CN108181424A - The speed coupling response function measurement device and method of propellant order Oscillating mode - Google Patents
The speed coupling response function measurement device and method of propellant order Oscillating mode Download PDFInfo
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- CN108181424A CN108181424A CN201711161731.4A CN201711161731A CN108181424A CN 108181424 A CN108181424 A CN 108181424A CN 201711161731 A CN201711161731 A CN 201711161731A CN 108181424 A CN108181424 A CN 108181424A
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- G01N31/00—Investigating or analysing non-biological materials by the use of the chemical methods specified in the subgroup; Apparatus specially adapted for such methods
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Abstract
The invention discloses the speed coupling response function measurement methods of propellant order Oscillating mode, select T-shaped burner, T-shaped burner includes burner body, both ends in burner body are separately installed with the propellant test specimen folder of identical configuration and formula, the jet pipe communicated with inside it is installed at the L/4 or 3L/4 of burner body length, the outer wall at burner body both ends is respectively equipped with a high frequency sound pressure transducer, and pressure transducer is used to measure the pressure oscillator signal in burner body；There are two triggering exciting banks for installation at the L/2 of burner body length, and by installing test flake on T-shaped burner, cyclic annular medicine is tested, and obtains speed coupling response function under second order sound and vibration frequency；The present invention under the premise of the T-shaped combustion experimental device of fundamental frequency length is not changed, can obtain the pressure oscillating characteristic of single second order frequency.
Description
Technical field
The invention belongs to solid propellant technical fields, and in particular to the speed coupling of propellant order Oscillating mode is rung
Answer function measurement device and method.
Background technology
At present frequently with the speed coupling process of solid propellant order Oscillating mode have the disadvantage that：(1) it tests
It is middle using medicine is driven to generate excitation, and for composite propellant, containing a large amount of solid particle and dust in combustion product,
Particle damping is bigger, is hardly formed self-oscillation；(2) driving medicine is different with the propellant formulation for testing medicine, needs to survey respectively
The pressure coupling response function of both medicines is measured, and tests be required for measuring several times every time, experiment number is relatively more；(3) two
The generation of rank excitation is maintained by offset nozzle and flammable baffle, and how to place flammable baffle practical operation get up it is very tired
Difficulty, position somewhat deviation, it is possible to motivate other vibration shapes.
Invention content
The technical problems to be solved by the invention are in view of the above shortcomings of the prior art, to provide one kind and do not change base
Under the premise of the T-shaped combustion experimental device of frequency length, the pressure oscillating characteristic of single second order frequency is obtained.
In order to solve the above technical problems, the technical solution adopted by the present invention is, the speed coupling of propellant order Oscillating mode
Receptance function measuring method is closed, which includes as follows：
Step 1: designated length is the T-shaped burner of L, which includes burner body, in burner body
Both ends be separately installed with identical configuration and formula propellant test specimen folder, the L/4 or 3L/4 of burner body length place installation
There is the jet pipe communicated with inside it, the outer wall at burner body both ends is respectively equipped with a high frequency sound pressure transducer, pressure
Sensor is used to measure the pressure oscillator signal in burner body；There are two trigger for installation at the L/2 of burner body length
Exciting bank, triggering exciting bank are used to generate pressure oscillation in burner body；
Step 2: by installing test flake on T-shaped burner, cyclic annular medicine is tested, and is tied according to test
Fruit obtains speed coupling response function under second order sound and vibration frequency：
Or
Wherein, αG(L8)For test is installed on flake propellant on the propellant test specimen folder at T-shaped burner both ends,
And the net growth rate of acoustic pressure that propellant combustion generates when test is installed on cyclic annular medicine at T-shaped burner L/8 positions；
αG(3L/8)For test is installed on the propellant test specimen folder at T-shaped burner both ends, and with flake propellant by test ring
Shape medicine is installed on the net growth rate of acoustic pressure that propellant combustion generates when at T-shaped burner L/8 positions, αG(L/8&5L/8)For that will test
With flake propellant be installed on T-shaped burner both ends propellant test specimen folder on, and will test with ring-type medicine be installed on it is T-shaped
The net growth rate of acoustic pressure that propellant combustion generates when at burner L/8 and 5L/8 positions, αG(3L/8&7L/8)For by test sheet
Medicine propellant is installed on the propellant test specimen folder at T-shaped burner both ends, and test is installed on T-shaped burner with cyclic annular medicine
The net growth rate of acoustic pressure that propellant combustion generates when at 3L/8 and 7L/8 positions, γ is specific heat ratio；For average pressure；SCFor
Aisle spare；SBFace area is fired for propellant；F pressure vibrates fundamental frequency；R is propellant burning rate；ρpFor propellant density.
