CN109252982B - Test method for nonlinear unstable combustion of solid rocket engine under overload condition - Google Patents
Test method for nonlinear unstable combustion of solid rocket engine under overload condition Download PDFInfo
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Abstract
The invention discloses a method for testing nonlinear unstable combustion of a solid rocket engine under an overload condition, and belongs to the field of unstable combustion of the solid rocket engine. The invention increases the overload condition on the basis of the static unstable combustion test on the ground of the solid rocket engine; the solid rocket engine is arranged on a ground high overload test device, and the overload angle theta and the rotating speed omega of the high overload test device are adjusted to ensure that the solid rocket engine has accelerated speeds in different directions and different magnitudes, so that the solid rocket engine works under different overload conditions; after ignition work, a pulse trigger arranged at the end socket generates pulses to trigger the unstable combustion phenomenon of the solid rocket engine, and meanwhile, the combustion state of the solid rocket engine is observed and recorded through a standard inner ballistic trajectory pressure sensor and a high-frequency response pressure sensor; by changing the test variables and analyzing the coupling effect between the overload and other test variables, the nonlinear unstable combustion test of the solid rocket engine under the overload condition is realized.
Description
Technical Field
The invention relates to a test method for nonlinear unstable combustion of a solid rocket engine under an overload condition, and belongs to the field of unstable combustion of the solid rocket engine.
Background
With the continuous development of missile weapons and aerospace propellant technologies, the requirements of high thrust, long range and the like are continuously provided, and more high-energy propellants are applied to solid rocket engines (SRM). The high-energy composite propellant is easy to cause the problem of unstable combustion, the inner ballistic curve is abnormal if the high-energy composite propellant is easy to cause, and the solid rocket engine is exploded if the high-energy composite propellant is serious, so the theory of unstable combustion of the composite propellant is always a hot point of research. The specific mechanism of the nonlinear unstable combustion is still lack of an authoritative model, the theoretical research is still in a starting stage, and the problem that the nonlinear unstable combustion has urgent need in engineering is solved.
Meanwhile, with the development of low-altitude and air-to-air missiles, the maneuverability of the missiles has higher requirements, so that the SRM can work under larger transverse and axial overload working conditions. The acceleration field under the overload condition can generate larger influence on the combustion process, so the combustion condition of the propellant can be more complicated under the high overload working condition, and meanwhile, the unstable combustion of the solid rocket engine can be caused, so that the solid rocket engine works abnormally and is even scrapped. Because the combustion of the SRM under the overload condition involves many complex physical and chemical processes and can couple with other factors affecting unstable combustion, the problem of the influence of the overload condition on the combustion of the solid rocket engine is the key and difficult point of the current solid rocket engine research.
At the end of the 20 th century, professors Blomshield, the Naval air war Center (Naval air surface Center), conducted a number of experiments on solid rocket engines operating under ground static conditions, and tested the effect of various factors on unstable combustion in detail, for the problems of linear and nonlinear unstable combustion. People have carried out a large amount of experiments to unstable combustion, have obtained the law of influence of each factor, but the experiment of most unstable combustion at present is only carried out under the static condition of ground, do not consider the influence of the high overload condition that the solid rocket engine receives under the actual conditions. Because the overload condition has great influence on the working process and the unstable combustion phenomenon of the solid rocket engine, the existing test conclusion cannot be completely suitable for the solid rocket engine working under the real working condition. With respect to the influence of overload on the combustion process, foreign researchers have relatively deeply understood the combustion law of solid propellants under overload conditions, for example, Glick conducts a large number of tests under the funding of Thiokol chemical Corporation, and summarizes the influence of overload on the combustion speed of the propellants through theoretical and experimental comparison, but does not explain the coupling effect between overload and unstable combustion; while the domestic research stage of summarizing the influence of overload on combustion through a large number of tests still needs to be carried out, the unstable combustion mechanism of the solid rocket engine under the overload condition is far from being understood. The coupling between overload conditions and other factors affecting nonlinear unstable combustion remains to be further disclosed.
