CN108131217A - The non-linear pressure coupling response function measurement method of solid propellant - Google Patents
The non-linear pressure coupling response function measurement method of solid propellant Download PDFInfo
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- CN108131217A CN108131217A CN201711161687.7A CN201711161687A CN108131217A CN 108131217 A CN108131217 A CN 108131217A CN 201711161687 A CN201711161687 A CN 201711161687A CN 108131217 A CN108131217 A CN 108131217A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
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Abstract
The invention discloses the non-linear pressure coupling response function measurement method of solid propellant, the measuring method is as follows：High Voltage external trigger motivational techniques are used to T-shaped burner measuring device, according to the operating pressure of triggering exciting bank, control the pressure oscillating characteristic in T-shaped burner, and using " secondary triggering excitation " method, it burns in T-shaped burner intermediate time and just finish time has carried out triggering excitation in solid propellant respectively, obtain non-linear pressure oscillatory extinction data, discrete processes are carried out to oscillatory extinction data, the attenuation coefficient of each rank Oscillatory mode shape is obtained respectively, so as to obtain the nonlinear response function value of all Oscillatory mode shapes.A kind of non-linear pressure coupling response function measurement method of solid solid propellant vibrates the non-linear pressure coupling response characteristic under environment for studying solid propellant in non-linear pressure.
Description
Technical field
The invention belongs to SOLID PROPELLANT COMBUSTION technical fields, and in particular to the non-linear pressure coupling response of solid propellant
Function measurement method.
Background technology
An important factor for pressure coupled characteristic of solid propellant is as combustion instability in solid propellant rocket is influenced
One of, paid attention to by domestic and international researcher.For solid propellant, pressure coupled characteristic usually uses pressure coupling response
Function characterizes, and pressure coupling response function then needs to obtain by testing measurement means.It can according to the characteristic of combustion instability
To be divided into, linear burner is unstable and non-linear burn is unstable, therefore propellant pressure coupling response characteristic can also be divided into line
Property and non-linear.Linear pressure coupling response function can be obtained by the method for the T-shaped burner of tradition.The master of T-shaped burner
It is the centre position that jet pipe is opened in combustion chamber to want feature, can reduce acoustical energy losses in this way, easily excitation oscillation.T-shaped burner
Generally use tubular combustion chamber installs the propellant that two panels is of uniform thickness, and it is made to light simultaneously respectively in burner ends, this
Sample causes whole burning surfaces to be in identical acoustic environment.Ideally, two pieces of propellants have burnt simultaneously.When there is axis
During to the acoustic pressure vibration shape, T-shaped burner both ends pressure oscillation amplitude is maximum, and it is maximum that the gain generated is coupled with propellant combustion.And
Acoustic speed, cross-flow velocity and the mean flow rate at both ends are 0, so as to remove the influence of speed coupling response.It is T-shaped
The axial oscillation fundamental frequency that burner can measure depends primarily on combustor length L and local velocity of sound a, expression formula f=
na/L.Wherein n is glottis neoplasms number, and a is the local velocity of sound in engine, related with T, f.Under normal conditions, according to T-shaped burner
The situation of change of length can obtain corresponding single frequency of oscillation.The characteristics of this linear pressure coupling response function is maximum be
It is obtained under the conditions of single-frequency, based on linear theory method, by changing the ginsengs such as tester length or modulation rotational frequency
Number is handled high-order glottis neoplasms frequency of oscillation longitudinal in same geometric configuration, with corresponding single order fundamental frequency respectively so as to obtain
Obtain the pressure coupling response functional value of different frequency mode.However, non-linear burn instability problem is extremely complex, usually by
Single-frequency harmonic oscillation caused by linear microvariations.With constantly there is energy to be injected into sound and vibration system in combustion process, low-order mode
State (referring generally to fundamental frequency) oscillation amplitude increases, and transmits energy to high order mode so that high order mode oscillation amplitude increases, and generates
Wave distortion is typically characterised by：The harmonic wave of multiple and different frequencies is contained in the distribution of pressure oscillation spectrum, and big amplitude is sent out
Life is at several low frequencies.In the case of this multi-modes coexist, the burning response process of solid propellant is no longer single
Frequency effect, but multi-modes collective effect, pressure coupling function show nonlinear characteristic, and by oscillation amplitude shadow
Sound is larger.However, tradition, which becomes length base frequency oscillation experimental measurement method, can not obtain nonlinear response function value, i.e., using elongated
The linear response function value spent under the fundamental frequency obtained has larger difference with the receptance function value under fundamental frequency frequency multiplication.Therefore,
It is necessary to establish non-linear pressure coupling response Function experiment measuring method, for non-linear under the conditions of multi-modes collective effect
Oscillating characteristic carries out relevant research work.