Further, the specific method of step 2 is：
Step a, test is installed on propellant on propellant test specimen folder, opens data collecting system, start pressure passes
Sensor, while start the ignition switch of two propellant test specimen folders, the test propellant at both ends is made to light a fire simultaneously；
T after igniting1Time triggers one of triggering exciting bank, forms first via triggering excitation, is passed by pressure
Sensor measures operating pressure attenuation coefficient α in burner body1；
After first via triggering encourages successfully, then postpone t2Time triggers another triggering exciting bank, forms second
Road triggering excitation, the operating pressure attenuation coefficient α in burner body is measured by pressure transducer2；
Wherein, t1=t/2, t are propellant total burning time；t2=t-t1+t3, when propellant is cup-shaped medicine, t3=
10ms；When propellant is flake, t3=0ms；
According to operating pressure attenuation coefficient α1、α2Obtain the net growth rate α of acoustic pressure that propellant combustion generatesG=αc0=α1-
α2, αc0The combustion face gain for being propellant test specimen at end positions, and second order is obtained according to pressure coupling response function expression
The receptance function value of frequency of oscillation；
Wherein,For the Average burning rate measured；A is the theoretical velocity of sound at a temperature of propellant combustion；amTo survey the velocity of sound, am
=2fL；
Step b, test is installed on flake propellant on the propellant test specimen folder at T-shaped burner both ends, and will surveyed
Ring-type medicine on probation is installed in T-shaped burner at L/8 positions, carries out igniting according to method in step a and triggering twice encourages,
By the record data of pressure transducer, the net growth rate α of acoustic pressure that propellant combustion generates is obtainedG(L/8)=αc0+αc(L/8)+
αV(L/8)；
Wherein, αV(L/8)For test is installed on the propellant reagent folder at both ends with flake propellant and uses test
Cyclic annular medicine is installed on speed coupling terms during L/8 positions in T-shaped burner；αc(L/8)For test flake propellant is installed
Pressure coupling terms when propellant reagent in both ends presss from both sides and test is installed on L/8 positions in T type burners with cyclic annular medicine,
And have
Wherein, x=L/8 at this time, for the cyclic annular medicine of test and the distance of combustion chamber end；
Step c, test is installed on flake propellant on the propellant test specimen folder at T-shaped burner both ends, and will surveyed
Ring-type medicine on probation is installed in T-shaped burner at 3L/8 positions, carries out igniting according to method in step a and triggering twice encourages,
By the record data of pressure transducer, the net growth rate α of acoustic pressure that propellant combustion generates is obtainedG(3L/8)=αc0+αc(3L/8)+
αV(3L/8)；
Wherein, αV(3L/8)For test is installed on the propellant reagent folder at both ends with flake propellant and uses test
Cyclic annular medicine is installed on speed coupling terms during 3L/8 positions in T-shaped burner；αc(3L/8)For test flake propellant is pacified
Propellant reagent loaded on both ends presss from both sides and couples the pressure tested when being installed on 3L/8 positions in T-shaped burner with cyclic annular medicine
；
Wherein, x=3L/8 at this time, for the cyclic annular medicine of test and the distance of combustion chamber end；
Step d, speed coupling response function under second order sound and vibration frequency is obtained according to step a, step b, step c：
Further, the specific method of step 2 is：
Step a ', test is installed on propellant on propellant test specimen folder, opens data collecting system, start pressure
Sensor, while start the ignition switch of two propellant test specimen folders, the test propellant at both ends is made to light a fire simultaneously；
T after igniting1Time triggers one of triggering exciting bank, forms first via triggering excitation, is passed by pressure
Sensor measures operating pressure oscillatory extinction factor alpha in burner body1；
After first via triggering encourages successfully, then postpone t2Time triggers another triggering exciting bank, forms second
Road triggering excitation, the operating pressure oscillatory extinction factor alpha in burner body is measured by pressure transducer2；
Wherein, t1=t/2, t are propellant total burning time；t2=t-t1+t3, when propellant is cup-shaped medicine, t3=
10ms；When propellant is flake, t3=0ms；
According to operating pressure oscillatory extinction factor alpha1、α2Obtain the net growth rate α of acoustic pressure that propellant combustion generatesG=αc0=
α1-α2, αc0The combustion face gain for being propellant test specimen at end positions, and obtained according to pressure coupling response function expression
The receptance function value of order Oscillating frequency；
Wherein,For the Average burning rate measured；A is the theoretical velocity of sound at a temperature of propellant combustion；amTo survey the velocity of sound, am
=2fL；
Step b ', test is installed on flake propellant on the propellant test specimen folder at T-shaped burner both ends, and will
Test is installed on cyclic annular medicine in T-shaped burner at L/8 and 5L/8 positions, according to method in step a ' carry out igniting with twice
Triggering excitation by the record data of pressure transducer, obtains the net growth rate of acoustic pressure that propellant combustion generates
