and noise reducing effect evaluation method according to claim 1, wherein the rocket launching is performed based on a launching system, the launching system comprises a launching platform (1), a launching tower (2), a primary water spraying device (3) and a secondary water spraying device (4), the launching platform (1) is used for bearing a rocket (5), the launching tower (2) is arranged at one side of the launching platform (1), and the primary water spraying device (3) and the secondary water spraying device (4) are arranged around the launching platform (1).
3. A rocket launching water spraying and noise reducing effect evaluation method according to claim 2, wherein the launching platform (1) and the launching tower (2) are arranged on a launching terrace (6), and the launching terrace (6) is provided with a diversion trench (7) at the lower side of the launching platform (1).
4. The method for evaluating the water spraying and noise reducing effect during rocket launching according to claim 3, wherein the intersection point of the axis of the core-grade engine nozzle of the rocket (5) and the launching platform (1) is taken as a launching center, the noise sensor is arranged on the launching tower (2) or the rocket (5), the distance from the noise sensor to the launching center is L, and L is more than or equal to 30D.
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103712808A (en) * | 2012-09-29 | 2014-04-09 | 北京航天发射技术研究所 | Detection system for single-jet-pipe rocket launch water-spray cooling noise-reduction effect |
| CN109974847A (en) * | 2019-03-26 | 2019-07-05 | 北京航天发射技术研究所 | Carrier rocket emits jet noise detection method |
| CN109974541A (en) * | 2019-03-26 | 2019-07-05 | 北京航天发射技术研究所 | Multi nozzle rocket dynamic jet test system |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108871060B (en) * | 2018-06-29 | 2021-03-26 | 北京航天发射技术研究所 | Emission system with functions of inhibiting peripheral and high-order jet flow noise by water spraying |
| CN109974523B (en) * | 2019-03-26 | 2022-07-29 | 北京航天发射技术研究所 | Multi-nozzle rocket jet test system |
-
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- 2021-04-12 CN CN202110388667.3A patent/CN113188819B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103712808A (en) * | 2012-09-29 | 2014-04-09 | 北京航天发射技术研究所 | Detection system for single-jet-pipe rocket launch water-spray cooling noise-reduction effect |
| CN109974847A (en) * | 2019-03-26 | 2019-07-05 | 北京航天发射技术研究所 | Carrier rocket emits jet noise detection method |
| CN109974541A (en) * | 2019-03-26 | 2019-07-05 | 北京航天发射技术研究所 | Multi nozzle rocket dynamic jet test system |
Non-Patent Citations (4)
| Title |
|---|
| "单喷管液体火箭发射喷流噪声模拟试验研究";陈劲松等;《空气动力学学报》;20151231;第33卷(第6期);全文 * |
| "An overview of research activity at the launch systems tested";Kandula B V M.;《Stockholm: Tenth International Congress on Sound and Vibration》;20031231;全文 * |
| "单喷管火箭发射喷水降噪机理研究";陈劲松等;《导弹与航天运载技术》;20151031;第38卷(第5期);正文的第0-2部分 * |
| "大型火箭发射喷水降噪技术研究进展";陈劲松等;《导弹与航天运载技术》;20190430;第42卷(第2期);全文 * |
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