Disclosure of Invention
The invention aims to solve the problems that the difference between the obtained law and the real working condition is large and the coupling effect of the overload condition and the unstable combustion is not clear because the nonlinear unstable combustion theory of the solid rocket engine is not complete at present and the test condition does not consider the influence of the overload condition on the actual working condition. The working conditions which can be tested by the invention comprise: (1) testing the internal ballistic performance of the solid rocket engine under the overload condition, wherein unstable combustion is caused by pulse triggering; (2) different overload conditions are obtained by adjusting the overload angle and the rotating speed of the high overload testing device, and testing under different overload conditions is carried out; (3) and carrying out a nonlinear unstable combustion test of the solid rocket engine under the conditions of different overload conditions, working pressures, propellant types, stability additives, lengths of the solid rocket engine and pulse intensities by changing test variables. Through the test to above-mentioned operating mode, the complicated overload state of simulation solid rocket engine when actual high altitude construction, turn, the coupling effect between the influence factor that complicated overload state produced to nonlinear unstable combustion and overload and nonlinear unstable combustion is analyzed, and then solve relevant engineering problem.
The purpose of the invention is realized by the following technical scheme.
The invention discloses a method for testing nonlinear unstable combustion of a solid rocket engine under an overload condition, which is characterized in that the overload condition is added on the basis of a ground static unstable combustion test of the solid rocket engine, and comprises an overload angle theta and an overload acceleration a. The solid rocket engine is arranged on the ground high overload test device, and the overload angle theta and the rotating speed omega of the high overload test device are adjusted, so that the solid rocket engine has accelerated speeds in different directions and different magnitudes, and works under different overload conditions. After the solid rocket engine is ignited to work, the pulse trigger arranged at the end socket generates pulses to trigger the combustion instability phenomenon of the solid rocket engine, and meanwhile, the combustion state in the solid rocket engine is observed and recorded through the standard inner ballistic trajectory pressure sensor and the high-frequency response pressure sensor. The test variables comprise overload conditions, working pressure, propellant types, stability additives, length and pulse intensity of the solid rocket engine, and the nonlinear unstable combustion test of the solid rocket engine under the overload conditions is realized by changing the conditions of the test variables and analyzing the coupling effect between overload and other test variables. Through the test to above-mentioned operating mode, the complicated overload state of simulation solid rocket engine when actual high altitude construction, turn, the coupling effect between the influence factor that complicated overload state produced to nonlinear unstable combustion and overload and nonlinear unstable combustion is analyzed, and then solve relevant engineering problem.
Preferably, the ground high overload testing device mainly comprises a multi-angle measuring device, a bearing shaft, a rotating main shaft, a large cantilever, a variable frequency motor and a commutator. The rotating main shaft is connected with an output shaft of the commutator through a coupler, has axial rotation with the angular velocity omega, and is used for driving the large cantilever to axially rotate. The two sides of the large cantilever are provided with multi-angle measuring devices which mainly comprise connecting blocks, connecting rods and fixing pieces and are used for realizing multi-angle installation of the solid rocket engine. The connecting rod links to each other with connecting block, mounting respectively, and length can be adjusted. The fixing piece is used for fixedly mounting the solid rocket engine, one end of the fixing piece is fixed, and the other end of the fixing piece is connected with the connecting rod. When the length of the connecting rod is changed, the fixing piece can rotate along the fixed end. The solid rocket engine to be tested is fixed on the fixing piece, and in the test, the length of the connecting rod is changed, so that the included angle between the axis of the fixing piece and the horizontal line of the test bed is different in overload angle theta, and the multi-angle overload installation of the ground height overload testing device on the solid rocket engine is realized. The rotating speed omega of the variable frequency motor is adjusted, and the variable frequency motor is transmitted to the solid rocket engine through the transmission main shaft and the large cantilever, so that the solid rocket engine fixed on the multi-angle measuring device obtains centrifugal acceleration a with different sizes, different overload accelerations are obtained, and the solid rocket engine is tested under different overload conditions. The overload condition includes an overload angle theta and an overload acceleration a.