Invention content
The technical problems to be solved by the invention are in view of the above shortcomings of the prior art, to provide a kind of solid solid and push away
Into the non-linear pressure coupling response function measurement method of agent, vibrated under environment in non-linear pressure for studying solid propellant
Non-linear pressure coupling response characteristic.
In order to solve the above technical problems, the technical solution adopted by the present invention is, the non-linear pressure coupling of solid propellant is rung
Answer function measurement method, which is characterized in that the measuring method is as follows：
To T-shaped burner measuring device using High Voltage external trigger motivational techniques, according to the work of triggering exciting bank
Pressure controls the pressure oscillating characteristic in T-shaped burner, and using " secondary triggering excitation " method, respectively in solid propellant in T
The interior burning intermediate time of type burner and just finish time carry out triggering excitation, obtain non-linear pressure oscillatory extinction data,
Discrete processes are carried out to oscillatory extinction data, the attenuation coefficient of each rank Oscillatory mode shape are obtained respectively, so as to obtain all oscillation modes
The nonlinear response function value of state.
Further, the non-linear pressure coupling response function measurement method of the solid propellant, which is characterized in that the measurement
Method includes the following steps：
Step 1: designated length is the T-shaped burner of L, which includes burner body, in burner body
Both ends the propellant test specimen folder of identical configuration and same recipe is installed, and in burner body) on the outer wall at both ends respectively
One triggering exciting bank is installed, for generating pressure oscillation in burner body；On the outer wall at the both ends of burner body
High frequency sound pressure transducer is also separately installed with, for measuring the pressure oscillator signal in burner body；
Step 2: lighting the propellant of propellant test specimen folder clamping, after propellant fire, postpone t1Then time triggers
One triggering exciting bank of burner body one end forms first via triggering excitation；Pressure transducer measures burner body
Interior operating pressure P`1(t)；Wherein, t1=t/2, t are total burning time of propellant；
Step 3: after forming first via triggering excitation, then postpone t2Time, one of the triggering burner body other end touch
Exciting bank is sent out, forms the triggering excitation of the second tunnel；Pressure transducer measures the operating pressure P` in burner body2(t)；Its
In：t2=t-t1+t3；
Step 4: Galerkin's Procedure is respectively adopted to the operating pressure in step 2 and step 3
Processing respectively obtains each rank frequency of oscillation f of correspondence after triggering encourages for the first time and after second of triggering excitation1,nWith
f2,nAnd the attenuation coefficient α of corresponding each rank oscillation amplitude1,nAnd α2,n；Wherein, b=1 or 2, AB, nRepresent each rank frequency of oscillation
Amplitude；fB, nFor each rank frequency of oscillation；αB, nAttenuation coefficient for each rank oscillation amplitude；N is Oscillatory mode shape number, and value is just whole
Number；
Step 5: by each rank frequency of oscillation described in step 4, the burning receptance function value of each rank frequency of oscillation is obtained
Rp(fn), using least square fitting, meet with a response function distribution curve：
Wherein：RpFor pressure coupling response function,For average pressure in burner body；ρpFor propellant density；For
Propellant Average burning rate；SB/SCFace and T-shaped burner channel area ratio are fired for propellant, a is the theoretical velocity of sound；amIt measures
The velocity of sound, am=2f1L, L are T-shaped combustor length.
Further, in the step 3, when propellant is cup-shaped medicine, t3=10ms, when propellant is flake, t3
=0ms.
