CN110136683A - A kind of space launching site tank is deflated and blow-line purging's noise silencer - Google Patents
A kind of space launching site tank is deflated and blow-line purging's noise silencer Download PDFInfo
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- CN110136683A CN110136683A CN201910326995.3A CN201910326995A CN110136683A CN 110136683 A CN110136683 A CN 110136683A CN 201910326995 A CN201910326995 A CN 201910326995A CN 110136683 A CN110136683 A CN 110136683A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
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- G—PHYSICS
- G10—MUSICAL INSTRUMENTS; ACOUSTICS
- G10K—SOUND-PRODUCING DEVICES; METHODS OR DEVICES FOR PROTECTING AGAINST, OR FOR DAMPING, NOISE OR OTHER ACOUSTIC WAVES IN GENERAL; ACOUSTICS NOT OTHERWISE PROVIDED FOR
- G10K11/00—Methods or devices for transmitting, conducting or directing sound in general; Methods or devices for protecting against, or for damping, noise or other acoustic waves in general
- G10K11/16—Methods or devices for protecting against, or for damping, noise or other acoustic waves in general
- G10K11/162—Selection of materials
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Abstract
For carrier rocket in launching site test emission process, tank, which is deflated, seriously affects the proper testing of working site and the physical and mental health of staff considerably beyond 85 decibels of national permitting deformation with the audible noise that can generate about 120 decibels when blow-line purging.The noise generating mechanisms when present invention is by tank deflation and blow-line purging are analyzed, the noise-related parameters such as gas Mach number, gas flow rate, resistance coefficient, tube outlet flow velocity are calculated, devise the deflation of the space launching site tank based on metal microperforated panel and the dedicated noise silencer of blow-line purging in conjunction with the environmental demand at launching site.The silencing means that the present invention designs can deflate carrier rocket tank with lower noise when blow-line purging to 85 decibels hereinafter, reaching the noise permissible criterion of national regulation, solve the problems, such as that launching site tank is deflated and noise pollution caused by blow-line purging.
Description
Technical field
The invention belongs to Aerospace tests to emit field, be related to a kind of space launching site carrier rocket tank and deflate and pipeline
The dedicated silencing means that the noise occurred when blowing is eliminated.
Background technique
In launching site test emission process, dynamical system Rocket tank generates carrier rocket when deflating with blow-line purging
Noise about at 120 decibels or so, considerably beyond 85 decibels of national permitting deformation, having seriously affected working site is respectively
System works normally and the physical and mental health of Field Force.Country launching site reduces rocket without dedicated muffling device at present
Tank is deflated and the noise of blow-line purging, can only individually arrange this to work and reduce Field Force to the greatest extent.It is therefore desirable to set
Dedicated silencing means is counted, tank is deflated and is reduced to safety requirements value with the noise in blow-line purging hereinafter, guaranteeing live people
The health and proper testing environment of member.Secondly, rocket system to test workshop purity requirements it is quite high, therefore use with
Sound-absorbing material is infeasible to cut down noise reduction scheme based on the resistive muffler of noise；Resistant noise-reducing device noise reduction frequency band is narrow, to height
Frequency erasure effect is poor；Impedance complex formula muffler service life is short, same infeasible.
Summary of the invention
The present invention, which analyses in depth, to be calculated space launching site tank and deflates and the mechanism of production of noise and specific when blow-line purging
Data, requirement and national noise permissible criterion in conjunction with launching site to site environment, devise a kind of space launching site liquid fire
Arrow tank is deflated and pipeline high pressure blows down dedicated silencing means.
Space launching site tank of the invention deflate and when blow-line purging silencing means implementation it is as follows: first into
The deflation of row tank and the noise genetic analysis of blow-line purging and relevant parameter calculate；Secondly to metal microperforated panel erasure effect
Analytical calculation is carried out with parameter setting；Finally, designing the silencing means structure and parameter met the requirements and being carried out to erasure effect
Verifying.
The space launching site tank that the present invention designs is deflated and blow-line purging's silencing means is shown in that specific embodiment part is retouched
It states.
