CN108181423A - The speed coupling response function measurement device and method of propellant single order Oscillatory mode shape - Google Patents
The speed coupling response function measurement device and method of propellant single order Oscillatory mode shape Download PDFInfo
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- 239000003380 propellant Substances 0.000 title claims abstract description 217
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Abstract
The invention discloses a kind of speed coupling response function measurement methods of propellant single order Oscillatory mode shape, designated length is the T-shaped burner of L, the 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 on burner body at L/2, burner body both ends outer wall is respectively equipped with a high frequency sound pressure transducer, a triggering exciting bank is separately installed on the outer wall of burner body both ends, by installing flake on T-shaped burner, ring-type test medicine, speed coupling response function under single order sound and vibration frequency;Solve the problems, such as that the pressure oscillating characteristic precision of the fundamental frequency obtained in the prior art is low.
Description
[ technical field ] A method for producing a semiconductor device
The invention belongs to the technical field of solid propellants, and particularly relates to a device and a method for measuring a velocity coupling response function of a first-order oscillation mode of a propellant.
[ background of the invention ]
The commonly adopted speed coupling method of the first-order oscillation mode of the solid propellant at present has the following defects: (1) in the experiment, the driving agent is used for excitation, and for the composite propellant, the combustion product contains a large amount of solid particles and dust, the particle damping is large, and self-oscillation is difficult to form; (2) the propellant formulas of the driving medicine and the testing medicine are different, the pressure coupling response functions of the driving medicine and the testing medicine need to be measured respectively, each experiment needs to be carried out for several times, and the experiment times are more.
[ summary of the invention ]
The invention aims to provide a device and a method for measuring a velocity coupling response function of a first-order oscillation mode of a propellant, which aim to solve the problem of low accuracy of pressure oscillation characteristics of first-order frequency acquired in the prior art.
The invention adopts the following technical scheme: the method for measuring the speed coupling response function of the first-order oscillation mode of the propellant specifically comprises the following steps:
step 1, selecting a T-shaped combustor with the length of L according to the condition that f is a/(2L), wherein f is a pressure oscillation fundamental frequency, and a is a theoretical sound velocity at the combustion temperature of a propellant; the T-shaped combustor comprises a combustor body, propellant test piece clamps are respectively installed at two ends in the combustor body, a spray pipe communicated with the interior of the combustor body is installed at the L/2 position on the combustor body, high-frequency-response pressure sensors are respectively installed on the outer walls of two ends of the combustor body, and each pressure sensor is used for measuring a pressure oscillation signal in the combustor body; the outer walls of the two ends of the burner body are respectively provided with a trigger excitation device, and each trigger excitation device 3 is used for generating pressure oscillation in the burner body;
step 2, installing the testing flaky medicine and the testing annular medicine on the T-shaped combustor for testing, and obtaining a velocity coupling response function under the first-order sound vibration frequency according to a test result:
wherein γ is the specific heat ratio;is the average pressure; sCIs the channel area; sBIs the combustion surface area of the propellant; r is the burning rate of the propellant; rhopis the density of the propellant, alphaV(L/4)the velocity coupling term is alpha when the test tablet propellant is mounted on the propellant reagent clips 5 at both ends and the test annular propellant is mounted at the L/4 position in the T-shaped burnerV(3L/4)The velocity coupling term is obtained when the test tablet propellant is mounted on the propellant reagent clips 5 at both ends and the test ring propellant is mounted at a 3L/4 position in the T-shaped burner.