αG(L/8&5L/8)=αc0+αc(L/8)+αc(5L/8)+αV(L/8)+αV(5L/8)；
Wherein, αc0The combustion face gain for being propellant test specimen at end positions, αv(L/8)、αv(5L/8)Respectively test is used
Flake propellant be installed on both ends propellant reagent folder and will test with ring-type medicine be installed on L/8 in T-shaped burner,
Speed coupling terms during 5L/8 positions；αc(L/8)、αc(5L/8)Test is respectively installed on pushing away for both ends with flake propellant
Pressure coupling terms when L/8,5L/8 position in T-shaped burner are installed on into agent reagent folder and by test with cyclic annular medicine, and are had
Wherein, x=L/8 at this time, for the cyclic annular medicine of test and the distance of combustion chamber end；
Wherein, x=5L/8 at this time, for the cyclic annular medicine of test and the distance of combustion chamber end；
Step c ', test is installed on flake propellant on the propellant test specimen folder at T-shaped burner both ends, and will
Test is installed on cyclic annular medicine in T-shaped burner at 3L/8 and 7L/8 positions, according to method in step a ' carry out igniting with twice
Triggering excitation by the record data of pressure transducer, obtains the net growth rate α of acoustic pressure that propellant combustion generatesG(3L/8&7L/8)
=αc0+αc(3L/8)+αc(7L/8)+αV(3L/8)+αV(7L/8)；
Wherein, αv(3L/8)、αv(7L/8)Respectively test is pressed from both sides with the propellant reagent that flake propellant is installed on both ends,
And speed coupling terms when being installed on 3L/8,7L/8 position in T-shaped burner with ring-type medicine, α will be testedc(3L/8)、αc(7L/8)Point
Test Wei be installed on the propellant reagent folder at both ends with flake propellant and test is installed on T-shaped combustion with cyclic annular medicine
Pressure coupling terms in burner when 3L/8,7L/8 position, and have
Wherein, x=3L/8 at this time, for the cyclic annular medicine of test and the distance of combustion chamber end；
Wherein, x=7L/8 at this time, for the cyclic annular medicine of test and the distance of combustion chamber end；
Step d ', speed coupling response function under second order sound and vibration frequency is obtained according to step a ', step b ', step c '：
Further, test is less than or equal to 3%L with the thickness of cyclic annular medicine.
The another technical solution of the present invention：A kind of speed coupling response function of above-mentioned propellant order Oscillating mode
The measuring device that measuring method uses is including lengthLT-shaped burner, the T-shaped burner include burner body, burning
The intrinsic both ends of device are equipped with the propellant test specimen folder of identical configuration and same recipe, and the L/2 on burner body outer wall
Installation is there are two triggering exciting bank at position, for generating pressure oscillation in burner body；The both ends of burner body
Outer wall on be also separately installed with high frequency sound pressure transducer, for measuring the pressure oscillator signal in burner body；Burning
Cyclic annular test medicine test specimen folder is provided at the L/8 and 5L/8 of device body length or at 3L/8 and 7L/8；
Further include data collecting system and igniting sequential control system, data collecting system respectively with pressure transducer, touch
Hair exciting bank is connected；Triggering exciting bank and propellant test specimen folder are connected with igniting sequential control system.
The speed coupling response function measurement device and method of propellant order Oscillating mode of the present invention have following excellent
Point：Under the premise of not changing the T-shaped combustion experimental device of fundamental frequency length, motivational techniques are triggered by controllable precise, obtain single two
The pressure oscillating characteristic of order frequency, and based on the oscillating characteristic, it is proposed that the speed coupling response under second order pressure oscillating condition
Function measurement method obtains solid propellant speed coupling response function characteristic.
Description of the drawings
Fig. 1 is that the structure of the speed coupling response function measurement device of solid propellant order Oscillating mode of the present invention is shown
It is intended to；
Fig. 2 is the structure diagram of solid propellant flake used and cyclic annular medicine in the present invention；
Fig. 3 is the time pressure relational graph obtained in the embodiment of the present invention by pressure sensor.
Wherein：1.T type burners；2. burner body；3. trigger exciting bank；4. pressure transducer；5. propellant tries
Part presss from both sides；6. data collecting system；7. igniting sequential control system, 8. cyclic annular test medicine test specimen folders；9. jet pipe.
Specific embodiment
The present invention is described in detail with reference to the accompanying drawings and detailed description.
The invention discloses a kind of speed coupling response function measurement method of propellant order Oscillating mode, in T-shaped combustion
1 length L of burner (oscillation fundamental frequency f=f1) remain unchanged under the premise of, using two-way excitation triggering by the way of triggered, be
Guarantee only generates single order Oscillating frequency (f2=2f1), triggering exciting bank 3 need to be placed in L/2 positions in T-shaped burner 1
Place, and to ensure that second order acoustical energy losses minimum jet pipe need to place L/4 (3L/4) position, the i.e. nodal point of order Oscillating mode.