Preferably, different overload angles theta are obtained by adjusting the included angle theta between the axis of the fixing piece and the horizontal line of the test bed, the rotating speed omega of the variable frequency motor is adjusted simultaneously, and finally overload conditions of different sizes are obtained, wherein the distance from the center of mass of the solid rocket engine to the axis of the rotating shaft is L, and at the moment, the solid rocket engine is in a solid stateThe centrifugal acceleration a of the engine is L omega2. The gravity acceleration borne by the solid rocket engine is small compared with the centrifugal acceleration, so that the gravity acceleration can be ignored. At a certain position of the burning surface of the propellant, the included angle between the acceleration a and the burning surface is theta, and the included angle between the acceleration a and the normal direction of the burning surface is 90-theta. Therefore, the normal acceleration a of the combustion surfacen＝acos(90°-θ)＝Lω2sin theta; tangential acceleration of combustion surface an＝acosθ＝Lω2cos θ. Therefore, different overload conditions are obtained by adjusting and adjusting the rotating speed omega of the variable frequency motor and the included angle theta between the axial direction of the connecting piece and the horizontal line, and the test of the nonlinear unstable combustion performance of the solid rocket engine under different overload conditions is realized.
Preferably, the unstable combustion of the solid rocket engine is triggered by an impulse. The pulse trigger arranged at the end socket generates pulses, and the pulse frequency is selected to be three times.
Preferably, in order to test the influence of the pressure on the nonlinear unstable combustion in the overload process, the working pressure of the solid rocket engine is adjusted in the test process; to test the effect of the stability additives on unstable combustion in the presence of an overload, part of the propellant was replaced by a different stability additive and a test comparison was carried out. In order to test the influence of the propellant type on the combustion state when overload exists, different types of propellant types are selected for the solid rocket engine to carry out the test. In order to test the influence of the length or oscillation frequency of the solid rocket engine on the combustion state when overload exists, solid rocket engines with different lengths are selected for testing.
The test method for the nonlinear unstable combustion of the solid rocket engine under the overload condition preferably comprises the following steps:
the method comprises the following steps: before the test starts, the end socket device of the solid rocket engine is debugged, whether the connecting line is intact and whether the sensor is reasonably installed or not are tested, and whether the end socket device can normally work or not is tested.
Step two: and determining test variables according to test requirements, and selecting proper propellant types, combustion chamber pressure, solid rocket engine length and propellant formulas.
Step three: and determining the overload angle theta and the device rotating speed omega of the solid rocket engine according to the test overload requirement. And (3) mounting the solid rocket engine on a high overload testing device, and adjusting an included angle theta between the connecting piece and the horizontal line of the test bed to finish the multi-angle mounting of the ground overload of the solid rocket engine.
Step four: and starting the high overload testing device, and igniting the solid rocket engine when the rotating platform reaches the set speed omega. The solid rocket engine now has the overload conditions required by the test.
Step five: and at 1s, 2s and 3s after the solid rocket engine starts to work, the pulse generator generates three pulse signals with different intensities to trigger the nonlinear unstable combustion of the solid rocket engine.
Step six: and recording an inner ballistic curve of the solid rocket engine during working process through a standard inner ballistic pressure sensor.
Step seven: and stopping the solid rocket engine, closing the high-overload testing device, and taking down the solid rocket engine.
Step eight: and changing the test variable, and repeating the third step to the seventh step to realize the test of the nonlinear unstable combustion of the solid rocket engine under different overload conditions.
The method also comprises the ninth step: through the test to above-mentioned operating mode, the complicated overload state of simulation solid rocket engine when actual high altitude construction, turn, the coupling effect between the influence factor that complicated overload state produced to nonlinear unstable combustion and overload and nonlinear unstable combustion is analyzed, and then solve relevant engineering problem.
Has the advantages that:
1. the invention discloses a test method for nonlinear unstable combustion of a solid rocket engine under overload conditions, which is characterized in that by improving a ground static unstable combustion test method and utilizing a ground high overload test device, the solid rocket engine works under different overload conditions, simultaneously nonlinear unstable combustion is caused by pulse triggering, and the inner ballistic performance is recorded by a sensor, so that the test of the inner ballistic performance of the solid rocket engine caused by the pulse triggering under the overload conditions is realized.