Further, the step 2 comprises the following specific steps:
step 2.1, installing the sheet propellant for testing on propellant test piece clamps at two ends of the T-shaped combustor, opening a data acquisition system, starting a pressure sensor, and simultaneously starting ignition switches of the two propellant test piece clamps to simultaneously ignite the test propellants at the two ends;
after ignition t1triggering one of the trigger excitation devices to form a first path of trigger excitation, and measuring the working pressure oscillation attenuation coefficient alpha in the combustor body by a pressure sensor1;
After the first path triggers the excitation to succeed, delaying t2triggering another trigger excitation device to form a second path of trigger excitation, and measuring the oscillation attenuation coefficient α of the working pressure in the combustor body by a pressure sensor2;
Wherein, t1T is t/2, and t is total combustion time of the propellant; t is t2=t-t1+t3When the propellant placed at both ends is a cup-shaped medicine, t310 ms; when the propellant is a tablet, t3=0ms;
attenuation coefficient alpha according to working pressure1and alpha2obtaining the net increase rate α of the sound pressure generated by the combustion of the propellantG=αc0=α1-α2,αc0The combustion surface of the propellant test piece at the two ends is gained, and a response function value with the oscillation frequency f is obtained according to the pressure coupling response function expression;
wherein,is the measured average burning rate; a is the theoretical sound velocity at the combustion temperature of the propellant; a ismTo measure the speed of sound, am=2fL;
step 2.2, the sheet propellant for testing is arranged on propellant test piece clamps at two ends of the T-shaped combustor, the annular propellant for testing is arranged at the L/4 position in the T-shaped combustor, ignition and twice triggering excitation are carried out according to the method in the step 2.1, and the net increase rate α of sound pressure generated by propellant combustion is obtained through the recorded data of the pressure sensor 4G(L/4)=αc0+αc(L/4)+αV(L/4);
wherein alpha isc(L/4)The pressure coupling term is used for mounting the test tablet propellant on propellant reagent clamps at two ends and mounting the test annular propellant at an L/4 position in a T-shaped combustor, and the test annular propellant has
Wherein, x is L/4, which is the distance between the test annular medicine and the end part of the combustion chamber;
step 2.3, installing the sheet propellant for testing on propellant test piece clamps 5 at two ends of the T-shaped combustor, installing the annular propellant for testing at the position of 3L/4 in the T-shaped combustor, igniting and triggering twice according to the method in the step 2.1, and obtaining the net increase rate α of sound pressure generated by propellant combustion through the recorded data of the pressure sensorG(3L/4)=αc0+αc(3L/4)+αV(3L/4);
wherein alpha isc(3L/4)The pressure coupling term is the pressure coupling term when the test flaky propellant is arranged on the propellant reagent clamps at the two ends and the test annular propellant is arranged at the 3L/4 position in the T-shaped combustor;
wherein, x is 3L/4, which is the distance between the test annular medicine and the end part of the combustion chamber;
step 2.4, alpha obtained according to step 2.2V(L/4)and alpha obtained in step 2.3V(3L/4)And obtaining a speed coupling response function under the first-order acoustic vibration frequency f:
further, the step 2 comprises the following specific steps:
step 2.1', the sheet propellant for testing is arranged on propellant test piece clamps at two ends of the T-shaped combustor, two same annular medicaments for testing are respectively arranged at the positions of L/4 and 3L/4 in the T-shaped combustor, a data acquisition system is turned on, a pressure sensor is started, and ignition switches of the two propellant test piece clamps are started simultaneously, so that the propellant for testing at the two ends is ignited simultaneously;
after ignition t1Triggering one of the trigger excitation devices to form a first path of trigger excitation; after the first path triggers the excitation to succeed, delay t again2Triggering another trigger excitation device to form a second path of trigger excitation; wherein, t1T is t/2, and t is total combustion time of the propellant; t is t2=t-t1+t3When the propellant placed at both ends is a cup-shaped medicine, t310 ms; when the propellant is a tablet, t3=0ms;
Obtaining the sound pressure increase rate through the recorded data of the pressure sensor
αG(L/4+3L/4)=αc0+αc(L/4)+αV(L/4)+αc(3L/4)+αV(3L/4);
wherein alpha isc0for the combustion surface gain, alpha, of the propellant test piece at the two end positionsc(L/4)α pressure coupling term of α tablet propellant for testing arranged on the propellant reagent clamps at two ends and α ring propellant for testing arranged at the L/4 position in the T-shaped burnerc(3L/4)The pressure coupling term is obtained when the test flaky propellant is arranged on the propellant reagent clamps at the two ends and the test annular propellant is arranged at the 3L/4 position in the T-shaped combustor;
