CN108181423B - Propellant first-order oscillation mode speed coupling response function measuring device and method - Google Patents

Propellant first-order oscillation mode speed coupling response function measuring device and method Download PDF

Info

Publication number
CN108181423B
CN108181423B CN201711161457.0A CN201711161457A CN108181423B CN 108181423 B CN108181423 B CN 108181423B CN 201711161457 A CN201711161457 A CN 201711161457A CN 108181423 B CN108181423 B CN 108181423B
Authority
CN
China
Prior art keywords
propellant
test
shaped
combustor
pressure
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
CN201711161457.0A
Other languages
Chinese (zh)
Other versions
CN108181423A (en
Inventor
金秉宁
刘佩进
徐冠宇
李阳
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Northwestern Polytechnical University
Original Assignee
Northwestern Polytechnical University
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Northwestern Polytechnical University filed Critical Northwestern Polytechnical University
Priority to CN201711161457.0A priority Critical patent/CN108181423B/en
Publication of CN108181423A publication Critical patent/CN108181423A/en
Application granted granted Critical
Publication of CN108181423B publication Critical patent/CN108181423B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • 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
    • G01N31/12—Investigating or analysing non-biological materials by the use of the chemical methods specified in the subgroup; Apparatus specially adapted for such methods using combustion

Landscapes

  • Health & Medical Sciences (AREA)
  • Chemical & Material Sciences (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Physics & Mathematics (AREA)
  • Combustion & Propulsion (AREA)
  • Molecular Biology (AREA)
  • Engineering & Computer Science (AREA)
  • Analytical Chemistry (AREA)
  • Biochemistry (AREA)
  • General Health & Medical Sciences (AREA)
  • General Physics & Mathematics (AREA)
  • Immunology (AREA)
  • Pathology (AREA)
  • Investigating Or Analyzing Materials Using Thermal Means (AREA)

Abstract

The invention discloses a propellant first-order oscillation mode speed coupling response function measuring method, which comprises the steps of selecting a T-shaped burner with the length of L, wherein the T-shaped burner comprises a burner body, propellant test piece clamps with the same configuration and formula are respectively installed at two ends in the burner body, a spray pipe communicated with the interior of the burner body is installed at the L/2 position on the burner body, high-frequency response pressure sensors are respectively installed on the outer walls of two ends of the burner body, a trigger excitation device is respectively installed on the outer walls of two ends of the burner body, and a speed coupling response function under a first-order sound vibration frequency is realized by installing a sheet-shaped medicine and an annular test medicine on the T-shaped burner; the problem of the pressure oscillation characteristic low precision of the first order frequency that obtains among the prior art is solved.

Description

Propellant first-order oscillation mode speed coupling response function measuring device and method
[ 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:
Figure BDA0001475321070000021
wherein γ is the specific heat ratio;
Figure BDA0001475321070000022
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, t 310 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;
Figure BDA0001475321070000031
wherein the content of the first and second substances,
Figure BDA0001475321070000032
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
Figure BDA0001475321070000033
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, the tablet propellant for testing is arranged on propellant test piece clamps 5 at two ends of the T-shaped combustor,and the annular medicine 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;
Figure BDA0001475321070000034
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:
Figure BDA0001475321070000041
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, t 310 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
Figure BDA0001475321070000051
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)For propulsion with test tablet propellant mounted at both endsThe pressure coupling term is arranged on the reagent clamp and is used for installing the annular medicine for testing at the 3L/4 position in the T-shaped combustor;
Figure BDA0001475321070000052
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)：
Figure BDA0001475321070000053
Wherein the content of the first and second substances,
Figure BDA0001475321070000054
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':
Figure BDA0001475321070000055
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, which is shown in fig. 1, fig. 2, fig. 3 and fig. 4, wherein f is a/(2L) and is selectedAnd (3) a T-shaped burner 1 with the fixed length L, wherein f is the pressure oscillation fundamental frequency, and a is the 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:
Figure BDA0001475321070000081
wherein γ is the specific heat ratio;
Figure BDA0001475321070000082
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, t 310 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 two ends is increased according to the pressure intensityObtaining a response function value with the oscillation frequency f by the coupling response function expression;
Figure BDA0001475321070000083
wherein the content of the first and second substances,
Figure BDA0001475321070000084
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
Figure BDA0001475321070000091
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)For mounting the test tablet propellant on propellant reagent clips 5 at both ends, andthe pressure coupling term when the annular medicine for testing is arranged at the 3L/4 position in the T-shaped combustor 1;
Figure BDA0001475321070000092
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:
Figure BDA0001475321070000093
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, t 310 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 burning surfaces of propellant test pieces at both end positionsgain, alphac(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)The pressure coupling term is obtained 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;
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
Figure BDA0001475321070000101
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;
Figure BDA0001475321070000111
here, x is 3L/4, which is the distance between the test ring and the combustion chamber end.
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 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)：
Figure BDA0001475321070000112
Wherein the content of the first and second substances,
Figure BDA0001475321070000113
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':
Figure BDA0001475321070000114
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 (4)