2. The invention discloses a method for testing nonlinear unstable combustion of a solid rocket engine under overload conditions, which enables the solid rocket engine fixed on a multi-angle measuring device to obtain different overload conditions by adjusting the rotating speed omega of a variable frequency motor and the included angle theta between the axis of a fixing piece and the horizontal line of a test bed, and realizes the test of the solid rocket engine under different overload conditions.
3. The invention discloses a combustion test method for the nonlinear instability of a solid rocket engine under an overload condition, which comprises the following steps of: overload size, overload angle, propellant type, combustion chamber pressure, stability additives, length and pulse strength of solid rocket engines, testing the influence of overload conditions on nonlinear unstable combustion, and coupling between overload conditions and other nonlinear unstable combustion influencing factors.
4. According to the method for testing the nonlinear unstable combustion of the solid rocket engine under the overload condition, disclosed by the invention, the solid rocket engine is arranged on a ground high overload testing device through improving a ground static unstable combustion testing method, the complex overload state in the flight process is simulated, the nonlinear unstable combustion measurement of the solid rocket engine which is more practical is realized, and further the related engineering problems are solved.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the invention and together with the description, serve to explain the principles of the invention.
FIG. 1 is a flow chart of a disclosed method for testing the combustion of a solid rocket engine for non-linear instability under overload conditions;
FIG. 2 is a diagram of a test apparatus for non-linear unstable combustion of a solid rocket engine under overload conditions in accordance with the present disclosure;
wherein: 2-1-a multi-angle mounting device, 2-2-a fixing piece, 2-3-a connecting rod, 2-4-a bearing shaft, 2-5-a rotating main shaft, 2-6-a commutator output shaft, 2-7-a commutator, 2-8-a variable frequency motor, 2-9-a connecting block and 2-10-a large cantilever;
FIG. 3 is a schematic illustration of an overload condition at the combustion face of the disclosed propellant;
FIG. 4 is a block diagram of a solid rocket engine disclosed herein;
wherein: 4-1-ignition torch, 4-2-solid rocket engine end socket, 4-3-shell, 4-4-propellant charge and 4-5-spray pipe;
FIG. 5 is an installation diagram of a specially designed head testing device disclosed by the present invention;
wherein: 5-1-ignition torch, 5-2, 5-3, 5-4-pulse generator, 5-5-standard inner ballistic trajectory pressure sensor, 5-6, 5-7-high frequency response pressure sensor, 5-8, 5-9, 5-10 pulse pressure sensor and 5-11-end enclosure;
fig. 6 is a schematic diagram of the inner ballistic curve under the pulse triggering condition in the overload and non-overload states disclosed in the present invention.
Detailed Description
For a better understanding of the objects and advantages of the present invention, reference should be made to the following detailed description taken in conjunction with the accompanying drawings and examples.
As shown in fig. 2, the method for testing nonlinear unstable combustion of a solid rocket engine under an overload condition disclosed in this embodiment adds an overload condition to a ground static unstable combustion test of the solid rocket engine, where the overload condition includes an overload angle θ and an overload acceleration a. The solid rocket engine is arranged on the ground high overload test device, and the overload angle theta and the rotating speed omega of the high overload test device are adjusted, so that the solid rocket engine has accelerated speeds in different directions and different magnitudes, and works under different overload conditions. After the solid rocket engine is ignited to work, the pulse trigger arranged at the end socket generates pulses to trigger the combustion instability phenomenon of the solid rocket engine, and meanwhile, the combustion state in the solid rocket engine is observed and recorded through the standard inner ballistic trajectory pressure sensor and the high-frequency response pressure sensor. The test variables comprise overload conditions, working pressure, propellant types, stability additives, length and pulse intensity of the solid rocket engine, and the nonlinear unstable combustion test of the solid rocket engine under the overload conditions is realized by changing the conditions of the test variables and analyzing the coupling effect between overload and other test variables. Through the test to above-mentioned operating mode, the complicated overload state of simulation solid rocket engine when actual high altitude construction, turn, the coupling effect between the influence factor that complicated overload state produced to nonlinear unstable combustion and overload and nonlinear unstable combustion is analyzed, and then solve relevant engineering problem.