Space launching site tank of the invention is deflated is with the advantages of blow-line purging's silencing means:
(1) present invention deflates tank with 120 decibels or more lower noises of generation during blow-line purging to 85 decibels
Hereinafter, reaching the noise permissible criterion of national regulation, solves launching site tank and deflate and the dirt of noise caused by blow-line purging
Dye；
(2) present invention devises based on metal microperforated panel noise elimination structure, supplemented by resistance filtering and decompression and expansion section
Space launching site tank deflate and the dedicated noise silencer of blow-line purging, will not to test environment pollute, meet hair
Penetrate the high-cleanness, high requirement of field test environment；
(3) silencing means of the invention is installed and used convenient reliable, and can be generalized to rocket general assembly factory etc., other are related single
Position, eliminating aspect to civilian exhaust noise also has very big reference function, and application prospect is good.
Detailed description of the invention
Fig. 1 silencing apparatus schematic diagram.
The mobility status of Fig. 2 gaseous blast；
The Noisy acoustic power that Fig. 3 gaseous blast primitive is radiated；
Fig. 4 unitary pipe flow diagram；
Fig. 5 Rocket tank deflation parameter calculates
Fig. 6 bilayer microperforated panel sound absorbing performance schematic diagram；
Noise elimination curve of the micro- formula silencer of Fig. 7 under different in flow rate；
Fig. 8 silencer microperforated panel structure division sound absorbing performance schematic diagram；
Specific embodiment
Step 1: launching site tank is deflated and the noise generating mechanisms of blow-line purging are analyzed
Air pertormance noise is the unstable process due to gas, the disturbance of gas in other words, gas and object phase
Interaction and generate.The continuity equation of turbulent gas is
ρ in formula --- density；νi--- air-flow is in xiSpeed on direction；T --- the time；Q --- unit time unit
The emission measure in the source of volume.
The equation of motion is
F in formulai--- the generalized force of unit volume；ρνiνj--- shear pressure tensor；pij--- with compression and viscous
The related tensor of stress of power.
Time diffusion is carried out to formula (1), (2) formula carries out xiDifferential, being computed can obtain
In formula
During tank is deflated with blow-line purging, 1,3 two on the right of (3) formula is constantly changing, to makeMoment is changing, i.e., gas density is changing always, its specific manifestation form is exactly in unit volume
Gas molecula number is persistently changing, to generate air pertormance noise.
1 jet noise
Rocket body tank is deflated and the process of blow-line purging is a kind of exhaust emptying process of pressure pan, in this process, by
Turbulent mixture occurs in the gas particle of hypervelocity and the low velocity gas particle of surrounding, destroys the stable state of atmosphere
And huge disturbance is generated, this generates powerful jet noises.
For air pertormance noise, for sound source characteristic, it can be mainly divided into three classes: Dan Yuan, double source, quadrapole
Source.The jet noise that tank is deflated and blow-line purging generates substantially belongs to quadrupole component for sound source characteristic.For four
Pole component, equation (3) can be reduced to
ρ in formula --- gas density；a0--- the velocity of sound in undisturbed medium；Tij--- the pressure of any point is answered in space
Power tensor.
Tensor of stress TijMainly by flow of momentum tensor ρ νiνjIt determines.It deflates and blow-line purging's process in rocket body tank
In, the variation of the active force is generated due to pressure change, and pressure change causes variable density, and here it is the sources of noise.
For far sound field, that is, the distance for leaving sound source is far longer than the point of the size of sound source and the size of wave length of sound, side
The solution (being indicated with acoustical power) of journey (5) is
ρ in formulac,ρ0--- the density of gaseous blast and surrounding medium；Tc,T0--- the absolute temperature of gaseous blast and surrounding medium
Degree；vc--- gaseous blast speed；D --- nozzle diameter；K --- proportionality coefficient can obtain K=2.8 × 10 by experimental data-5。
The acoustical power of jet noise is directly proportional to the eight power of gaseous blast speed, meanwhile, the acoustical power of jet noise also with
The factors such as nozzle diameter, gas density, medium temperature are related.