The invention also discloses dresses used in the non-linear pressure coupling response function measurement method of above-mentioned solid propellant
It puts, including the T-shaped burner that length is L, which includes burner body, and the both ends in burner body are equipped with
The propellant test specimen of identical configuration and same recipe presss from both sides, and is separately installed with a triggering on the outer wall at burner body both ends and swashs
Device is encouraged, for generating pressure oscillation in burner body；Height is also separately installed on the outer wall at the both ends of burner body
Frequency response pressure transducer, for measuring the pressure oscillator signal in burner body；
Data collecting system and igniting sequential control system are further included, the data collecting system is connected with pressure transducer
It connects；The triggering exciting bank and propellant test specimen folder are connected with igniting sequential control system.
The invention has the advantages that：Under the premise of not changing T-shaped combustor length, encouraged by the triggering of controllable precise
Method obtains the non-linear pressure that can reflect under the conditions of the nonlinear instability pressure oscillating characteristic in the real engine course of work
Close coupling receptance function distribution curve, this method can reduce the change length experimental provision brought by Frequency measurement, reduce
Experiment measurement cost and experiment measure workload, and the result that this method measures more can really reflect that propellant is starting
The non-linear response characteristic to burn in machine.
Description of the drawings
Fig. 1 is the structure diagram of the non-linear pressure coupling response function measurement device of propellant in the present invention；
Fig. 2 is that pressure working curve after excitation is triggered in the present invention；
A1. typical triggering excitation pressure working curve under 20~30MPa；
B1. typical triggering excitation pressure working curve under 50~60MPa；
C1. typical triggering excitation pressure working curve under 80~90MPa；
D1. typical triggering excitation pressure working curve under 150MPa；
A2. pressure working curve after triggering encourages under 20~30MPa；
B2. pressure working curve after triggering encourages under 50~60MPa；
C2. pressure working curve after triggering encourages under 80~90MPa；
D2. pressure working curve after triggering encourages under 150MPa；
Fig. 3 triggering excitation pressure influences to scheme on each rank glottis neoplasms oscillation amplitude；
3a. triggerings excitation pressure is to the influence figure of total glottis neoplasms oscillation amplitude；
3b. triggerings excitation pressure is to the influence figure of each rank glottis neoplasms oscillation amplitude.
Wherein：1.T type burners；2. burner body, 3. triggering exciting banks；4. pressure transducer；5. propellant tries
Part presss from both sides；6. data collecting system；7. igniting sequential control system.
Specific embodiment
The non-linear pressure coupling response function measurement method of solid propellant of the present invention, the measuring method are as follows：
To T-shaped burner measuring device using High Voltage external trigger motivational techniques, according to the work of triggering exciting bank
Pressure controls the pressure oscillating characteristic in T-shaped burner 1, and using " secondary triggering excitation " method, exists respectively in solid propellant
The interior burning intermediate time of T-shaped burner 1 and just finish time carry out triggering excitation, obtain non-linear pressure oscillatory extinction number
According to carrying out discrete processes to oscillatory extinction data, the attenuation coefficient of each rank Oscillatory mode shape obtained respectively, so as to obtain all oscillations
The nonlinear response function value of mode.