Test measurement uses secondary triggering advocate approach, respectively in solid propellant in the T-shaped burner 1 burning intermediate time and just
Finish time carries out triggering excitation, obtains single second order pressure oscillatory extinction data, two are obtained respectively using Galerkin's Procedure
Pressure oscillatory extinction coefficient after secondary triggering, so as to obtain the speed coupling response functional value under order Oscillating frequency effect
The measuring method specifically comprises the following steps：
Step 1: fundamental frequency f is vibrated according to pressure1Designated length is the T-shaped burner 1 of L, meets f1=a/ (2L), this is T-shaped
Burner 1 includes burner body 2, and the both ends in burner body 2 are separately installed with the propellant examination of identical configuration and formula
Part presss from both sides 5, and the jet pipe 9 communicated with inside it, 1 both ends of burner body are equipped at the L/4 or 3L/4 of 1 length of burner body
Outer wall one high frequency sound pressure transducer 4 is respectively installed, pressure transducer 4 is used to measure the pressure in burner body 2
Oscillator signal；There are two triggering exciting banks 3 for installation at the L/2 of 2 length of burner body, trigger exciting bank 3 and are used for
Pressure oscillation is generated in burner body 2, triggering exciting bank 3 can be selected the device in ZL201310014235.1, meet
Ppulser=~20MPa, Ppulser=~50MPa, Ppulser=~90MPa and PpulserTetra- types of=~150MPa.
Step 2: by installing test flake on T-shaped burner 1, cyclic annular medicine is tested, and according to test
As a result speed coupling response function under second order sound and vibration frequency is obtained：
Or
Wherein, αG(L/8)For test is installed on flake propellant on the propellant test specimen folder at T-shaped burner both ends,
And the net growth rate of acoustic pressure that propellant combustion generates when test is installed on cyclic annular medicine at T-shaped burner L/8 positions；
αG(3L/8)For test is installed on the propellant test specimen folder at T-shaped burner both ends, and with flake propellant by test ring
Shape medicine is installed on the net growth rate of acoustic pressure that propellant combustion generates when at T-shaped burner L/8 positions, αG(L/8&5L/8)For that will test
With flake propellant be installed on T-shaped burner both ends propellant test specimen folder on, and will test with ring-type medicine be installed on it is T-shaped
The net growth rate of acoustic pressure that propellant combustion generates when at burner L/8 and 5L/8 positions, αG(3L/8&7L/8)For by test sheet
Medicine propellant is installed on the propellant test specimen folder at T-shaped burner both ends, and test is installed on T-shaped burner with cyclic annular medicine
The net growth rate of acoustic pressure that propellant combustion generates when at 3L/8 and 7L/8 positions, γ is specific heat ratio；For average pressure；SCIt is logical
Road area；SBFace area is fired for propellant；F pressure vibrates fundamental frequency；R is propellant burning rate；ρpFor propellant density.
Two methods realization can be used in step 2.First method is specially：
Step a, test is installed on propellant on propellant test specimen folder 5, opens data collecting system 6, start pressure
Sensor 4, while start the ignition switch of two propellant test specimen folders 5, the test propellant at both ends is made to light a fire simultaneously；
T after igniting1Time triggers one of triggering exciting bank 3, forms first via triggering excitation, is passed by pressure
Sensor 4 measures operating pressure attenuation coefficient α in burner body 21；
After first via triggering encourages successfully, then postpone t2Time triggers another triggering exciting bank 3, forms second
Road triggering excitation, the operating pressure attenuation coefficient α in burner body 2 is measured by pressure transducer 42；
Wherein, t1=t/2, t are propellant total burning time；t2=t-t1+t3, when propellant is cup-shaped medicine, t3=
10ms；When propellant is flake, t3=0ms；
According to operating pressure attenuation coefficient α1、α2Obtain the net growth rate α of acoustic pressure that propellant combustion generatesG=αc0=α1-
α2, αc0The combustion face gain for being propellant test specimen at end positions, and second order is obtained according to pressure coupling response function expression
The receptance function value of frequency of oscillation；
Wherein,For the Average burning rate measured；A is the theoretical velocity of sound at a temperature of propellant combustion；amTo survey the velocity of sound, am
=2fL；
Step b, test is installed on flake propellant on the propellant test specimen folder 5 at T-shaped 1 both ends of burner, and will
Test is installed on cyclic annular medicine in T-shaped burner 1 at L/8 positions, carries out igniting according to method in step a and triggering twice swashs
It encourages, by the record data of pressure transducer 4, obtains the net growth rate α of acoustic pressure that propellant combustion generatesG(L/8)=αc0+αc(L/8)
+αV(L/8)；
Wherein, αV(L/8)For test is installed on the propellant reagent folder 5 at both ends with flake propellant and uses test
Cyclic annular medicine is installed on speed coupling terms during L/8 positions in T-shaped burner 1；αc(L/8)For test flake propellant is pacified
Propellant reagent folder 5 loaded on both ends and pressure coupling when being installed on L/8 positions in T-shaped burner 1 with ring-type medicine will be tested
Item is closed, and is had
Wherein, x=L/8 at this time, for the cyclic annular medicine of test and the distance of combustion chamber end.