step 2.2 ', the sheet propellant for testing is arranged on the propellant test piece clamps at the two ends of the T-shaped combustor, the annular propellant for testing is arranged at the L/4 position of the T-shaped combustor, ignition and twice triggering excitation are carried out according to the method in the step 2.1', and the net increase rate α of sound pressure generated by the combustion of the propellant is obtained through the recorded data of the pressure sensorG(L/4)=αc0+αc(L/4)+αV(L/4)(ii) a And is provided with
Wherein, x is L/4, which is the distance between the test annular medicine and the end part of the combustion chamber;
step 2.3 ', sheet propellant for testing is arranged on propellant test piece clamps at two ends of the T-shaped combustor, annular propellant for testing is arranged at the position of 3L/4 in the T-shaped combustor, ignition and twice triggering excitation are carried out according to the method in the step 2.1', and the net increase rate α of sound pressure generated by propellant combustion is obtained through the recorded data of the pressure sensorG(3L/4)=αc0+αc(3L/4)+αV(3L/4);
wherein alpha isc(3L/4)The pressure coupling term is the pressure coupling term when the test flaky propellant is arranged on the propellant reagent clamps at the two ends and the test annular propellant is arranged at the 3L/4 position in the T-shaped combustor;
wherein, x is 3L/4, which is the distance between the test annular medicine and the end part of the combustion chamber;
step 2.4 ', α is obtained according to step 2.1 ', step 2.2 ', step 2.3c0=α1-α2,α1、α2When the tablet propellant for testing is arranged on propellant test piece clamps at two ends of the T-shaped burner, the first path of trigger excitation and the second path of trigger excitation respectively generate working pressure oscillation attenuation coefficients in the burner body;
and a response function value R is obtainedp(f):
Wherein,is the measured average burning rate; a is the theoretical sound velocity at the combustion temperature of the propellant; a ismTo measure the speed of sound, am=2fL;
Step 2.5 ', obtaining a speed coupling response function under the first-order sound vibration frequency according to the step 2.4':
further, the thickness of the test ring is 3% L or less.
The other technical scheme of the invention is as follows: the measuring device used in the propellant first-order oscillation mode speed coupling response function measuring method comprises a T-shaped combustor with the length of L, wherein the T-shaped combustor comprises a combustor body, propellant test piece clamps with the same configuration and the same formula are installed at two ends in the combustor body, and a trigger excitation device is respectively installed on the outer walls of two ends of the combustor body and used for generating pressure oscillation in the combustor body; the outer walls of the two ends of the burner body are respectively provided with a high-frequency-response pressure sensor for measuring a pressure oscillation signal in the burner body;
the ignition control system is characterized by also comprising a data acquisition system and an ignition time sequence control system, wherein the data acquisition system is respectively connected with the pressure sensor and the trigger excitation device; the trigger excitation device and the propellant test piece clamp are both connected with an ignition time sequence control system.
The invention has the beneficial effects that: the method can accurately obtain the speed coupling response function characteristic of the solid propellant under the action of the first-order acoustic oscillation frequency, thereby laying an experimental foundation for accurately analyzing the speed coupling response characteristic of the propellant under the nonlinear combustion unstable oscillation environment of the solid rocket engine. The T-shaped combustor generates an accurate controllable single first-order frequency pressure oscillation phenomenon in the working process through external triggering excitation, and therefore a solid propellant speed coupling response function is obtained under the control of the accurate external triggering excitation.
[ description of the drawings ]
FIG. 1 is a schematic view of a T-shaped burner according to the present invention;
FIG. 2 is a schematic representation of the tablet and ring for testing in the present invention;
FIG. 3 is a graph of the test results of the present invention;
fig. 4 is a sound pressure and sound velocity distribution diagram of the first order vibration mode in the present invention.
Wherein: a T-shaped burner; 2. a burner body; 3. triggering an excitation device; 4. a pressure sensor; 5. a propellant test piece clamp; 6. a data acquisition system; 7. an ignition timing control system; 8. an annular test drug test piece clamp; 9. and (4) a spray pipe.
[ detailed description ] embodiments
The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.