The non-linear pressure coupling response function measurement method of the solid propellant includes the following steps：
Step 1: designated length is the T-shaped burner 1 of L, as shown in Figure 1, the T-shaped burner 1 includes burner body 2,
Both ends in burner body 2 are equipped with the propellant test specimen folder 5 of identical configuration and same recipe, and in 2 liang of burner body
A triggering exciting bank 3 is separately installed on the outer wall at end, for generating pressure oscillation in burner body 2；Burner sheet
High frequency sound pressure transducer 4 is also separately installed on the outer wall at the both ends of body 2, is shaken for measuring the pressure in burner body 2
Swing signal；
Step 2: lighting the propellant of 5 clamping of propellant test specimen folder, after propellant fire, postpone t1Then time triggers
One triggering exciting bank 3 of 2 one end of burner body forms first via triggering excitation；Pressure transducer 4 measures burner sheet
Operating pressure P` in body 21(t)；Wherein, t1=t/2, t are total burning time of propellant；
Step 3: after forming first via triggering excitation, then postpone t2Time, one of triggering 2 other end of burner body
Exciting bank 3 is triggered, forms the triggering excitation of the second tunnel；Pressure transducer 4 measures the operating pressure P` in burner body 32
(t)；Wherein：t2=t-t1+t3；
Step 4: Galerkin's Procedure is respectively adopted to the operating pressure in step 2 and step 3
Processing respectively obtains each rank frequency of oscillation f of correspondence after triggering encourages for the first time and after second of triggering excitation1,nWith
f2,nAnd the attenuation coefficient α of corresponding each rank oscillation amplitude1,nAnd α2,n；Wherein b=1 or 2, AB, nRepresent each rank frequency of oscillation
Amplitude；fB, nFor each rank frequency of oscillation；αB, nAttenuation coefficient for each rank oscillation amplitude；N is Oscillatory mode shape number, and value is just whole
Number；
Step 5: by each rank frequency of oscillation described in step 4, the burning receptance function value of each rank frequency of oscillation is obtained
Rp(fn), using least square fitting, meet with a response function distribution curve：
Wherein：RpFor pressure coupling response function,For average pressure in burner body；ρpFor propellant density；For
Propellant Average burning rate；SB/SCFace and T-shaped burner channel area ratio are fired for propellant, a is the theoretical velocity of sound；amIt measures
The velocity of sound, am=2f1L, L are T-shaped combustor length.
When propellant is cup-shaped medicine, t3=10ms, when propellant is flake, t3=0ms.
The invention also discloses the measuring devices used in above-mentioned measuring method, should including the T-shaped burner 1 that length is L
T-shaped burner 1 includes burner body 2, and the both ends in burner body 2 are equipped with the propellant of identical configuration and same recipe
Test specimen folder 5, and a triggering exciting bank 3 is separately installed on the outer wall at 2 both ends of burner body, in burner body
Pressure oscillation is generated in 2；High frequency sound pressure transducer 4 is also separately installed on the outer wall at the both ends of burner body 2, for surveying
Measure the pressure oscillator signal in burner body 2；
Further include data collecting system 6 and igniting sequential control system 7, the data collecting system 6 and pressure transducer 4
It is connected；The triggering exciting bank 3 and propellant test specimen folder 5 are connected with igniting sequential control system 7.
The triggering that triggering exciting bank 3 and high frequency sound pressure transducer 4 are mounted on corresponding T-shaped burner outer wall face swashs
It encourages on seat and pressure measurement seat, and is connected through a screw thread fit sealing.There is the through-hole of φ 5mm in triggering excitation seat and pressure measurement seat, make
The high-temperature high-pressure fuel gas that the generation of exciting bank 3 must be triggered enters generation incentive action in T-shaped burner 1, and T-shaped burner 1
Interior high-temperature high-pressure fuel gas enters experiment pressure signal in high frequency sound pressure transducer 4 and measures.In triggering excitation seat and pressure measurement seat
Position of opening need to be in T-shaped burner at propellant combustion face neighbouring position.The two need on same cross section, between angle be less than
180 ° of high-temperature high-pressure fuel gas generated with guarantee triggering exciting bank 3 cannot be injected directly into measuring pressure of sensor hole in order to avoid causing to press
The damage of strong sensor 4.
It is tested using the non-linear pressure coupling response function measurement method of solid propellant in the present invention, specifically such as
Under：
The operatic tunes length for designing T-shaped burner 1 is L=2.8m, under conditions of operating pressure is 9~10MPa, according to propulsion
The agent working time by high-precision, the igniting sequential control system 7 of multichannel, observes the work feelings of four kinds of triggering excitation pressure
Condition.Excitation is triggered in experimentation twice altogether, for the first time in T-shaped burner 1 work intermediate time t1, it is to push away for the second time
Into agent just completion of combustion moment t2.The igniter quantity triggered in exciting bank 3 is respectively 5g, 10g, 15g and 27g, is being encouraged
The high-temperature fuel gas of 20~30MPa, 50~60MPa, 80~90MPa and~150MPa can be generated in device 3.