The ground height overload testing device is composed of a multi-angle measuring device 2-1, a variable frequency motor 2-8, a commutator 2-7, a rotating main shaft 2-5, a bearing shaft 2-4 and a large cantilever 2-10. The rotating main shaft 2-5 is connected with an output shaft 2-6 of the commutator through a coupler, has axial rotation with the angular velocity omega, and is used for driving the large cantilever 2-10 to axially rotate. The two sides of the large cantilever 2-10 are provided with multi-angle measuring devices 2-1 which mainly comprise connecting blocks 2-9, connecting rods 2-3 and fixing pieces 2-2 and are used for realizing multi-angle installation of the solid rocket engine. The connecting rod 2-3 is respectively connected with the connecting block 2-9 and the fixing piece 2-2, and the length can be adjusted. The fixing piece 2-2 is used for fixedly mounting the solid rocket engine, one end of the fixing piece is fixed, and the other end of the fixing piece is connected with the connecting rod 2-3. When the length of the connecting rod 2-3 is changed, the fixing piece 2-2 can rotate along the fixed end. The solid rocket engine of the object to be tested is fixed on the fixing piece 2-2, and in the test, the length of the connecting rod 2-3 is changed, so that the included angles between the axis of the fixing piece 2-2 and the horizontal line of the test bed form different overload angles theta, and the multi-angle overload installation of the ground high overload testing device on the solid rocket engine is realized. The rotating speed omega of the variable frequency motor 2-8 is adjusted, and the variable frequency motor is transmitted to the solid rocket engine through the transmission main shaft 2-5 and the large cantilever 2-10, so that the solid rocket engine fixed on the multi-angle measuring device 2-1 obtains centrifugal acceleration a with different sizes, different overload accelerations are obtained, and the solid rocket engine is tested under different overload conditions. The overload condition includes an overload angle theta and an overload acceleration a.
As shown in fig. 3, different overload angles θ are obtained by adjusting an included angle θ between the axis of the fixing member 2-2 and the horizontal line of the test bed, and simultaneously, the rotating speed ω of the variable frequency motor 2-8 is adjusted, so that overload conditions of different sizes are finally obtained: solid rocket engineThe distance from the mass center of the engine to the axle center of the rotating shaft is L, and the centrifugal acceleration a borne by the solid rocket engine is that a is L omega2. The gravity acceleration borne by the solid rocket engine is small compared with the centrifugal acceleration, so that the gravity acceleration can be ignored. At a certain position of the burning surface of the propellant, the included angle between the acceleration a and the burning surface is theta, and the included angle between the acceleration a and the normal direction of the burning surface is 90-theta. Therefore, the normal acceleration a of the combustion surfacen＝acos(90°-θ)＝Lω2sin theta; tangential acceleration of combustion surface an＝acosθ＝Lω2cos θ. Therefore, different overload conditions are obtained by adjusting and adjusting the rotating speed omega of the variable frequency motor and the included angle theta between the axial direction of the connecting piece and the horizontal line, and the test of the nonlinear unstable combustion performance of the solid rocket engine under different overload conditions is realized.