The mobility status of gaseous blast is as shown in Figure 2.Entire air-flow is divided into two parts: initial segment part and main paragraph portion
Point.Initial segment has determining core speed, and length is about 5 times of nozzle diameter.Main paragraph extends farther.Fig. 3 is
The acoustical power variation relation of the gaseous blast partial radiation of spout different distance X is left, i.e.,With the relationship of X/D.Away from
The initial segment part of 5 times of diametral distances of spout, the noise acoustical power of primitive volume radiation account for the half of entire gaseous blast acoustical power
More than, and the noise acoustical power of each primitive volume radiation and the primitive volume position for leaving spout are almost unrelated.Separate
The main paragraph part of spout, the acoustical power that gaseous blast primitive volume is radiated is with 7 powers of the distance for leaving spout and sharply
Ground decline.Therefore, gaseous blast noise is mainly as caused by the jet section in a distance from 6 times from spout diameters.This point pair
The control of jet noise is of great significance.
Gaseous blast near spout mainly radiates high frequency noise, and by reason of heavy pressure, flow velocity it is high, the noise of radiation
Sound level is quite high.With the increase for leaving jet opening distance, low frequency part is gradually increased.The intensity of jet noise is in different directions
Also different.It is obtained by experiment, maximum radiation occurs in jet shaft angle degreeWithin.
2 sounds of the wind
Jet noise is the principal element that tank is deflated with blow-line purging's noise, secondly because flow velocity is larger when deflating, gas
The sound of the wind that stream impacts extraneous free air and generates also be can not ignore.During tank is deflated with blow-line purging, due to air-flow
It impacts extraneous static atmosphere and generates sound of the wind, main component is vortex and vortex breakdown noise.
The acoustical power of sound of the wind sharp increases with the increase of air velocity, it is directly proportional to 6 powers of speed,
It is directly proportional to its 5.5 power when speed is smaller.Its cross-sectional area with object, frontal drag coefficient, gas density also have
It closes.It is indicated with mathematical form, is
W∝ρSξ2ν6, (7)
W in formula --- acoustical power；ρ --- gas density；The cross-sectional area of S --- object；The front resistance of ξ --- object
Force coefficient；ν --- gas flow rate.
By the derivation in step 1 it can be concluded that
(1) acoustical power of jet noise is directly proportional to the eight power of gaseous blast speed；
(2) gaseous blast noise is mainly as caused by the jet section in a distance from 6 times from spout diameters；
(3) frequency spectrum of jet noise is broad continuous spectrum, and the gaseous blast near spout mainly radiates high frequency noise,
Pressure is big, flow velocity is high, and the noise level of radiation is quite high, and with the increase for leaving jet opening distance, low frequency part is gradually increased；
(4) radiation of the maximum intensity of jet noise occurs in jet shaft angle degreeWithin；
(5) acoustical power of sound of the wind is directly proportional to 6 powers of speed when speed is larger, when speed is smaller, with its 5.5
Power is directly proportional.
It is calculated Step 2: launching site tank is deflated with the noise parameter during blow-line purging
It can be seen that in tank deflation course by above analysis, air velocity influences most the formation of noise
Greatly.Therefore the parameters such as flow velocity when tank is deflated are calculated first.To make the following assumptions and approximate convenient for calculating:
(1) deflation course is endothermic process, and gas temperature constantly reduces in tank, but to flow when temperature change is little
Influence is not significant, therefore it is invariable (calculating by 300K) that gas temperature in tank is approximately considered when calculating；
(2) gas has little time to carry out sufficient heat exchange with the external world deflation velocity in pipes is fast, flowing time is short, can be with
Approximation is calculated by the permanent pitometer of constant entropy unitary.
Relationship between physical quantity on 1 arbitrary section and stagnation state physical quantity
Stagnation state is the perfect condition that fluid velocity is zero, is indicated with subscript " 0 ", i.e. ν0=0 or M0=0 state,
Other each physical quantity T0、p0、ρ0It indicates.
For the unitary pipe stream being connected with bulk container, (such as Rocket tank deflation) is such as schemed since container volume is sufficiently large
Shown in 4, it is believed that the state in container is in the null stagnation state of speed.Then formula (8), (9), (10) just provide
Relational expression in container on physical quantity and pipe stream arbitrary section between physical quantity.