Pressure-time plot shown in Fig. 2 is obtained, as shown in Figure 2, from curve as can be seen that in T-shaped burner 1
After interior igniting, before the excitation of first time external trigger, apparent pressure oscillatory occurences is not generated in T-shaped burner 1, and use
Difference excitation pressure triggering after, generate pressure oscillatory occurences in T-shaped burner 1, respectively to triggering encourage after oscillation section into
Row Fourier analysis can be seen that using different excitation pressure triggerings, and the oscillation of generation has apparent difference, substantially against tactile
The increase of hair excitation pressure, oscillation amplitude is in increased Long-term change trend, and especially in super-pressure, (super-pressure refers to the pressure of more than 80MPa
Under the conditions of by force), amplitude significantly increases.
Fourier's series analysis is carried out to oscillation section respectively, from figure 3, it can be seen that the frequency information included in global oscillation
It is different, wherein under the conditions of 20~30MPa, vibrate based on single order base frequency oscillation, be linear osccilation, and with oscillation amplitude
Increase, high order of frequency gradually is excited out, and the oscillation amplitude of each mode gradually increases, and pressure oscillation is in typical non-thread
Property characteristic.
The receptance function of each rank mode is affected by oscillation amplitude, with the increase of each rank oscillation amplitude, responds letter
Numerical value is in increased Long-term change trend.It can be seen that the change of triggering energisation mode by testing the pressure time graph measured, it is right
Pressure oscillation result is generated in T-shaped burner large effect, can inspire non-linear pressure oscillating characteristic, and T-shaped combustion
Burner is working properly, and parameter setting is reasonable, has reached expected experiment effect.This explanation, based on the controllable outside of High Voltage precision
Triggering encourages T-shaped burner experimental provision, measures the measurement side of the non-linear pressure coupling response functional value of solid propellant
Method is feasible.
Claims (4)
1. the non-linear pressure coupling response function measurement method of solid propellant, which is characterized in that the measuring method is as follows：
To T-shaped burner measuring device using High Voltage external trigger motivational techniques, according to the operating pressure of triggering exciting bank,
The pressure oscillating characteristic in T-shaped burner is controlled, and using " secondary triggering excitation " method, respectively in solid propellant in T-shaped combustion
The interior burning intermediate time of burner and just finish time carry out triggering excitation, non-linear pressure oscillatory extinction data are obtained, to shaking
It swings attenuation data and carries out discrete processes, the attenuation coefficient of each rank Oscillatory mode shape is obtained respectively, so as to obtain all Oscillatory mode shapes
Nonlinear response function value.
2. the non-linear pressure coupling response function measurement method of solid propellant according to claim 1, which is characterized in that
The measuring method includes the following steps：
Step 1: designated length is the T-shaped burner (1) of L, which includes burner body (2), burner sheet
Both ends in body (2) are equipped with the propellant test specimen folder (5) of identical configuration and same recipe, and at burner body (2) both ends
Outer wall on be separately installed with a triggering exciting bank (3), for generating pressure oscillation in the burner body (2)；Burner
High frequency sound pressure transducer (4) is also separately installed on the outer wall at the both ends of ontology (2), for measuring in burner body (2)
Pressure oscillator signal；
Step 2: lighting the propellant of propellant test specimen folder (5) clamping, after propellant fire, postpone t1Time, then triggering combustion
One triggering exciting bank () of burner ontology (2) one end forms first via triggering excitation；Pressure transducer (4) measures burning
Operating pressure P` in device ontology (2)1(t)；Wherein, t1=t/2, t are total burning time of propellant；
Step 3: after forming first via triggering excitation, then postpone t2Time, a triggering of triggering burner body (2) other end
Exciting bank (3) forms the triggering excitation of the second tunnel；Pressure transducer (4) measures the operating pressure P` in burner body (3)2
(t)；Wherein：t2=t-t1+t3；
Step 4: Galerkin's Procedure is respectively adopted to the operating pressure in step 2 and step 3
Processing respectively obtains each rank frequency of oscillation f of correspondence after triggering encourages for the first time and after second of triggering excitation1,nWith
f2,nAnd the attenuation coefficient α of corresponding each rank oscillation amplitude1,nAnd α2,n；Wherein, b=1 or 2, AB, nRepresent each rank frequency of oscillation
Amplitude；fB, nFor each rank frequency of oscillation；αB, nAttenuation coefficient for each rank oscillation amplitude；N is Oscillatory mode shape number, and value is just whole
Number；
Step 5: by each rank frequency of oscillation described in step 4, the burning receptance function value R of each rank frequency of oscillation is obtainedp
(fn), using least square fitting, meet with a response function distribution curve：
Wherein：RpFor pressure coupling response function,For average pressure in burner body；ρpFor propellant density；To promote
Agent Average burning rate；SB/SCFace and T-shaped burner channel area ratio are fired for propellant, a is the theoretical velocity of sound；amFor the sound measured
Speed, am=2f1L, L are T-shaped combustor length.