The invention discloses a method for measuring a velocity coupling response function of a first-order oscillation mode of a propellant, as shown in fig. 1, fig. 2, fig. 3 and fig. 4, a T-shaped burner 1 with the length of L is selected according to f ═ a/(2L), wherein f is a pressure oscillation fundamental frequency, and a is a theoretical sound velocity at the combustion temperature of the propellant. Under the premise that the length L (oscillation fundamental frequency f) of the T-shaped combustor 1 is kept unchanged, the T-shaped combustor is triggered by adopting a two-way excitation triggering mode, and in order to ensure that only a single first-order oscillation frequency (f ═ f) is generated1) The trigger excitation device 3 is required to be arranged at two ends of the T-shaped combustor 1, and an L/2 position, namely a node of a first-order oscillation mode, is required to be arranged in order to ensure the minimum first-order acoustic energy loss of the nozzle. The test measurement adopts a secondary trigger excitation method, trigger excitation is respectively carried out at the middle time and the end time of the solid propellant in the T-shaped combustor 1 to obtain single-order pressure oscillation attenuation data, and the pressure oscillation attenuation coefficients after two times of triggering are respectively obtained by adopting a Galileo method, so as to obtain a speed coupling response function value under the action of first-order oscillation frequency, and the method specifically comprises the following steps:
step 1, selecting a T-shaped combustor 1 with the length of L according to the pressure oscillation fundamental frequency f.
As shown in fig. 1, according to f ═ a/(2L), a T-shaped burner 1 with a length L is selected, the T-shaped burner 1 comprises a burner body 2, propellant test piece holders 5 with the same configuration and formula are respectively installed at two ends in the burner body 2, a spray pipe 9 communicated with the interior of the burner body 2 is installed at the L/2 position on the burner body 2, a high-frequency response pressure sensor 4 is respectively installed on the outer wall of each of two ends of the burner body 2, and each pressure sensor 4 is used for measuring a pressure oscillation signal in the burner body 2. The outer walls of the two ends of the burner body 2 are respectively provided with a trigger excitation device 3, and each trigger excitation device 3 is used for generating pressure oscillation in the burner body 2.
Step 2, installing the flaky powder and the annular powder for testing in the T-shaped combustor 1, wherein the flaky powder and the annular powder are shown in figure 2, testing, and obtaining a velocity coupling response function under the first-order sound vibration frequency according to a test result:
wherein γ is the specific heat ratio;is the average pressure; sCIs the channel area; sBIs the combustion surface area of the propellant; r is the burning rate of the propellant; rhopis the density of the propellant, alphaV(L/4)a velocity coupling term alpha when the test tablet propellant is mounted on the propellant reagent clips 5 at both ends and the test ring propellant is mounted at the L/4 position in the T-shaped burner 1V(3L/4)The velocity coupling term is obtained when the test tablet propellant is mounted on the propellant reagent clips 5 at both ends and the test ring propellant is mounted at a 3L/4 position in the T-shaped burner 1.
Step 2 can be realized by two methods, the first method is as follows:
step 2.1, installing the sheet propellant for testing on propellant test piece clamps 5 at two ends of the T-shaped combustor 1, starting a data acquisition system 6, starting a pressure sensor 4, and simultaneously starting ignition switches of the two propellant test piece clamps 5 by adopting a multi-channel ignition time sequence control device to simultaneously ignite the test propellants at the two ends;
after ignition t1one of the trigger excitation devices 3 is triggered to form a first path of trigger excitation, and a pressure sensor 4 measures the working pressure oscillation attenuation coefficient α in the combustor body 21;
After the first path triggers the excitation to succeed, delaying t2triggering another trigger excitation device 3 to form a second trigger excitation, and measuring the oscillation attenuation coefficient α of the working pressure in the combustor body 2 by a pressure sensor 42;
Wherein, t1T is t/2, and t is total combustion time of the propellant; t is t2=t-t1+t3When the propellant is a cup-shaped drug, t310 ms; when the propellant is a tablet, t3=0ms;
oscillation attenuation coefficient α according to working pressure1and alpha2obtaining the net increase rate α of the sound pressure generated by the combustion of the propellantG=αc0=α1-α2,αc0The combustion surface of the propellant test piece at the two ends is gained, and a response function value with the oscillation frequency f is obtained according to the pressure coupling response function expression;
wherein,is the measured average burning rate; a is the theoretical sound velocity at the combustion temperature of the propellant; a ismTo measure the speed of sound, am=2fL;
step 2.2, the sheet propellant for testing is arranged on propellant test piece clamps 5 at two ends of the T-shaped combustor 1, the annular propellant for testing is arranged at the L/4 position in the T-shaped combustor 1, ignition and twice triggering excitation are carried out according to the method in the step 2.1, and the net increase rate α of sound pressure generated by propellant combustion is obtained through the recorded data of the pressure sensor 4G(L/4)=αc0+αc(L/4)+αV(L/4);
wherein alpha isc(L/4)The pressure coupling term is used for mounting the test tablet propellant on the propellant reagent clamps 5 at two ends and mounting the test annular propellant at the L/4 position in the T-shaped combustor 1, and the test annular propellant has
Here, x is L/4, which is the distance between the test ring and the combustion chamber end.