The experimental solid rocket engine is shown in figure 4. In order to test the influence of the overload condition on the unstable combustion and the coupling effect between the overload condition and other test variables, different overload conditions, working pressures, stability additives, propellant types, lengths and pulse intensities of solid rocket engines were selected for testing. The overload condition can be changed by the above method. In order to test the influence of the pressure on the nonlinear unstable combustion in the overload state, the working pressure of the solid rocket engine is adjusted in the test process. The end cover of the solid rocket engine is preferably designed by threads, and a mode of installing front and rear lock catch rings is replaced, so that the solid rocket engine can bear the pressure of 70MPa at most, bear higher strength, and improve the reusability of the solid rocket engine. To test the effect of the stability additives on unstable combustion in the presence of an overload, 1% of the propellant was replaced by different stability additives, such as 8 mm alumina, 90 mm alumina and 3 mm zirconium carbide, and experimental comparisons were made. To test the effect of propellant type on combustion state in the presence of overload, solid rocket engines were tested by selecting different types of propellant, for example: star-shaped, cylindrical, the first two thirds star-shaped, the last one third cylindrical, etc. In order to test the influence of the length or oscillation frequency of the solid rocket engine on the combustion state when overload exists, solid rocket engines with different lengths are selected for testing. For example, a solid rocket motor having a length of 1.7m was selected for testing, where the solid rocket motor had a fundamental longitudinal frequency of about 330 Hz. The length of the solid rocket engine is changed, the solid rocket engine with the length of 0.85m is adopted for testing, at the moment, the solid rocket engine oscillates at about 660Hz in a first longitudinal mode, and the combustion conditions under different frequencies can be obtained by comparing test results.
As shown in fig. 5, the solid rocket motor is equipped with specially designed heads 5-11, which are equipped with a standard internal ballistic pressure sensor, two high frequency response pressure sensors and three pulse generators and ignition torches for recording internal ballistic changes and generating pulse signals. The concrete configuration is as follows: the ignition torch 5-1 is positioned in the center of the end socket; the devices 5-2, 5-3 and 5-4 are pulse generators which respectively generate three pulse signals with different intensities in 1s, 2s and 3s after the solid rocket engine works, and the purpose is to test the stability of the solid rocket engine to sound wave disturbance. The response of solid rocket engines to impulses is divided into two categories: 1) the solid rocket engine was stable after the pulse, and the acoustic oscillations produced by the pulse decayed with time, as shown by the dashed line in the inner ballistic graph 5; 2) the solid rocket engine was severely unstable after the pulse, as shown by the solid line in the inner ballistic graph 5. During the test, different test conditions are selected for the solid rocket engine, and pulse triggering is carried out after the solid rocket engine is ignited. If the triggering is unstable, testing each influence factor of the nonlinear unstable combustion of the solid rocket engine; device 5-5 is a standard internal ballistic pressure sensor; the devices 5-6 and 5-7 are high-frequency response pressure sensors respectively; the devices 5-8, 5-9 and 5-10 are pulse pressure sensors. Besides the device, the test is also specially provided with a pulse ignition control channel and multi-channel processing of high-frequency pressure sensor signals.
As shown in fig. 6, the left graph is the inner ballistic curve under no overload condition and the right graph is the inner ballistic curve under overload condition. The solid rocket engines all cause combustion instability under the triggering of the second pulse, and the change of the p-t curve is shown in the figure.
The test method for the nonlinear unstable combustion of the solid rocket engine under the overload condition comprises the following specific test steps:
the method comprises the following steps: before the test starts, the end socket device of the solid rocket engine is debugged, whether the connecting line is intact and whether the sensor is reasonably installed or not are tested, and whether the end socket device can normally work or not is tested.
Step two: and determining test variables according to test requirements, and selecting proper propellant types, combustion chamber pressure, solid rocket engine length and propellant formulas.
Step three: and determining the overload angle theta and the device rotating speed omega of the solid rocket engine according to the test overload requirement. And (3) mounting the solid rocket engine on a high overload testing device, and adjusting an included angle theta between the connecting piece and the horizontal line of the test bed to finish the multi-angle mounting of the ground overload of the solid rocket engine.
Step four: and starting the high overload testing device, and igniting the solid rocket engine when the rotating platform reaches a set speed. The solid rocket engine now has the high overload conditions required by the test.
Step five: and at 1s, 2s and 3s after the solid rocket engine starts to work, the pulse generator generates three pulse signals with different intensities to trigger the nonlinear unstable combustion of the solid rocket engine.
Step six: and recording an inner ballistic curve of the working process of the solid rocket engine through a standard inner ballistic pressure sensor, and analyzing the combustion state of the charge.
Step seven: and stopping the solid rocket engine, closing the high-overload testing device, and taking down the solid rocket engine.