Step c, test is installed on flake propellant on the propellant test specimen folder 5 at T-shaped 1 both ends of burner, and will
Test is installed on cyclic annular medicine in T-shaped burner 1 at 3L/8 positions, carries out igniting according to method in step a and triggering twice swashs
It encourages, by the record data of pressure transducer 4, obtains the net growth rate α of acoustic pressure that propellant combustion generatesG(3L/8)=αc0+
αc(3L/8)+αV(3L/8)；
Wherein, αV(3L/8)For test is installed on the propellant reagent folder 5 at both ends with flake propellant and will be tested
Speed coupling terms during 3L/8 positions in T-shaped burner 1 are installed on cyclic annular medicine；αc(3L/8)For by test flake propellant
It is installed on the propellant reagent folder 5 at both ends and pressure when being installed on 3L/8 positions in T-shaped burner 1 with ring-type medicine will be tested
Coupling terms；
Wherein, x=3L/8 at this time, for the cyclic annular medicine of test and the distance of combustion chamber end.
Step d, speed coupling response function under second order sound and vibration frequency is obtained according to step a, step b, step c：
Another method is specially：
Step a ', test is installed on propellant on propellant test specimen folder 5, opens data collecting system 6, start pressure
Strong sensor 4, while start the ignition switch of two propellant test specimen folders 5, the test propellant at both ends is made to light a fire simultaneously；
T after igniting1Time triggers one of triggering exciting bank 3, forms first via triggering excitation, is passed by pressure
Sensor 4 measures operating pressure oscillatory extinction factor alpha in burner body 21；
After first via triggering encourages successfully, then postpone t2Time triggers another triggering exciting bank 3, forms second
Road triggering excitation, the operating pressure oscillatory extinction factor alpha in burner body 2 is measured by pressure transducer 42；
Wherein, t1=t/2, t are propellant total burning time；t2=t-t1+t3, when propellant is cup-shaped medicine, t3=
10ms；When propellant is flake, t3=0ms；
According to operating pressure oscillatory extinction factor alpha1、α2Obtain the net growth rate α of acoustic pressure that propellant combustion generatesG=αc0=
α1-α2, αc0The combustion face gain for being propellant test specimen at end positions, and obtained according to pressure coupling response function expression
Receptance function value；
Wherein,For the Average burning rate measured；A is the theoretical velocity of sound at a temperature of propellant combustion；amTo survey the velocity of sound, am
=2fL；
Step b ', test is installed on flake propellant on the propellant test specimen folder 5 at T-shaped 1 both ends of burner, and
Test is installed on cyclic annular medicine in T-shaped burner 1 at L/8 and 5L/8 positions, igniting and two are carried out according to method in step a '
Secondary triggering excitation by the record data of pressure transducer 4, obtains the net growth rate of acoustic pressure that propellant combustion generates
αG(L/8&5L/8)=αc0+αc(L/8)+αc(5L/8)+αV(L/8)+αV(5L/8)；
Wherein, αc0The combustion face gain for being propellant test specimen at end positions, αv(L/8)、αv(5L/8)Respectively test is used
Flake propellant be installed on both ends propellant reagent folder 5 and will test with ring-type medicine be installed on L/8 in T-shaped burner 1,
Speed coupling terms during 5L/8 positions；αc(L/8)、αc(5L/8)Test is respectively installed on pushing away for both ends with flake propellant
Pressure coupling terms when L/8,5L/8 position in T-shaped burner 1 are installed on into agent reagent folder 5 and by test with cyclic annular medicine, and
Have
Wherein, x=L/8 at this time, for the cyclic annular medicine of test and the distance of combustion chamber end；
Wherein, x=5L/8 at this time, for the cyclic annular medicine of test and the distance of combustion chamber end.
Step c ', test is installed on flake propellant on the propellant test specimen folder 5 at T-shaped 1 both ends of burner, and
Test is installed on cyclic annular medicine in T-shaped burner 1 at 3L/8 and 7L/8 positions, according to method in step a ' carry out igniting with
Triggering excitation twice by the record data of pressure transducer 4, obtains the net growth rate of acoustic pressure that propellant combustion generates
αG(3L/8&7L/8)=αc0+αc(3L/8)+αc(7L/8)+αV(3L/8) +αV(7L/8)；
Wherein, αv(3L/8)、αv(7L/8)The propellant reagent that test is respectively installed on to both ends with flake propellant presss from both sides
5 and speed coupling terms when being installed on 3L/8,7L/8 position in T-shaped burner 1 with ring-type medicine, α will be testedc(3L/8)、αc(7L/8)
Test is respectively installed on the propellant reagent folder 5 at both ends with flake propellant and test is installed on T with cyclic annular medicine
Pressure coupling terms in type burner 1 when 3L/8,7L/8 position, and have
Wherein, x=3L/8 at this time, for the cyclic annular medicine of test and the distance of combustion chamber end；
Wherein, x=7L/8 at this time, for the cyclic annular medicine of test and the distance of combustion chamber end.
Step d ', speed coupling response function under second order sound and vibration frequency is obtained according to step a ', step b ', step c '：
Wherein, test is less than or equal to 3%L with the thickness of cyclic annular medicine in above steps.