For column state equation in the presence of perfect gas
p0=ρ0RT0 (11)
Q=ρ ν A (14)
R in formula --- gas constant, the R=287J/KgK of air；A --- velocity of sound；Q --- gas flow；The ratio between gas constant pressure specific heat and specific heat at constant volume, γ=1.4 of air；A --- the area of pipe stream arbitrary cross section.
It can be obtained by formula (8)
It can be obtained by formula (8), (9), (11)
For CZ-2F rocket, known by data, level-one fires case T0Maximum discharge quantity when=300K is 1.5kg/s (empty
Gas), p0=0.35Mpa pacifies the valve export cross-sectional area that overflowsOutlet temperature T=270K.
It brings above data into formula (12), (13), (14), (15), (16), acquires maximum discharge quantity Q=1.502kg/s,
The data provided with data are very close, and it is applicable that explanation, which calculates tank deflation problem with above formula,.
Relationship between physical quantity on 2 arbitrary sections and critical state physical quantity
Critical state is state when fluid velocity is equal to local velocity of sound, is indicated with subscript " * ", i.e. V*=a*, a*It is critical
The velocity of sound, V*For critical speed, M at this time*=1, other each physical quantity T*、p*、 ρ*It indicates.
Relational expression between physical quantity on arbitrary section and critical state physical quantity is
A in formula*For the area of section at M=1.
Parameter in 3 tank deflation courses calculates
According to the tank gas pressure of certain rocket series, tank gas temperature, pacify the parameters such as valve export internal diameter of overflowing, directly
Shi Anyi valve export temperature is arranged by obtained by experience, the applicability physical quantity on arbitrary section and stagnation state object
It is correct feasible for being verified in relationship between reason amount.Acquire gas Mach number, the gas flow rate under the section.It calculates
The data obtained is listed in Fig. 5.
As seen from Figure 5, as gas vent section internal diameter D=0.05m, air-flow maximum speed in 255m/s or so,
When gas vent section, internal diameter expands as D=0.2m, air-flow maximum speed is substantially reduced, only 12m/s or so.By front
Derivation in step 1 it is found that the acoustical power of the jet noise in tank deflation course and the eight power of gaseous blast speed at just
Than the acoustical power of sound of the wind and six powers of air-flow are directly proportional；Again by the step of back three it is found that propose meter with microperforated panel
Silencing means based on structure, gas flow rate is lower, and erasure effect is better；Combine wanting for silencing means outer dimension
It asks, the air stream outlet section internal diameter for selecting tank deflation silencing means is 0.05m.
Noise parameter in 4 blow-line purgings calculates
Certain rocket series require ground blow-line purging pressure be 4.1~5.1Mpa, hose specification have φ 6mm, φ 8mm,
Tri- kinds of φ 12mm, 5.1Mpa presses in maximum blowoff pressure herein, and caliber is calculated by φ 12mm, and the silencing means of design can in the future
Take into account the blow-line purging of these three specifications.Due to gas flow rate height, pipeline is longer when blowing, and soft pipeline portions are ripples
Pipe, hard tube have a few place's bendings, calculate so to be insulated pipe flow friction according to unitary.
(1) resistance coefficient calculates
For hose road, in maximum stream flow subordinate rough region pipe stream, so coefficient of frictional resistance
Coefficient of partial resistance ξl=0.20；Hard tube equivalent roughness takes Δ=0.19mm, bore D1=0.012m, pipe range
Take l1=5m, then
Coefficient of partial resistance ξ1=0.318, total drag coefficients when blow-line purging:
F=fl+ξl+f1+ξ1=115+0.20+14.6+0.318=130.118, takes f=130.
(2) tube outlet gas flow rate
The mass flow formula for having the adiabatic flow in pip of frictional resistance is
G=ρ1v1A1=ρ2v2A2 (27)
Bernoulli equation
It is obtained by formula (27), (28), (29)
Nozzle flow velocity when calculating blow-line purging is in 265m/s or so, and when air stream outlet section, internal diameter expands as D=
When 0.05m, gas flow rate can be controlled in 12m/s or so.It is similarly managed with tank deflation silencing means air stream outlet internal diameter is determined
By determining that blow-line purging's silencing means air stream outlet internal diameter is more than or equal to 0.05m.
Step 3: space launching site tank is deflated and blow-line purging's noise silencer is designed and realized
1 metal microperforated panel soundabsorbing construction
Metal microperforated panel soundabsorbing construction be 1 millimeter of plate thickness hereinafter, aperture φ 1 hereinafter, punching rate 0.5-5% metal
The compound sound-absorption structural of microperforated panel and cavity composition.Microperforated panel soundabsorbing construction is the sound simultaneously with acoustic resistance and acoustic mass
Learn element；Its cavity has the function of acoustic compliance again simultaneously, collectively constitutes a resonance system with microperforated panel.
The opposite acoustic resistance of metal microperforated panel soundabsorbing construction and opposite acoustic mass are respectively
Wherein kr、kmRespectively acoustic resistance constant and acoustic mass constant.
The resonant frequency of microperforated panel soundabsorbing construction is
Microperforated panel soundabsorbing construction resonate when acoustic absorptivity be
For microperforated panel, α value is generally 0.90 or more, and absorbing angular frequency width, (frequency bandwidth is multiplied by 2
π) it is substantially equal to acoustic resistance rAWith acoustic mass mAThe ratio betweenBy its available ratio of formula (33)-(36)
By formula (39) as it can be seen that aperture d is smaller,Bigger, therefore, diameter is less than the microperforated panel of 1mm, can obtain ratio
The much broader wide band sound absorption of conventional punch plate.
Usual microperforated panel uses double-layer sound absorbing structure, to obtain bigger wide band sound absorption.There are two the above resonance at this time
Peak, resonant frequency are
Antiresonant frequency
Fig. 6 is the double-deck microperforated panel sound absorbing performance schematic diagram.As it can be seen that the double-deck microperforated panel by appropriately combined, can obtain
To very wide Absorber Bandwidth.
The relationship of 2 air velocities and metal microperforated panel muffler performance muffler
When the air-flow of friction speed passes through muffler, different influences is generated to performance muffler.One in static and low speed
The lower good muffler of erasure effect, when high-speed flow passes through, effect may degenerate significantly.Sometimes design it is improper or
It manufactures bad, is not only unable to noise reduction, or even the Noise Amplifier that can also make silencing means become certain frequencies.
Fig. 7 is noise reduction curve of the tubular type microperforated panel muffler (referred to as micro- formula muffler) under different in flow rate.It can see
Out, with the increase of flow velocity, sound-damping qualities are smaller and smaller, because the silencer element in muffler can not be made to very smoothly,
Air-flow can encounter barrier in advance and generate vortex, this is the principal element that regeneration noise is generated in muffler.In low speed
When, regeneration noise is also unobvious, but the regeneration noise that high speed when generates just be can not ignore.For micro- formula muffler, it is put down
Equal sound-damping qualities Δ LpThere is good linear relationship with lg ν.
The design of 3 silencing means and realization
Tank is deflated with during blow-line purging, and tank maximum pressure reaches 0.45Mpa, and blow-line purging's pressure exists
5.1Mpa or so, and atmospheric pressure is 0.1Mpa, pressure is high, and flow is big, and this requires silencing means to make with decompression and expansion
With to reduce differential pressure when exhaust.Meanwhile the noise spectrum of generation is broad continuous spectrum, and noise level is high,
Influence wide, deflation time is long, therefore it is required that the sound-damping qualities of silencing means are big, noise reduction frequency range is wide, proposed adoption microperforated panel noise reduction
Structure is main noise reduction section.In addition, being calculated by front it is found that gas flow rate is higher during deflating and blowing down, up to 250m/s
Left and right reduces gas flow rate so to expand the section of pipeline.
Silencing means design is divided into two parts.First part is resistance filtering and decompression and expansion part.Sound wave is in this paragraph
Sectional area mutation, perforated sheet, elbow etc. are encountered, due to the variation of acoustic impedance, makes quite a few sound energy reflection and loses；
Meanwhile the high pressure gas being discharged out of tank or pipeline makes pressure jump be changed into pressure by continuous decompression and expansion
Gradual change, flow velocity reduce noise level from becoming low speed at a high speed.Second part is microperforated panel noise-reducing structure and main noise reduction
Section.Microperforated panel noise-reducing structure is much higher than the erasure effect to high-speed flow, low speed gas to the erasure effect of low speed flow
Stream reaches the noise permissible criterion of national regulation by microperforated panel silencing means, noise.