Step eight: and changing the test variable, and repeating the third step to the seventh step to realize the test of the nonlinear unstable combustion of the solid rocket engine under different overload conditions.
The method also comprises the ninth step: the influence of the complex overload state of the solid rocket engine on nonlinear unstable combustion during aloft work and turning is simulated and analyzed through testing the working conditions, the influence of the complex overload state on the nonlinear unstable combustion and the coupling effect between the overload and nonlinear unstable combustion influence factors are analyzed, and then the related engineering problems are solved.
The above description is only an embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.
Claims (7)
1. The method for testing the nonlinear unstable combustion of the solid rocket engine under the overload condition is characterized in that the overload condition is added on the basis of a ground static unstable combustion test of the solid rocket engine, the overload condition comprises an overload angle theta and an overload acceleration α, the solid rocket engine is arranged on a high overload testing device, the overload angle theta and the rotating speed omega of the high overload testing device are adjusted, the solid rocket engine has different directions and magnitudes of acceleration, the solid rocket engine works under different overload conditions, after the solid rocket engine is ignited to work, pulse triggers (5-2), (5-3) and (5-4) arranged at a seal head (5-11) generate pulses to trigger the combustion instability of the solid rocket engine, meanwhile, the combustion state in the solid rocket engine is observed and recorded through a standard in-trajectory pressure sensor (5-5), a high-frequency response pressure sensor (5-6) and a high-frequency response pressure sensor (5-7), test variables comprise the overload condition, the working pressure, a propellant type, a stability additive, the length and the pulse strength of the solid rocket engine, the test variables comprise the overload condition, the linear unstable combustion influence of the overload condition and the nonlinear unstable combustion of the complicated overload condition, and the nonlinear unstable combustion of the solid rocket engine under the overload condition are analyzed by changing the conditions.
2. The method for testing the nonlinear unstable combustion of a solid rocket engine under overload conditions according to claim 1, wherein the method comprises the following steps: the method can simulate the complex overload state of the solid rocket engine during actual high-altitude operation and turning, analyze the influence of the complex overload state on nonlinear unstable combustion and the coupling effect between the overload and nonlinear unstable combustion influence factors, and further solve the related engineering problems.
3. A method of testing the nonlinear unstable combustion of a solid rocket engine under overload conditions as recited in claim 1 or 2 in which: the high overload testing device mainly comprises a multi-angle measuring device (2-1), a bearing shaft (2-4), a rotating main shaft (2-5), a large cantilever (2-10), a variable frequency motor (2-8) and a commutator (2-7); the rotating main shaft (2-5) is connected with an output shaft (2-6) of the commutator through a coupler, has axial rotation with the angular velocity omega, and is used for driving the large cantilever (2-10) to axially rotate; the two sides of the large cantilever (2-10) are provided with multi-angle measuring devices (2-1) which mainly comprise connecting blocks (2-9), connecting rods (2-3) and fixing pieces (2-2) and are used for realizing multi-angle installation of the solid rocket engine; the connecting rods (2-3) are respectively connected with the connecting blocks (2-9) and the fixing pieces (2-2), and the length can be adjusted; the fixing piece (2-2) is used for fixedly mounting the solid rocket engine, one end of the fixing piece is fixed, and the other end of the fixing piece is connected with the connecting rod; when the length of the connecting rod is changed, the fixing piece can rotate along the fixing end; the solid rocket engine of the object to be tested is fixed on the fixing piece (2-2), and in the test, the length of the connecting rod (2-3) is changed, so that the included angles between the axis of the fixing piece (2-2) and the horizontal line of the test bed form different overload angles theta, and the multi-angle overload installation of the high overload testing device on the solid rocket engine is realized; the rotating speed omega of the variable frequency motor (2-8) is adjusted and is transmitted to the solid rocket engine through the rotating main shaft (2-5) and the large cantilever (2-10), so that the solid rocket engine fixed on the multi-angle measuring device (2-1) obtains centrifugal acceleration a with different sizes, different overload accelerations are obtained, and the solid rocket engine is tested under different overload conditions; the overload condition includes an overload angle theta and an overload acceleration a.