A kind of speed coupling response function measurement method the invention also discloses propellant order Oscillating mode uses
Measuring device, as shown in Figure 1, including the T-shaped burner 1 that length is L, which includes burner body 2, burning
Both ends in device ontology 2 are equipped with the propellant test specimen folder 5 of identical configuration and same recipe, and on 2 outer wall of burner body
Installation is there are two triggering exciting bank 3 at L/2 positions, for generating pressure oscillation in burner body 2；Burner body 2
Both ends outer wall on be also separately installed with high frequency sound pressure transducer 4, for measure the pressure in burner body 2 oscillation
Signal；Cyclic annular test medicine test specimen folder 8 is provided at the L/8 and 5L/8 of 2 length of burner body or at 3L/8 and 7L/8.
Further include data collecting system 6 and igniting sequential control system 7, data collecting system 6 respectively with pressure transducer
4th, triggering exciting bank 3 is connected；Triggering exciting bank 3 and propellant test specimen folder 5 are connected with igniting sequential control system 7
It connects.
In the present embodiment, the length of T-shaped burner 1 is 3.438m, a diameter of 0.09m, jet size 0.006m.It is T-shaped
The operating pressure of burner 1 is taken as 10MPa, and the frequency of pulse excitation is intrinsic frequency, that is, 340Hz of second_mode.Such as Fig. 2 institutes
Show, sheet propellant, cyclic annular propellant are same formula.The shortcomings that in view of present in composite propellant, here using not
Double base propellant containing aluminium.Test Types of Medicine positioned at both ends are cigarette burning powder charge, for measuring its pressure coupling response letter
Number, the test medicine positioned at L/8 and 3L/8 is cyclic annular medicine, for measuring its speed coupling response function.As shown in figure 3, it is logical
The time pressure relational graph that over-pressed force snesor 4 obtains.
Claims (5)
1. the speed coupling response function measurement method of propellant order Oscillating mode, which is characterized in that the measuring method includes
It is as follows：
Step 1: designated length is the T-shaped burner (1) of L, which includes burner body (2), the burning
Both ends in device ontology (2) are separately installed with the propellant test specimen folder (5) of identical configuration and formula, the burner body (1)
The jet pipe (9) communicated with inside it is installed, the outer wall at burner body (1) both ends is divided equally at the L/4 or 3L/4 of length
One high frequency sound pressure transducer (4) is not installed, the pressure transducer (4) is for measuring the pressure in burner body (2)
Oscillator signal；There are two triggering exciting bank (3), the triggering excitation dresses for installation at the L/2 of burner body (2) length
(3) are put for generating pressure oscillation in burner body (2)；
Step 2: by installing test flake on T-shaped burner (1), cyclic annular medicine is tested, and according to test result
Obtain speed coupling response function under second order sound and vibration frequency：
Or
Wherein, αG(L/8)For test is installed on flake propellant on the propellant test specimen folder at T-shaped burner both ends, and will
The net growth rate of acoustic pressure that propellant combustion generates when test is installed on cyclic annular medicine at T-shaped burner L/8 positions；αG(3L/8)To incite somebody to action
Test is installed on flake propellant on the propellant test specimen folder at T-shaped burner both ends, and test is installed on T with cyclic annular medicine
The net growth rate of acoustic pressure that propellant combustion generates when at type burner L/8 positions；αG(L/8&5L/8)For test is promoted with flake
Agent is installed on the propellant test specimen folder at T-shaped burner both ends, and test is installed on T-shaped burner L/8 and 5L/ with cyclic annular medicine
The net growth rate of acoustic pressure that propellant combustion generates when at 8 positions；αG(3L/8&7L/8)For test is installed on T with flake propellant
On the propellant test specimen folder at type burner both ends, and test is installed on cyclic annular medicine at T-shaped burner 3L/8 and 7L/8 positions
When propellant combustion generate the net growth rate of acoustic pressure；γ is specific heat ratio；P is average pressure；SCFor aisle spare；SBFor propellant
Combustion face area；F pressure vibrates fundamental frequency；R is propellant burning rate；ρpFor propellant density.