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:
Figure FDA0002290679670000011
wherein γ is the specific heat ratio;
Figure FDA0002290679670000012
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)For mounting the test tablet propellant in propellant reagent clips (5) at both ends, andthe velocity coupling term when the annular agent is installed at a 3L/4 position in the T-shaped burner (1) is tested.
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 t1one of the trigger excitation devices (3) is triggered to form a first path of trigger excitation, and a pressure sensor (4) is used for measuring the oscillation attenuation coefficient α of the working pressure in the combustor body (2)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;
Figure FDA0002290679670000021
wherein the content of the first and second substances,
Figure FDA0002290679670000022
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)The pressure coupling term is used 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 L/4 position in the T-shaped combustor (1), and the pressure coupling term is provided
Figure FDA0002290679670000031
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);
Figure FDA0002290679670000032
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:
Figure FDA0002290679670000033
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)The test tablet propellant is mounted on propellant reagent clips (5) at two ends, and the test ring propellant is mounted on a T-shapedpressure coupling term of L/4 position in burner (1) < alpha >c(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
Figure FDA0002290679670000041
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);
Figure FDA0002290679670000051
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)：
Figure FDA0002290679670000052
Wherein the content of the first and second substances,
Figure FDA0002290679670000053
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':
Figure FDA0002290679670000054
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.
CN201711161457.0A 2017-11-21 2017-11-21 Propellant first-order oscillation mode speed coupling response function measuring device and method Active CN108181423B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201711161457.0A CN108181423B (en) 2017-11-21 2017-11-21 Propellant first-order oscillation mode speed coupling response function measuring device and method

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201711161457.0A CN108181423B (en) 2017-11-21 2017-11-21 Propellant first-order oscillation mode speed coupling response function measuring device and method

Publications (2)

Publication Number Publication Date
CN108181423A CN108181423A (en) 2018-06-19
CN108181423B true CN108181423B (en) 2020-06-02

Family

ID=62545080

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201711161457.0A Active CN108181423B (en) 2017-11-21 2017-11-21 Propellant first-order oscillation mode speed coupling response function measuring device and method

Country Status (1)

Country Link
CN (1) CN108181423B (en)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
CN113530716B (en) * 2021-07-05 2022-08-12 上海机电工程研究所 Solid propellant fluctuation combustion pressure coupling response function measuring device and method
CN114354201A (en) * 2022-01-04 2022-04-15 中国航发贵阳发动机设计研究所 Method for acquiring experimental modal parameters of jet pipe of aircraft engine

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5366371A (en) * 1991-11-18 1994-11-22 Manufacturing And Technology Conversion International, Inc. Process and apparatus utilizing an improved pulse combustor for atomizing liquids and slurries
GB2496092A (en) * 2011-07-07 2013-05-08 John Montgomery Water treatment

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2001289123A (en) * 2000-04-03 2001-10-19 Natl Space Development Agency Of Japan Pressure reducing device for high-altitude test
CN103018397A (en) * 2012-11-19 2013-04-03 苏万兴 Secondary pulsating pressure coupling response measuring method
CN103075270B (en) * 2013-01-15 2015-01-28 西北工业大学 High-pressure-intensity external pulse excitation device for T-shaped burner
CN103122807B (en) * 2013-01-16 2014-11-12 西北工业大学 Multichannel solid rocket engine ignition sequence control method

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5366371A (en) * 1991-11-18 1994-11-22 Manufacturing And Technology Conversion International, Inc. Process and apparatus utilizing an improved pulse combustor for atomizing liquids and slurries
GB2496092A (en) * 2011-07-07 2013-05-08 John Montgomery Water treatment

Non-Patent Citations (13)