3. the non-linear pressure coupling response function measurement method of solid propellant according to claim 1, which is characterized in that
In the step 3, when propellant is cup-shaped medicine, t3=10ms, when propellant is flake, t3=0ms.
4. the non-linear pressure coupling response function measurement device of propellant, which is characterized in that including the T-shaped burner that length is L
(1), which includes burner body (2), and the both ends in burner body (2) are equipped with identical configuration and identical
The propellant test specimen folder (5) of formula, and a triggering exciting bank is separately installed on the outer wall at burner body (2) both ends
(3), it is vibrated for generating pressure in burner body (2)；It is also separately installed on the outer wall at the both ends of burner body (2)
High frequency sound pressure transducer (4), for measuring the pressure oscillator signal in burner body (2)；
Further include data collecting system (6) and igniting sequential control system (7), the data collecting system (6) respectively with pressure
Sensor (4), triggering exciting bank (3) are connected；It is described triggering exciting bank (3) and propellant test specimen press from both sides (5) with igniting
Sequential control system (7) is connected.
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| CN109458275A (en) * | 2018-10-21 | 2019-03-12 | 西安航天动力测控技术研究所 | A kind of experimental rig using echo test method detection engine inflation pressure |
| CN110145410A (en) * | 2019-06-06 | 2019-08-20 | 北京理工大学 | A kind of end combustion powder charge solid propellant rocket for overloading experiment |
| CN111751110A (en) * | 2020-07-04 | 2020-10-09 | 西北工业大学 | Carbon fiber heat release sound production device for oscillation combustion of solid propellant |
| CN113530716A (en) * | 2021-07-05 | 2021-10-22 | 上海机电工程研究所 | Solid propellant fluctuation combustion pressure coupling response function measuring device and method |
| CN113676827A (en) * | 2021-08-25 | 2021-11-19 | 西北工业大学 | Direct-blowing type variable frequency oscillation experimental device for measuring frequency response function of solid propellant |
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| CN113686580A (en) * | 2021-08-25 | 2021-11-23 | 西北工业大学 | Standing wave oscillation experimental device for simulating nonlinear acoustic vibration mode of engine combustion chamber |
| CN113676827A (en) * | 2021-08-25 | 2021-11-19 | 西北工业大学 | Direct-blowing type variable frequency oscillation experimental device for measuring frequency response function of solid propellant |
| CN113686580B (en) * | 2021-08-25 | 2024-05-10 | 西北工业大学 | Standing wave oscillation experimental device for simulating nonlinear acoustic vibration mode of engine combustion chamber |
| CN113882973A (en) * | 2021-10-21 | 2022-01-04 | 上海机电工程研究所 | Time-varying acoustic vibration modal frequency identification method and system for combustion chamber of solid rocket engine |
| CN113882973B (en) * | 2021-10-21 | 2022-11-29 | 上海机电工程研究所 | Time-varying acoustic vibration modal frequency identification method and system for combustion chamber of solid rocket engine |
| CN114636169A (en) * | 2022-02-21 | 2022-06-17 | 北京航空航天大学 | Flame stabilizer perforation parameter determination method and device and radial flame stabilizer |
| CN114636169B (en) * | 2022-02-21 | 2023-01-20 | 北京航空航天大学 | Flame stabilizer perforation parameter determination method and device and radial flame stabilizer |
| CN115013187A (en) * | 2022-06-24 | 2022-09-06 | 哈尔滨工程大学 | Method and die for measuring pressure coupling response function of solid propellant |
| WO2023245874A1 (en) * | 2022-06-24 | 2023-12-28 | 哈尔滨工程大学 | Solid propellant pressure-coupled response function measurement method and molds |
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