2. the speed coupling response function measurement method of propellant order Oscillating mode as described in claim 1, feature exist
In the specific method of step 2 is：
Step a, test is installed on propellant on propellant test specimen folder (5), opens data collecting system (6), start pressure
Sensor (4), while start the ignition switch of two propellant test specimen folders (5), the test propellant at both ends is made to light a fire simultaneously；
T after igniting1Time triggers one of triggering exciting bank (3), first via triggering excitation is formed, by pressure transducer
(4) burner body (2) interior operating pressure attenuation coefficient α is measured1；
After first via triggering encourages successfully, then postpone t2Time triggers another triggering exciting bank (3), forms the second tunnel and touches
Hair excitation measures the operating pressure attenuation coefficient α in burner body (2) by pressure transducer (4)2；
Wherein, t1=t/2, t are propellant total burning time；t2=t-t1+t3, when propellant is cup-shaped medicine, t3=10ms；When
When propellant is flake, t3=0ms；
According to operating pressure attenuation coefficient α1、α2Obtain the net growth rate α of acoustic pressure that propellant combustion generatesG=αc0=α1-α2, αc0
The combustion face gain for being propellant test specimen at end positions, and order Oscillating frequency is obtained according to pressure coupling response function expression
The receptance function value of rate；
Wherein,For the Average burning rate measured；A is the theoretical velocity of sound at a temperature of propellant combustion；amTo survey the velocity of sound, am=
2fL；
Step b, test is installed on flake propellant on the propellant test specimen folder (5) at T-shaped burner (1) both ends, and will
Test is installed on cyclic annular medicine at the interior L/8 positions of T-shaped burner (1), is carried out igniting according to method in step a and is touched twice
Hair excitation by the record data of the pressure transducer (4), obtains the net growth rate α of acoustic pressure that propellant combustion generatesG(L/8)
=αc0+αc(L/8)+αV(L/8)；
Wherein, αV(L/8)Propellant reagent for test to be installed on to both ends with flake propellant presss from both sides (5) and by test ring
Shape medicine is installed on speed coupling terms during the interior L/8 positions of T-shaped burner (1)；αc(L/8)For test flake propellant is installed
Propellant reagent in both ends presss from both sides (5) and will test pressure coupling when being installed on the interior L/8 positions of T-shaped burner (1) with ring-type medicine
Item is closed, and is had
Wherein, x=L/8 at this time, for the cyclic annular medicine of test and the distance of combustion chamber end；
Step c, test is installed on flake propellant on the propellant test specimen folder (5) at T-shaped burner (1) both ends, and will
Test is installed on cyclic annular medicine at the interior 3L/8 positions of T-shaped burner (1), according to method in step a carry out igniting with twice
Triggering excitation by the record data of the pressure transducer (4), obtains the net growth rate of acoustic pressure that propellant combustion generates
αG(3L/8)=αc0+αc(3L/8)+αV(3L/8)；
Wherein, αV(3L/8)Propellant reagent for test to be installed on to both ends with flake propellant presss from both sides (5) and by test ring
Shape medicine is installed on speed coupling terms during the interior 3L/8 positions of T-shaped burner (1)；αc(3L/8)For test flake propellant is pacified
Propellant reagent folder (5) loaded on both ends and pressure when the interior 3L/8 positions of T-shaped burner (1) are installed on ring-type medicine will be tested
Close coupling item；
Wherein, x=3L/8 at this time, for the cyclic annular medicine of test and the distance of combustion chamber end；
Step d, speed coupling response function under second order sound and vibration frequency is obtained according to step a, step b, step c：
3. the speed coupling response function measurement method of propellant order Oscillating mode as described in claim 1, feature exist
In the specific method of step 2 is：
Step a ', test is installed on propellant on propellant test specimen folder (5), opens data collecting system (6), start pressure
Sensor (4), while start the ignition switch of two propellant test specimen folders (5), the test propellant at both ends is made to light a fire simultaneously；
T after igniting1Time triggers one of triggering exciting bank (3), first via triggering excitation is formed, by pressure transducer
(4) burner body (2) interior operating pressure oscillatory extinction factor alpha is measured1；
After first via triggering encourages successfully, then postpone t2Time triggers another triggering exciting bank (3), forms the second tunnel and touches
Hair excitation measures the operating pressure oscillatory extinction factor alpha in burner body (2) by pressure transducer (4)2；
Wherein, t1=t/2, t are propellant total burning time；t2=t-t1+t3, when propellant is cup-shaped medicine, t3=10ms；When
When propellant is flake, t3=0ms；
According to operating pressure α1、α2Obtain the net growth rate α of acoustic pressure that propellant combustion generatesG=αc0=α1-α2, αc0For propellant
Combustion face gain of the test specimen at end positions, and obtain according to pressure coupling response function expression the response of order Oscillating frequency
Functional value；
Wherein,For the Average burning rate measured；A is the theoretical velocity of sound at a temperature of propellant combustion；amTo survey the velocity of sound, am=
2fL；
Step b ', test is installed on flake propellant on the propellant test specimen folder (5) at T-shaped burner (1) both ends, and will