Resistance filtering and decompression and expansion part, using with a thickness of 2mm, perforated plate diameter phi 10mm, punching rate 40%, plate
4 layers of annular slab of spacing 25mm form, and high-speed flow is in this section of flow process, and several times by perforated plate, rocket motor is cut
Area is gradually expanded, and gas pressure reduces, flow velocity decline.Simultaneously as the variation of acoustic impedance, part sound energy reflection is simultaneously lost
Fall.
Microperforated panel noise-reducing structure part, using thickness 0.8mm, the double-deck micropunch of two of perforated plate diameter phi 0.8mm
Plate.Ante-chamber depth 30mm, back cavity depth 70mm, front layer microperforated panel punching rate 2.5%, rear layer microperforated panel are obtained by formula (40), (41)
The resonant frequency of 2 formants of the double-deck microperforated panel of punching rate 1% is respectively 4322Hz, 315Hz, reflection resonance peak
Resonant frequency is 1281Hz.Ante-chamber depth 20mm, back cavity depth 10mm can be similarly obtained, front layer microperforated panel punching rate 5%, rear layer is micro-
The resonant frequency of 2 formants of the double-deck microperforated panel of perforated plate punching rate 3% is respectively 5790Hz, 3030Hz, anti-
The resonant frequency for penetrating formant is 3939Hz, and sound absorption qualities are as shown in Figure 8.As it can be seen that its noise reduction bandwidth is from centre frequency
315Hz (280-355) arrives centre frequency 6300Hz (5600-7100), up to the bandwidth of 14 third-octaves.It can according to (43) formula
, the average sound-damping qualities of perforated microstructure section are 37 decibels (air velocity ν is based on 13m/s).Therefore, entire silencing means
Sound-damping qualities are up to 40 decibels or more.Tank is deflated and blow-line purging's silencing means schematic diagram is as shown in Figure 1.
Launching site tank is deflated and blow-line purging's silencing means is pacified the valve that overflows with rocket body and connect using overflow connector knot
Structure, technology maturation, connection is reliable, while any damage will not be caused to rocket body quality.There are 3 kinds of specifications in view of pipeline, pipeline is blown
Except silencing means is using 3 kinds of interfaces for respectively corresponding this 3 kinds of specification pipelines, when blowing down a certain specification pipeline, blocked with steel plug
Another two interface.
Claims (1)
1. a kind of space launching site tank is deflated and blow-line purging's noise silencer, comprising:
Step 1: launching site tank is deflated and the noise generating mechanisms of blow-line purging are analyzed.
It is calculated Step 2: launching site tank is deflated with the noise parameter during blow-line purging.
Step 3: space launching site tank is deflated and the design and realization of blow-line purging's noise silencer.
It is characterized by:
Step 1: launching site tank is deflated and the noise generating mechanisms of blow-line purging are analyzed.
Rocket body tank is deflated and the process of blow-line purging is a kind of exhaust emptying process of pressure pan, by analysis, it is determined that make an uproar
Mainly by the gas particle for high speed and the low velocity gas particle of surrounding the jet noise and air-flow that turbulent mixture generates occur for sound
It impacts the wind that extraneous free air generates to make an uproar composition, specifies the main inhibition approach of noise.
It is calculated Step 2: launching site tank is deflated with the noise parameter during blow-line purging.
It is straight according to the parameters such as the tank gas pressure of certain rocket series, tank gas temperature, the excessive valve export internal diameter of peace and gas
The launching site real data for arranging Shi Anyi valve export gas flow temperature, calculate the gas Mach number of outlet, gas flow rate,
The parameters such as resistance coefficient, tube outlet flow velocity, as silencing means design-calculated foundation.
Step 3: space launching site tank is deflated and blow-line purging's noise silencer is designed and realized.
The dedicated silencing means of design consists of two parts: first part is reflected by resistance filtering and decompression and expansion and portion is lost
Divide sound energy, and reduces high pressure air reducing dilatation by flow velocity to reduce noise；Second part is using microperforated panel to low speed flow
Further decrease noise to the noise permissible criterion of national regulation or less.
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