step 2.3, installing the sheet propellant for testing on propellant test piece clamps 5 at two ends of the T-shaped combustor 1, installing the annular propellant for testing at the position of 3L/4 in the T-shaped combustor 1, igniting and triggering twice according to the method in the step 2.1, and obtaining the net increase rate α of sound pressure generated by propellant combustion through the recorded data of the pressure sensor 4G(3L/4)=αc0+αc(3L/4)+αV(3L/4);
wherein alpha isc(3L/4)The pressure coupling term is the pressure coupling term when the test tablet propellant is arranged on the propellant reagent clamps 5 at the two ends and the test annular propellant is arranged at the 3L/4 position in the T-shaped combustor 1;
here, x is 3L/4, which is the distance between the test ring and the combustion chamber end.
step 2.4, alpha obtained according to step 2.2V(L/4)and alpha obtained in step 2.3V(3L/4)And obtaining a velocity coupling response function under the first-order acoustic vibration frequency:
the second specific method adopted in the step 2 is as follows:
step 2.1', the sheet propellant for testing is arranged on propellant test piece clamps 5 at two ends of the T-shaped combustor 1, two same annular medicaments for testing are respectively arranged at the positions of L/4 and 3L/4 in the T-shaped combustor 1, a data acquisition system 6 is turned on, a pressure sensor 4 is started, and ignition switches of the two propellant test piece clamps 5 are started simultaneously, so that the propellant for testing at the two ends is ignited simultaneously;
after ignition t1Triggering one of the trigger excitation devices 3 to form a first path of trigger excitation; after the first path triggers the excitation to succeed, delay t again2Triggering another trigger excitation device 3 to form a second path of trigger excitation; wherein, t1T is t/2, and t is total combustion time of the propellant; t is t2=t-t1+t3When the propellant placed at both ends is a cup-shaped medicine, t310 ms; when the propellant is a tablet, t3=0ms;
The sound pressure increase rate is obtained through the recorded data of the pressure sensor 4
αG(L/4+3L/4)=αc0+αc(L/4)+αV(L/4)+αc(3L/4)+αV(3L/4);
wherein alpha isc0for the combustion surface gain, alpha, of the propellant test piece at the two end positionsc(L/4)α pressure coupling term alpha for mounting the test tablet propellant on the propellant reagent clamps 5 at the two ends and mounting the test annular propellant at the L/4 position in the T-shaped burner 1c(3L/4)Will be used for testingThe tablet propellant is arranged in propellant reagent clamps 5 at two ends, and the annular propellant for testing is arranged in a pressure coupling term at a 3L/4 position in the T-shaped combustor 1;
step 2.2 ', the sheet propellant for testing is arranged on the propellant test piece clamps 5 at the two ends of the T-shaped combustor 1, the annular propellant for testing is arranged at the L/4 position in the T-shaped combustor 1, ignition and twice triggering excitation are carried out according to the method in the step 2.1', and the net increase rate α of sound pressure generated by propellant combustion is obtained through the recorded data of the pressure sensor 4G(L/4)=αc0+αc(L/4)+αV(L/4)(ii) a And is provided with
Here, x is L/4, which is the distance between the test ring and the combustion chamber end.
step 2.3 ', the sheet propellant for testing is arranged on the propellant test piece clamps 5 at the two ends of the T-shaped combustor 1, the annular propellant for testing is arranged at the 3L/4 position in the T-shaped combustor 1, ignition and twice triggering excitation are carried out according to the method in the step 2.1', and the net increase rate α of sound pressure generated by propellant combustion is obtained through the recorded data of the pressure sensor 4G(3L/4)=αc0+αc(3L/4)+αV(3L/4);
wherein alpha isc(3L/4)The pressure coupling term is the pressure coupling term when the test tablet propellant is arranged on the propellant reagent clamps 5 at the two ends and the test annular propellant is arranged at the 3L/4 position in the T-shaped combustor 1;
here, x is 3L/4, which is the distance between the test ring and the combustion chamber end.
Step 2.4 ', according to step 2.1', step2.2 ', step 2.3' gives αc0=α1-α2,α1、α2When the tablet propellant for testing is arranged on the propellant test piece clamps 5 at the two ends of the T-shaped combustor 1, the first path of trigger excitation and the second path of trigger excitation respectively generate working pressure oscillation attenuation coefficients in the combustor body 2;
and a response function value R is obtainedp(f):
Wherein,is the measured average burning rate; a is the theoretical sound velocity at the combustion temperature of the propellant; a ismTo measure the speed of sound, am=2fL;
Step 2.5 ', obtaining a speed coupling response function under the first-order sound vibration frequency according to the step 2.4':
the thickness of the test ring in each step of the above two methods is less than or equal to 3% L.
The invention also discloses a measuring device used in the method for measuring the velocity coupling response function of the first-order oscillation mode of the propellant, which comprises a T-shaped burner 1 with the length of L, wherein the T-shaped burner 1 comprises a burner body 2, propellant test piece clamps 5 with the same configuration and the same formula are arranged at two ends in the burner body 2, and trigger exciting devices 3 are respectively arranged on the outer walls at two ends of the burner body 2 and are used for generating pressure oscillation in the burner body 2; the outer walls of the two ends of the burner body 2 are respectively provided with a high-frequency-response pressure sensor 4 for measuring a pressure oscillation signal in the burner body 2;
the ignition control system also comprises a data acquisition system 6 and an ignition time sequence control system 7, wherein the data acquisition system 6 is respectively connected with the pressure sensor 4 and the trigger excitation device 3; the trigger excitation device 3 and the propellant test piece clamp 5 are both connected with an ignition sequence control system 7.
Claims (5)
1. The method for measuring the velocity coupling response function of the first-order oscillation mode of the propellant is characterized by comprising the following steps:
step 1, selecting a T-shaped combustor (1) with the length of L according to the condition that f is a/(2L), wherein f is a pressure oscillation fundamental frequency, and a is a theoretical sound velocity at the combustion temperature of a propellant; the T-shaped combustor (1) comprises a combustor body (2), propellant test piece clamps (5) are respectively installed at two ends in the combustor body (2), a spray pipe (9) communicated with the interior of the combustor body (2) is installed at the position of L/2 of the combustor body (2), high-frequency-response pressure sensors (4) are respectively installed on the outer walls of two ends of the combustor body (2), and each pressure sensor (4) is used for measuring a pressure oscillation signal in the combustor body (2); the outer walls of the two ends of the burner body (2) are respectively provided with a trigger excitation device (3), and each trigger excitation device (3) is used for generating pressure oscillation in the burner body (2);
step 2, installing the testing flaky medicine and the testing annular medicine in the T-shaped combustor (1), testing, and obtaining a velocity coupling response function under the first-order sound vibration frequency according to a test result:
wherein γ is the specific heat ratio;is the average pressure; sCIs the channel area; sBIs the combustion surface area of the propellant; r is the burning rate of the propellant; rhopis the density of the propellant, alphaV(L/4)the velocity coupling term is alpha when the test tablet propellant is arranged on the propellant reagent clips (5) at the two ends and the test annular propellant is arranged in the T-shaped burner (1) at the L/4 positionV(3L/4)The velocity coupling term is obtained when the test tablet propellant is mounted on the propellant reagent clips (5) at both ends and the test annular propellant is mounted at the 3L/4 position in the T-shaped burner (1).
2. The method for measuring the velocity coupling response function of the first-order oscillation mode of the propellant according to claim 1, wherein the specific method in the step 2 is as follows:
step 2.1, installing the sheet propellant for testing on propellant test piece clamps (5) at two ends of a T-shaped combustor (1), turning on a data acquisition system (6), starting a pressure sensor (4), and simultaneously starting ignition switches of the two propellant test piece clamps (5) to simultaneously ignite the propellant for testing at the two ends;
after ignition t1Time to trigger one of the trigger excitation devices (3) to form a first trigger excitationthe oscillation attenuation coefficient alpha of the working pressure in the combustor body (2) is measured by a pressure sensor (4)1;
After the first path triggers the excitation to succeed, delaying t2triggering another trigger excitation device (3) to form a second trigger excitation, and measuring the working pressure oscillation attenuation coefficient alpha in the combustor body (2) by a pressure sensor (4)2;
Wherein, t1T is t/2, and t is total combustion time of the propellant; t is t2=t-t1+t3When the propellant is a cup-shaped drug, t310 ms; when the propellant is a tablet, t3=0ms;
oscillation attenuation coefficient α according to working pressure1and alpha2obtaining the net increase rate α of the sound pressure generated by the combustion of the propellantG=αc0=α1-α2,αc0The combustion surface of the propellant test piece at the two ends is gained, and a response function value with the oscillation frequency f is obtained according to the pressure coupling response function expression;
wherein,is the measured average burning rate; a is the theoretical sound velocity at the combustion temperature of the propellant; a ismTo measure the speed of sound, am=2fL;
step 2.2, installing the sheet propellant for testing on propellant test piece clamps (5) at two ends of the T-shaped combustor (1), installing the annular propellant for testing at the L/4 position in the T-shaped combustor (1), igniting and triggering twice according to the method in the step 2.1, and obtaining the net increase rate α of sound pressure generated by propellant combustion through the recorded data of the pressure sensor (4)G(L/4)=αc0+αc(L/4)+αV(L/4);
wherein alpha isc(L/4)For mounting the test tablet propellant on propellant reagent clips (5) at both ends and mounting the test tablet propellant on the propellant reagent clipsThe pressure coupling term of the annular medicine is used for testing when the annular medicine is arranged at the L/4 position in the T-shaped combustor (1) and is provided with
Wherein, x is L/4, which is the distance between the test annular medicine and the end part of the combustion chamber;
step 2.3, installing the sheet propellant for testing on propellant test piece clamps (5) at two ends of the T-shaped combustor (1), installing the annular propellant for testing at the 3L/4 position in the T-shaped combustor (1), igniting and triggering twice according to the method in the step 2.1, and obtaining the net increase rate α of sound pressure generated by propellant combustion through the recorded data of the pressure sensor (4)G(3L/4)=αc0+αc(3L/4)+αV(3L/4);
wherein alpha isc(3L/4)The pressure coupling term is the pressure coupling term when the test flaky propellant is arranged on the propellant reagent clamps (5) at the two ends and the test annular propellant is arranged at the 3L/4 position in the T-shaped combustor (1);
wherein, x is 3L/4, which is the distance between the test annular medicine and the end part of the combustion chamber;
step 2.4, alpha obtained according to step 2.2V(L/4)and alpha obtained in step 2.3V(3L/4)And obtaining a speed coupling response function under the first-order acoustic vibration frequency f:
3. the method for measuring the velocity coupling response function of the first-order oscillation mode of the propellant according to claim 1, wherein the specific method in the step 2 is as follows:
step 2.1', sheet propellant for testing is arranged on propellant test piece clamps (5) at two ends of a T-shaped combustor (1), two same annular propellant for testing are respectively arranged at the positions of L/4 and 3L/4 in the T-shaped combustor (1), a data acquisition system (6) is turned on, a pressure sensor (4) is started, and ignition switches of the two propellant test piece clamps (5) are simultaneously started to simultaneously ignite the propellant for testing at the two ends;
after ignition t1Time, trigger one of the trigger excitation devices (3) to form a first path of trigger excitation; after the first path triggers the excitation to succeed, delay t again2Triggering another trigger excitation device (3) to form a second path of trigger excitation; wherein, t1T is t/2, and t is total combustion time of the propellant; t is t2=t-t1+t3When the propellant placed at both ends is a cup-shaped medicine, t310 ms; when the propellant is a tablet, t3=0ms;
Obtaining the sound pressure increase rate through the recorded data of the pressure sensor (4)
αG(L/4+3L/4)=αc0+αc(L/4)+αV(L/4)+αc(3L/4)+αV(3L/4);
wherein alpha isc0for the combustion surface gain, alpha, of the propellant test piece at the two end positionsc(L/4)α pressure coupling term of α tablet propellant for test mounted on the propellant reagent clamps (5) at both ends and α ring propellant for test mounted at the L/4 position in the T-shaped burner (1); alphac(3L/4)The pressure coupling term is obtained when the test flaky propellant is arranged on the propellant reagent clamps (5) at the two ends and the test annular propellant is arranged at the 3L/4 position in the T-shaped combustor (1);
step 2.2 ', sheet-shaped propellant for testing is arranged on propellant test piece clamps (5) at two ends of a T-shaped combustor (1), annular propellant for testing is arranged at the position of L/4 in the T-shaped combustor (1), ignition and twice triggering excitation are carried out according to the method in the step 2.1', and the net increase rate α of sound pressure generated by propellant combustion is obtained through the recorded data of the pressure sensor (4)G(L/4)=αc0+αc(L/4)+αV(L/4)(ii) a And is provided with
Wherein, x is L/4, which is the distance between the test annular medicine and the end part of the combustion chamber;
step 2.3 ', sheet-shaped propellant for testing is arranged on propellant test piece clamps (5) at two ends of a T-shaped combustor (1), annular propellant for testing is arranged at the position of 3L/4 in the T-shaped combustor (1), ignition and twice triggering excitation are carried out according to the method in the step 2.1', and the net increase rate α of sound pressure generated by propellant combustion is obtained through the recorded data of the pressure sensor (4)G(3L/4)=αc0+αc(3L/4)+αV(3L/4);
wherein alpha isc(3L/4)The pressure coupling term is the pressure coupling term when the test flaky propellant is arranged on the propellant reagent clamps (5) at the two ends and the test annular propellant is arranged at the 3L/4 position in the T-shaped combustor (1);
wherein, x is 3L/4, which is the distance between the test annular medicine and the end part of the combustion chamber;
step 2.4 ', α is obtained according to step 2.1 ', step 2.2 ', step 2.3c0=α1-α2,α1、α2When the tablet propellant for testing is arranged on propellant test piece clamps (5) at two ends of a T-shaped burner (1), the first path of trigger excitation and the second path of trigger excitation respectively generate working pressure oscillation attenuation coefficients in a burner body (2);
and a response function value R is obtainedp(f):
Wherein,is the measured average burning rate; a is the principle at the combustion temperature of the propellantThe theoretical sound velocity; a ismTo measure the speed of sound, am=2fL;
Step 2.5 ', obtaining a speed coupling response function under the first-order sound vibration frequency according to the step 2.4':
4. the method of measuring a velocity coupled response function of a first order mode of oscillation of a propellant according to any of claims 1 to 3, wherein the thickness of the test ring is 3% L or less.
5. A measuring device used in the method for measuring the velocity coupling response function of the first-order oscillation mode of the propellant is characterized by comprising a T-shaped burner (1) with the length L, wherein the T-shaped burner (1) comprises a burner body (2), propellant test piece clamps (5) with the same configuration and the same formula are arranged at two ends in the burner body (2), and a triggering excitation device (3) is respectively arranged on the outer walls of the two ends of the burner body (2) and is used for generating pressure oscillation in the burner body (2); the outer walls of the two ends of the burner body (2) are respectively provided with a high-frequency response pressure sensor (4) for measuring a pressure oscillation signal in the burner body (2);
the ignition control system is characterized by further comprising a data acquisition system (6) and an ignition time sequence control system (7), wherein the data acquisition system (6) is respectively connected with the pressure sensor (4) and the trigger excitation device (3); the trigger excitation device (3) and the propellant test piece clamp (5) are both connected with an ignition timing sequence control system (7).
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