Test is installed on cyclic annular medicine at the interior L/8 and 5L/8 positions of T-shaped burner (1), is lighted a fire according to method in step a '
Triggering excitation twice by the record data of the pressure transducer (4), show that the acoustic pressure that propellant combustion generates has a net increase of length
Rate
αG(L/8&5L/8)=αc0+αc(L/8)+αc(5L/8)+αV(L/8)+αV(5L/8)；
Wherein, αc0The combustion face gain for being propellant test specimen at end positions, αv(L/8)、αv(5L/8)Respectively by test sheet
Medicine propellant be installed on both ends propellant reagent folder (5) and will test with ring-type medicine be installed on the interior L/8 of T-shaped burner (1),
Speed coupling terms during 5L/8 positions；αc(L/8)、αc(5L/8)Test is respectively installed on to the propulsion at both ends with flake propellant
Agent reagent presss from both sides (5) and will test pressure coupling terms when interior L/8,5L/8 position of T-shaped burner (1) is installed on ring-type medicine, and
Have
Wherein, x=L/8 at this time, for the cyclic annular medicine of test and the distance of combustion chamber end；
Wherein, x=5L/8 at this time, for the cyclic annular medicine of test and the distance of combustion chamber end；
Step c ', test is installed on flake propellant on the propellant test specimen folder (5) at T-shaped burner (1) both ends, and will
Test is installed on cyclic annular medicine at T-shaped burner (1) 3L/8 the and 7L/8 positions, according to method in step a ' carry out igniting with
Triggering excitation twice by the record data of the pressure transducer (4), obtains the net growth rate of acoustic pressure that propellant combustion generates
αG(3L/8&7L/8)=αc0+αc(3L/8)+αc(7L/8)+αV(3L/8)+αV(7L/8)；
Wherein, αv(3L/8)、αv(7L/8)Respectively by test with flake propellant be installed on both ends propellant reagent folder (5) and
Speed coupling terms when interior 3L/8,7L/8 position of T-shaped burner (1) is installed on ring-type medicine, α will be testedc(3L/8)、αc(7L/8)Point
Not Wei by test with flake propellant be installed on both ends propellant reagent press from both sides (5) and will test with ring-type medicine be installed on it is T-shaped
Pressure coupling terms during interior 3L/8,7L/8 position of burner (1), and have
Wherein, x=3L/8 at this time, for the cyclic annular medicine of test and the distance of combustion chamber end；
Wherein, x=7L/8 at this time, for the cyclic annular medicine of test and the distance of combustion chamber end；
Step d ', speed coupling response function under second order sound and vibration frequency is obtained according to step a ', step b ', step c '：
4. the speed coupling response function measurement method of propellant order Oscillating mode as described in any one of claims 1-3,
It is characterized in that, the test is less than or equal to 3%L with the thickness of cyclic annular medicine.
5. a kind of speed coupling response function measurement method of any propellant order Oscillating mode of claim 1-4 makes
Measuring device, which is characterized in that including the T-shaped burner (1) that length is L, which includes burner sheet
Body (2), the both ends in burner body (2) are equipped with the propellant test specimen folder (5) of identical configuration and same recipe, and are burning
Installation is there are two triggering exciting bank (3) at L/2 positions on device ontology (2) outer wall, for generating pressure in burner body (2)
Hard oscillation；High frequency sound pressure transducer (4) is also separately installed on the outer wall at the both ends of burner body (2), is fired for measuring
Pressure oscillator signal in burner ontology (2)；It is set at the L/8 and 5L/8 of burner body (2) length or at 3L/8 and 7L/8
There is cyclic annular test medicine test specimen folder (8)；
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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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102095800A (en) * | 2011-02-17 | 2011-06-15 | 西安电子科技大学 | System for testing ultrasonic dynamic burning rate of solid propellant |
| CN103018397A (en) * | 2012-11-19 | 2013-04-03 | 苏万兴 | Secondary pulsating pressure coupling response measuring method |
| CN103075270A (en) * | 2013-01-15 | 2013-05-01 | 西北工业大学 | High-pressure-intensity external pulse excitation device for T-shaped burner |
| CN103122807A (en) * | 2013-01-16 | 2013-05-29 | 西北工业大学 | Multichannel solid rocket engine ignition sequence control method |
-
2017
- 2017-11-21 CN CN201711161731.4A patent/CN108181424A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102095800A (en) * | 2011-02-17 | 2011-06-15 | 西安电子科技大学 | System for testing ultrasonic dynamic burning rate of solid propellant |
| CN103018397A (en) * | 2012-11-19 | 2013-04-03 | 苏万兴 | Secondary pulsating pressure coupling response measuring method |
| CN103075270A (en) * | 2013-01-15 | 2013-05-01 | 西北工业大学 | High-pressure-intensity external pulse excitation device for T-shaped burner |
| CN103122807A (en) * | 2013-01-16 | 2013-05-29 | 西北工业大学 | Multichannel solid rocket engine ignition sequence control method |
Non-Patent Citations (5)
| Title |
|---|
| E.E. STEEP: "Effect of Pressure and Velocity Coupling on Low-Frequency Instability", 《AIAA JOURNAL》 * |
| 刘佩进: "两种含铝复合推进剂压强耦合响应的实验对比", 《固体火箭技术》 * |
| 吕振中: "固体火箭发动机不稳定燃烧的速度耦合模型的研究", 《推进技术》 * |
| 王明雄: "固体推进剂速度耦合响应函数研究", 《固体火箭技术》 * |
| 郜冶: "速度耦合与压力耦合的相互作用", 《兵工学报》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN111751110B (en) * | 2020-07-04 | 2021-05-14 | 西北工业大学 | Carbon fiber heat release sound production device for oscillation combustion 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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