4. A method of testing the nonlinear unstable combustion of a solid rocket engine under overload conditions as recited in claim 1 or 2 in which: different overload angles are obtained by adjusting the included angle theta between the axis of the fixing part (2-2) and the horizontal line of the test bedThe degree theta is measured, the rotating speed omega of the variable frequency motor (2-8) is adjusted simultaneously, and finally the overload conditions with different sizes are obtained, namely the distance from the center of mass of the solid rocket engine to the axis of the rotating shaft is L, and the centrifugal acceleration a borne by the solid rocket engine is that a is L omega2(ii) a At a certain position of a combustion surface of the propellant, an included angle between the acceleration a and the combustion surface is theta, and an included angle between the acceleration a and the normal direction of the combustion surface is 90-theta; therefore, the normal acceleration a of the combustion surfacen＝acos(90°-θ)＝Lω2sin theta; tangential acceleration of combustion surface an＝acosθ＝Lω2cos θ; therefore, different overload conditions are obtained by adjusting the rotating speed omega of the variable frequency motors (2-8) and the included angle theta between the axial direction of the connecting piece and the horizontal line, and the test of the nonlinear unstable combustion performance of the solid rocket engine under different overload conditions is realized.
5. A method of testing the nonlinear unstable combustion of a solid rocket engine under overload conditions as recited in claim 1 or 2 in which: the unstable combustion of the solid rocket engine is triggered by a pulse; the pulse trigger arranged at the end socket generates pulses, and the pulse frequency is selected to be three times.
6. A method of testing the nonlinear unstable combustion of a solid rocket engine under overload conditions as recited in claim 1 or 2 in which: in order to test the influence of the pressure on the nonlinear unstable combustion in the overload process, the working pressure of the solid rocket engine is adjusted in the test process; in order to test the influence of the stability additive on unstable combustion in the case of overload, part of the propellant is replaced by different stability additives, and test comparison is carried out; in order to test the influence of the propellant type on the combustion state when overload exists, the solid rocket engine selects different types of propellant for testing; in order to test the influence of the length or oscillation frequency of the solid rocket engine on the combustion state when overload exists, solid rocket engines with different lengths are selected for testing.
7. A method of testing the nonlinear unstable combustion of a solid rocket engine under overload conditions as recited in claim 1 or 2 in which: comprises the following steps of (a) carrying out,
the method comprises the following steps: before the test is started, debugging is carried out on the solid rocket engine end socket device, and whether the connecting line is intact and whether the sensor is reasonably installed or not can be tested to normally work or not;
step two: determining test variables according to test requirements, and selecting proper propellant types, combustion chamber pressure, solid rocket engine lengths and propellant formulas;
step three: determining the overload angle theta of the solid rocket engine and the rotation speed omega of the device according to the test overload requirement; mounting the solid rocket engine on a high overload testing device, and adjusting an included angle theta between a connecting piece and a horizontal line of a test bed to finish multi-angle mounting of ground overload of the solid rocket engine;
step four: starting the high overload testing device, and igniting the solid rocket engine when the rotating platform reaches a set speed omega; the solid rocket engine has overload conditions required by tests;
step five: the pulse generator generates three times of pulse signals with different intensities at 1s, 2s and 3s after the solid rocket engine starts to work, and the solid rocket engine is triggered to burn nonlinearly and unstably;
step six: recording an inner ballistic curve of the solid rocket engine in the working process through a standard inner ballistic pressure sensor;
step seven: stopping the solid rocket engine, closing the high overload testing device, and taking down the solid rocket engine;
step eight: and changing the test variable, and repeating the third step to the seventh step to realize the test of the nonlinear unstable combustion of the solid rocket engine under different overload conditions.
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| CN112594095A (en) * | 2020-12-07 | 2021-04-02 | 西安航天动力测控技术研究所 | Solid rocket engine real-time variable-angle centrifugal overload ignition test device |
| 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 |
| CN113776842A (en) * | 2021-09-02 | 2021-12-10 | 北京理工大学 | High-pressure combustor with pressure measurement and solid particle collection functions |
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