* Cited by examiner, † Cited by third party
Title
Effect of Pressure and Velocity coupling on Low-Frequency Instability;E .E.Stepp;《AIAA Journal》;19670531;第5卷(第5期);全文 *
Erosion Mechanism for Nonlinear Instability in the Axial Modes of Solid Propellant Rocket Motors;F. T. McCLURE;《ARS JOURNAL》;20130724;全文 *
Finite Acoustic Oscillations and Erosive Burning in Solid Fuel Rockets;J. F. BIRD;《AIAA JOURNAL》;19651231;第3卷(第12期);全文 *
J. F. BIRD.Finite Acoustic Oscillations and Erosive Burning in Solid Fuel Rockets.《AIAA JOURNAL》.1965,第3卷(第12期),全文. *
Nonlinear Heterogeneous Model of Composite Solid-Propellant Combustion;B. Rasmussen;《JOURNAL OF PROPULSION AND POWER》;20021231;第18卷(第5期);全文 *
Solid Propellant Combustion in a High-Velocity Cross-Flow of Gases (Review);V. A. Arkhipov;《Combustion, Explosion, and Shock Waves》;20161231;第52卷(第5期);全文 *
SOLID-PROPELLANT COMBUSTION II?JSTABILITY AND THE ROLE OF VELOCITY COUPLING;Louis A. Povinelli;《NATIONAL AERONAUTICS AND SPACE ADMINISTRATION》;19691231;全文 *
T-Burner Data and Combustion Instability in Solid Propellant Rockets;F. E. c. CULICK;《AIAA JOURNAL》;19690630;第7卷(第6期);全文 *
THEORY OF ACOUSTIC INSTABILITY IN SOLID-PROPELLANT ROCKET COMBUSTION;R. W. HART;《Tenth Symposium (International) on Combustion》;19651231;全文 *
Velocity Coupling Experiments of Solid Propellant Acoustic Oscillating Combustion;Lu Zhen-Zhong;《AIAA/SAE/ASME 20th Joint Propulsion Conference》;19840611;全文 *
Velocity-Coupled Flow Oscillations in a Simulated Solid-Propellant Rocket Environment;V. Yang;《AlAA 26th Aerospace Sciences Meeting》;19880111;全文 *
固体推进剂速度藕合响应函数研究;王明雄;《固体火箭技术》;19920331(第1期);全文 *
固体火箭发动机不稳定燃烧的速度祸合模型的研究;吕振中;《推进技术》;19951231(第6期);全文 *

Also Published As

Publication number Publication date
CN108181423A (en) 2018-06-19

Similar Documents

Publication Publication Date Title
CN108181423B (en) Propellant first-order oscillation mode speed coupling response function measuring device and method
CN103122807B (en) Multichannel solid rocket engine ignition sequence control method
Gupta et al. Various methods for the determination of the burning rates of solid propellants: an overview
CN103075270B (en) High-pressure-intensity external pulse excitation device for T-shaped burner
Falempin et al. Recent experimental results obtained on continuous detonation wave engine
CN105974049B (en) A kind of device and measuring method for measuring the instantaneous burn rate of solid propellant
CN109505712A (en) It is a kind of for measuring the impulse generator of solid propellant rocket combustion instability
CN104457457B (en) Testing delay of detonator delay element new method
Klingenberg Investigation of combustion phenomena associated with the flow of hot propellant gases. III: Experimental survey of the formation and decay of muzzle flow fields and of pressure measurements
Pandiya et al. Efficacy of acoustics in determining the operating mode of a rotating detonation engine
Ishii et al. Behavior of detonation waves at low pressures
CN111397768B (en) Multi-channel ms-level dynamic pressure and quick response temperature calibration system and method
CN108181424A (en) The speed coupling response function measurement device and method of propellant order Oscillating mode
Hasson et al. Transition from deflagration to detonation, spark ignition, and detonation characteristics of ethylene-oxygen mixtures in a tube
Hoskin et al. The motion of plates and cylinders driven by detonation waves at tangential incidence
Nagai et al. A study on DDT processes in a narrow channel
Levin et al. Features of combustion product flow structure in a spherical semi-open cavity
CN115013187B (en) Solid propellant pressure coupling response function measurement method and mold
Barbour et al. The impact of a converging-diverging nozzle on PDE performance and its associated flowfield
JPH07301151A (en) Burner for testing solid propellant vibration combustion characteristic
Caldwell et al. Acoustic measurements of multiple pulse detonation engines firing out of phase
US3788126A (en) Pulsed end-burning t-burner
Elkarous et al. Investigation on gas pressure measurement inside small caliber weapons with piezoelectric transducers
WO2005038451A3 (en) Mass spectrometer for entrained particles, and method for measuring masses of the particles
Baklanov et al. Formation of high-speed gas flow at combustion in the regime of multi-step detonation

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant