CN108548754B - Device and method for quickly extinguishing solid propellant under high pressure condition - Google Patents
Device and method for quickly extinguishing solid propellant under high pressure condition Download PDFInfo
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- G01N7/00—Analysing materials by measuring the pressure or volume of a gas or vapour
- G01N7/02—Analysing materials by measuring the pressure or volume of a gas or vapour by absorption, adsorption, or combustion of components and measurement of the change in pressure or volume of the remainder
- G01N7/06—Analysing materials by measuring the pressure or volume of a gas or vapour by absorption, adsorption, or combustion of components and measurement of the change in pressure or volume of the remainder by combustion alone
Abstract
The invention provides a method and a device for quickly extinguishing a solid propellant under a high-pressure condition, which comprise a high-pressure combustor, a positive binding post, a negative binding post, an auxiliary explosive package, a test sample, a rupture disc, a pressing screw, a sample support, a pressure sensor and an ignition power supply, wherein the high-pressure combustor is connected with the positive binding post; the ignition power supply is connected with the auxiliary medicine bag and the test sample through a positive wiring terminal and a negative wiring terminal on one side of the high-voltage combustor; the high-pressure combustor is provided with an exhaust hole, and the rupture disk is fixed on the exhaust hole by using an adjustable-caliber pressing screw; the side wall of the high-pressure combustor is provided with a pressure sensor for testing pressure intensity; a large-volume copper table is fixed in the high-pressure combustor and used as a sample support for fixing a test sample, and an auxiliary explosive package is fixed above the test sample. The pressure in the high-pressure combustor is increased to the target pressure by igniting the auxiliary explosive package, so that the propellant sample is ignited by the auxiliary explosive package under relatively stable initial pressure, and meanwhile, the propellant explosive strip is smoothly extinguished by utilizing the pressure screw adjusting exhaust hole and the copper platform sample support in the pressure relief process.
Description
Technical Field
The invention belongs to the field of rapid flameout of solid propellants, and particularly relates to a rapid flameout device and a rapid flameout method of a solid propellant under a high-pressure condition.
Background
The solid propellant rocket engine is widely applied to strategic and tactical weapon systems due to the inherent advantages, and in order to further improve the maneuverability and the defense-breaking capability of a missile weapon system, the solid propellant rocket engine not only needs to improve the controllability, but also needs to have the capability of starting for multiple times. The technical application of flameout engines needs to be researched to realize the adjustability of the thrust of the solid engine and the repeated starting, and the high-performance solid engine depends on the high-pressure working mode, namely the working pressure of a combustion chamber is increased, the specific impulse performance of the engine is improved, and the high-pressure working mode provides challenges for the reduction of the pressure index of the solid propellant, the improvement of the thermal stability and the high-pressure combustion performance. The decompression flameout process belongs to an unstable combustion process, and the combustion mechanism of the solid propellant, particularly the unstable combustion mechanism, can be understood more deeply through the research on the combustion in the decompression process.
The invention patent CN201010531622.9 discloses a solid propellant rapid flameout device, which mainly comprises a combustion chamber, a pressure sensor, a photoelectric sensor, an ignition power supply, a high-pressure switch electromagnetic valve, a high-pressure gas cylinder, a matched computer acquisition system and the like. The combustion chamber is stamped through the booster pump and the high-pressure gas cylinder, so that the combustion chamber maintains stable initial pressure, the ignition power supply is connected with the high-pressure switch electromagnetic valve, and the propellant is ignited while the electromagnetic valve is opened to rapidly extinguish. The pressure sensor and a matched system record and collect the pressure change curve of the combustion chamber in real time, and the photoelectric sensor judges whether the propellant is flameout successfully or not. However, this device has some problems: the initial pressure of the combustion chamber is improved through the booster pump, and the range is limited and cannot meet the high pressure (more than 30Mpa test) in the future; the whole device is heavy due to the gas cylinder booster pump, the gas is required to be recharged to build pressure before measurement every time, the operation is complex, and the test cost is increased.
The existing decompression flameout device is mainly used for quickly flameout the propellant of the gun, obtaining the burning surface information of the burning transient state of the propellant and is an important means for researching the burning mechanism of the propellant. The common propellant powder fast flameout device mainly comprises a burner, a pressure-bearing film, a pressure building explosive package, an exhaust regulator, a pressure sensor, an ignition power supply and the like. The working principle is as follows: a certain amount of propellant powder is taken as a pressure building powder bag to provide the pressure required by the experiment, when the pressure building powder bag is ignited, the pressure of the burner body exceeds the pressure limit of the pressure-bearing diaphragm, the diaphragm is broken, the pressure is quickly relieved through the exhaust regulator, and simultaneously the ignited test sample is extinguished due to sudden pressure drop. The device has the advantages of simple structure and convenient test operation. But through the experiment demonstration, with the device direct application of the quick flame-out of gun propellant to the quick flame-out field of solid propellant, when exhaust regulator was opened because of pressure, can't realize putting out flame with solid propellant.
Disclosure of Invention
Based on the defects of the prior art, the applicant carefully analyzes that the reason why the device for quickly extinguishing the gunpowder of the gun is directly applied to the field of quickly extinguishing the solid propellant cannot be realized is as follows: the solid propellant develops high energy, and a superfine oxidant, nano aluminum powder or other energy-containing substances are usually added to improve the burning rate and the specific impact energy of the propellant. Under the influence of these factors, the extinguishing of the solid propellant and the acquisition of an effective frozen combustion surface are a great problem. The quick flameout device based on the gun propellant adopts quick pressure relief simply, so that the propellant is unstable and reburns, and flameout of the solid propellant cannot be realized. The applicant adopts a mode of combining rapid depressurization and cooling to rapidly release pressure, so that the propellant is unstable in combustion, the heat transfer quantity of the combustion surface is reduced, and the thermal decomposition rate is reduced; the metal copper has good thermal conductivity, and the large-volume copper platform is adopted to inhibit and restrict the combustion of the propellant, so that the wall surface becomes a cold wall, the heat released by the combustion of the propellant is absorbed, and when the heat absorption strength is high enough, the further surface thermal decomposition and combustion of the propellant are influenced, thereby realizing flameout.
The invention provides a device and a method for rapidly extinguishing a solid propellant under a high-pressure condition.
The technical scheme of the invention is as follows: the utility model provides a solid propellant rapid flameout device under high pressure condition which characterized in that: the device comprises a high-pressure combustor, a positive wiring terminal, a negative wiring terminal, an auxiliary explosive package, a test sample, a rupture disk, a pressing screw, a copper platform sample support, a pressure sensor and an ignition power supply; the copper platform sample support is fixedly arranged in the high-pressure combustor, the test sample is embedded in the copper platform sample support, 1/8-1/7 of the volume of the test sample is enabled to be exposed out of the copper platform sample support, the auxiliary explosive package is arranged on the test sample, and the auxiliary explosive package and the test sample are the same solid propellant; the positive wiring terminal and the negative wiring terminal penetrate through and are fixed on the side wall of the high-pressure combustor, one end of the positive wiring terminal and one end of the negative wiring terminal are connected with a thermal power supply, and the other end of the positive wiring terminal and the other end of the negative wiring terminal are connected with an auxiliary medicine bag; the high-pressure combustor is provided with an exhaust hole, and the rupture disk is fixed on the exhaust hole by using the pressure screw; the side wall of the high-pressure combustor is provided with a small hole, and the pressure sensor is arranged on the small hole and used for testing the pressure intensity.
The further technical scheme of the invention is as follows: the pressure screw is a flange pressure point nut with different inner diameters and can be replaced, the pressure release rate of the exhaust hole can be adjusted according to needs, and the inner diameter can be adjusted to be 5-20 mm.
The further technical scheme of the invention is as follows: the rupture disk is made of a material with the thickness of 0.2mm and is a 304 stainless steel disk, and the rupture pressure is 7 MPa.
The further technical scheme of the invention is as follows: the high-pressure combustor is made of stainless steel, the internal volume is 150 +/-10 ml, the pressure bearing is 120Mpa calculated theoretically, and the constant volume burning rate test result shows that the high-pressure combustor is airtight within 100Mpa pressure bearing.
A method for carrying out quick flameout by using a solid propellant quick flameout device under a high-pressure condition is characterized in that:
the method comprises the following steps: according to the pressure required by the experiment and the data of the high-pressure combustor test, calculating the mass of the auxiliary explosive package for determining the required pressure, wherein the calculation process is as follows:
a. calculating W according to equation (1)t：
ptVt＝(WF+Wpt)RTrv/Mg(1)
Wherein T isrvThe actual temperature of the fuel gas in the high-pressure combustor; r is a universal gas constant; wFIs the quality of the auxiliary medicine; mgIs the relative molecular mass of the solid propellant gas; wptMass of test sample consumed for combustion at time t; vtIs the free volume of the burner at time t; wtIs WFAnd WptThe sum of (1);
b. solving the corresponding pressure p during blasting at the moment t according to the following processt：
Igniting the auxiliary explosive package in the closed high-pressure combustor to enable the rupture disk to explode, and recording a pressure-time curve through a pressure sensor; simultaneously recording the corresponding pressure p during blasting at the t moment on a pressure-time curvet；
The free volume V of the burner at time t is calculated according to the following proceduret：
The method comprises the following steps of (1) calibrating the free volume of a high-pressure combustor by adopting absolute ethyl alcohol: (1) firstly, assembling a combustor without installing a pressure sensor; (2) filling absolute ethyl alcohol through a pressure measuring hole by using a clean needle tube, wherein the liquid level reaches the installation position of a pressure measuring hole sensor; (3) calculating the initial free volume V of the high-pressure combustor according to the mass and density of the absolute ethyl alcohol0；
Free volume in the high-pressure combustor at time t: vt＝V0-Wp0/ρp+Wt/ρpWhere ρ ispIs the density of the propellant, Wp0The initial total weight of the solid propellant;
the relative molecular mass M of the solid propellant gas was calculated according to the following procedureg：
Inputting the pressure P of an initial combustion chamber, the initial temperature T, the molecular formula, the state, the percentage content and the generated heat of each component of the propellant formula into CEA thermal calculation software, and calculating the relative molecular mass Mg of the solid propellant gas through CEA;
calculating the actual temperature T of the gas according to the following processrv：
Igniting a known mass W in a closed high pressure combustorF1The maximum pressure p at the end of combustion is measured, and p and V are known0、WF1R and MgSubstituting into formula pV0＝WF1RTrv/MgTo find the actual temperature T of the gasrv；
c. According to the calculated WtTaking Wt85% -95% of the total amount of the active ingredient is taken as the mass W of the auxiliary medicineF；
Step two: fixing a test sample on the copper platform sample support, fixing an auxiliary medicine package above the test sample, and simultaneously connecting the auxiliary medicine package with the positive binding post and the negative binding post;
step three: according to experimental pressure ptSelecting a corresponding pressing screw and a corresponding rupture disk, and completing installation;
step four: installing a pressure sensor on a side wall small hole of the high-pressure combustor to ensure that a contact surface is sealed;
step five: setting the acquisition frequency of a computer acquisition system, completing the line connection between a computer and a high-pressure combustion chamber, and ensuring normal signal output;
step six: setting ignition voltage, and measuring the resistance of an ignition loop by using a universal meter to ensure normal ignition; starting an ignition power supply, heating an ignition wire to ignite the auxiliary explosive package, increasing the pressure in the closed high-pressure combustor, and successfully igniting the test sample when the pressure rises to an upper limit value; the rupture disk is quickly decompressed after being completely broken under pressure, and absorbs heat released by propellant combustion through the copper platform sample support, so that flameout of the solid propellant is realized.
Technical effects
The auxiliary medicine package can be used for easily providing any required initial pressure for the burner, the combustion process of the solid propellant conforms to the parallel layer combustion rule, the initial pressure provided by the same propellant pressure building medicine package with the same size and quality is tested for many times according to the existing high-pressure burner, the reproducibility is good, the pressure fluctuation range is five thousandth, and the propellant medicine strip can be ensured to be ignited under relatively stable pressure. Meanwhile, the reliable flameout of the solid propellant is realized by combining two modes of quick pressure relief and large-volume copper platform cooling by installing the rupture disk on the exhaust hole in the flameout process. The whole device is convenient to operate, simple in structure, convenient to detach and clean and capable of conducting multiple tests.
Drawings
Fig. 1 is a schematic view of a solid propellant rapid extinguishing device under high pressure condition according to the present invention.
FIG. 2 is a P-t curve of successful flameout of a composite solid propellant at different pressures.
FIG. 3 is a P-t curve of a composite propellant adjuvant of the same mass.
Description of reference numerals: 1. pressing the snail; 2. a rupture disk; 3. a high pressure combustor; 4. positive and negative binding posts; 5. an auxiliary drug package; 6. testing the sample; 7. a copper table sample support; 8. a pressure sensor.
Detailed Description
Referring to fig. 1, the fast extinguishing device for the solid propellant under the high-pressure condition comprises a high-pressure combustor 3, a positive binding post 4, a negative binding post 4, an auxiliary explosive package 5, a test sample 6, a rupture disk 2, a pressing screw 1, a copper platform sample support 7, a pressure sensor 8 and an ignition power supply.
The copper platform sample support 7 is fixedly arranged in the high-pressure combustor 3, the test sample 6 is arranged on the copper platform sample support 7, and the auxiliary explosive package 5 is arranged on the test sample 6; the positive wiring terminal 4 and the negative wiring terminal 4 penetrate through and are fixed on the side wall of the high-pressure combustor 3, one end of each wiring terminal is connected with a thermal power supply, and the other end of each wiring terminal is connected with an auxiliary medicine package 5; the high-pressure combustor 3 is provided with an exhaust hole, and the rupture disk 2 is fixed on the exhaust hole by using the pressure screw 1; the side wall of the high-pressure combustor 3 is provided with a small hole, and the pressure sensor 8 is arranged on the small hole and used for testing the pressure.
The high-pressure combustor 3 is made of stainless steel, the internal volume is 150 +/-10 ml, the pressure bearing is 120Mpa calculated theoretically, and the result of a constant volume burning rate test shows that the high-pressure combustor is airtight within 100Mpa pressure bearing.
The pressure sensor 8 is a model KIST L ER-6215, the measuring range is between 0 and 600MPa, the auxiliary explosive package 5 is made of powder or small explosive columns of a test sample 6, the pressure building range is determined by the quality of propellant powder, the general rule is that 3g of the auxiliary explosive package 5 can enable the pressure in the high-pressure combustor 3 to reach 6MPa, 5g of the auxiliary explosive package 5 corresponds to 10MPa, the corresponding relation is not linear, and multiple tests are needed, the rupture disk 2 is an aluminum or stainless steel round thin disk, the thickness of the rupture disk can be estimated according to a formula in national standard GB567-1999, for example, a 304 stainless steel round disk with the thickness of 0.2mm is provided, the rupture pressure is about 7MPa, the inner diameter of the adjustable caliber pressing screw 1 is adjustable between 5 and 20mm and is used for fixing and tightening the rupture disk 2, a computer control system is connected with a thermal power supply, an acquisition system is connected with the pressure sensor 8, and.
The invention relates to a method for using a solid propellant quick flameout device under a high-pressure condition, which comprises the following steps:
the method comprises the following steps: according to the pressure required by the experiment and the data of the high-pressure combustor test, calculating the mass of the auxiliary explosive package for determining the required pressure, wherein the calculation process is as follows:
calculating W according to equation (1)t：
ptVt＝(WF+Wpt)RTrv/Mg(1)
Wherein T isrvThe actual temperature of the fuel gas in the high-pressure combustor; r is a universal gas constant; wFIs the quality of the auxiliary medicine; mgIs the relative molecular mass of the solid propellant gas; wptMass of test sample consumed for combustion at time t; vtIs the free volume of the burner at time t; wtIs WFAnd WptThe sum of (1);
b. solving the corresponding pressure p during blasting at the moment t according to the following processt：
Igniting the auxiliary explosive package in the closed high-pressure combustor to enable the rupture disk to explode, and recording a pressure-time curve through a pressure sensor; simultaneously recording the corresponding pressure p during blasting at the t moment on a pressure-time curvet；
The free volume V of the burner at time t is calculated according to the following proceduret：
The method comprises the following steps of (1) calibrating the free volume of a high-pressure combustor by adopting absolute ethyl alcohol: (1) firstly, assembling a combustor without installing a pressure sensor; (2) filling absolute ethyl alcohol through a pressure measuring hole by using a clean needle tube, wherein the liquid level reaches the installation position of a pressure measuring hole sensor; (3) calculating the initial free volume V of the high-pressure combustor according to the mass and density of the absolute ethyl alcohol0；
Free volume in the high-pressure combustor at time t: vt＝V0-Wp0/ρp+Wt/ρpWhere ρ ispIs the density of the propellant, Wp0The initial total weight of the solid propellant;
the relative molecular mass M of the solid propellant gas was calculated according to the following procedureg：
Inputting the pressure P of an initial combustion chamber, the initial temperature T, the molecular formula, the state, the percentage content and the generated heat of each component of the propellant formula into CEA thermal calculation software, and calculating the relative molecular mass Mg of the solid propellant gas through CEA;
calculating the actual temperature T of the gas according to the following processrv：
Igniting a known mass W in a closed high pressure combustorF1The maximum pressure p at the end of combustion is measured, and p and V are known0、WF1R and MgSubstituting into formula pV0＝WF1RTrv/MgTo find the actual temperature T of the gasrv；
c. According to the calculated WtTaking Wt85% -95% of the total amount of the active ingredient is taken as the mass W of the auxiliary medicineF；
Step two: fixing a test sample on the copper platform sample support, fixing an auxiliary medicine package above the test sample, and simultaneously connecting the auxiliary medicine package with the positive binding post and the negative binding post;
step three: according to experimental pressure ptSelecting a corresponding pressing screw and a corresponding rupture disk, and completing installation;
step four: installing a pressure sensor on a side wall small hole of the high-pressure combustor to ensure that a contact surface is sealed;
step five: setting the acquisition frequency of a computer acquisition system, completing the line connection between a computer and a high-pressure combustion chamber, and ensuring normal signal output;
step six: setting ignition voltage, and measuring the resistance of an ignition loop by using a universal meter to ensure normal ignition; starting an ignition power supply, heating an ignition wire to ignite the auxiliary explosive package, increasing the pressure in the closed high-pressure combustor, and successfully igniting the test sample when the pressure rises to an upper limit value; the rupture disk is quickly decompressed after being completely broken under pressure, and absorbs heat released by combustion of the propellant through the copper platform, so that flameout of the solid propellant is realized; the data acquisition system records a pressure-time curve of the experimental process, and the reference is made to fig. 2;
step seven: taking out the unburned propellant strips after the experiment is finished, and cleaning a combustion chamber; repeating the steps, preparing for the next group of experiments, processing the data at the later stage, and obtaining the pressure reduction rate of the flameout experiment from the slope of the descending section of the pressure-time curve; the observation and determination of the extinguishing surface of the propellant was done by Scanning Electron Microscopy (SEM) and X-ray photoelectron spectroscopy (XPS).
Claims (4)
1. A method for carrying out quick flameout by using a solid propellant quick flameout device under a high-pressure condition is characterized in that: the quick flameout device comprises a high-pressure combustor, a positive wiring terminal, a negative wiring terminal, an auxiliary explosive package, a test sample, a rupture disc, a pressing screw, a copper platform sample bracket, a pressure sensor and an ignition power supply; the copper platform sample support is fixedly arranged in the high-pressure combustor, the test sample is embedded in the copper platform sample support, 1/8-1/7 of the volume of the test sample is enabled to be exposed out of the copper platform sample support, the auxiliary explosive package is arranged on the test sample, and the auxiliary explosive package and the test sample are the same solid propellant; the positive wiring terminal and the negative wiring terminal penetrate through and are fixed on the side wall of the high-pressure combustor, one end of the positive wiring terminal and one end of the negative wiring terminal are connected with a thermal power supply, and the other end of the positive wiring terminal and the other end of the negative wiring terminal are connected with an auxiliary medicine bag; the high-pressure combustor is provided with an exhaust hole, and the rupture disk is fixed on the exhaust hole by using the pressure screw; the side wall of the high-pressure combustor is provided with a small hole, and the pressure sensor is arranged on the small hole and used for testing the pressure intensity;
the method for rapidly extinguishing the flame comprises the following specific steps:
the method comprises the following steps: according to the pressure required by the experiment and the data of the high-pressure combustor test, calculating the mass of the auxiliary explosive package for determining the required pressure, wherein the calculation process is as follows:
a. calculating W according to equation (1)t：
ptVt＝(WF+Wpt)RTrv/Mg(1)
Wherein T isrvThe actual temperature of the fuel gas in the high-pressure combustor; r is a universal gas constant; wFIs the quality of the auxiliary medicine; mgIs the relative molecular mass of the solid propellant gas; wptMass of test sample consumed for combustion at time t; vtIs the free volume of the burner at time t; wtIs WFAnd WptThe sum of (1);
b. solving the corresponding pressure p during blasting at the moment t according to the following processt：
Igniting the auxiliary explosive package in the closed high-pressure combustor to enable the rupture disk to explode, and recording a pressure-time curve through a pressure sensor; simultaneously recording the corresponding pressure p during blasting at the t moment on a pressure-time curvet；
The free volume V of the burner at time t is calculated according to the following proceduret：
The method comprises the following steps of (1) calibrating the free volume of a high-pressure combustor by adopting absolute ethyl alcohol: (1) firstly, assembling a combustor without installing a pressure sensor; (2) filling absolute ethyl alcohol through pressure measuring hole by using clean needle tube, and filling absolute ethyl alcohol from liquid level to pressure measuring hole sensorInstalling a position; (3) calculating the initial free volume V of the high-pressure combustor according to the mass and density of the absolute ethyl alcohol0；
Free volume in the high-pressure combustor at time t: vt＝V0-Wp0/ρp+Wt/ρpWhere ρ ispIs the density of the propellant, Wp0The initial total weight of the solid propellant;
the relative molecular mass M of the solid propellant gas was calculated according to the following procedureg：
Inputting the pressure P of an initial combustion chamber, the initial temperature T, the molecular formula, the state, the percentage content and the generated heat of each component of the propellant formula into CEA thermal calculation software, and calculating the relative molecular mass Mg of the solid propellant gas through CEA;
calculating the actual temperature T of the gas according to the following processrv：
Igniting a known mass W in a closed high pressure combustorF1The maximum pressure p at the end of combustion is measured, and p and V are known0、WF1R and MgSubstituting into formula pV0＝WF1RTrv/MgTo find the actual temperature T of the gasrv；
c. According to the calculated WtTaking Wt85% -95% of the total amount of the active ingredient is taken as the mass W of the auxiliary medicineF；
Step two: fixing a test sample on the copper platform sample support, fixing an auxiliary medicine package above the test sample, and simultaneously connecting the auxiliary medicine package with the positive binding post and the negative binding post;
step three: according to experimental pressure ptSelecting a corresponding pressing screw and a corresponding rupture disk, and completing installation;
step four: installing a pressure sensor on a side wall small hole of the high-pressure combustor to ensure that a contact surface is sealed;
step five: setting the acquisition frequency of a computer acquisition system, completing the line connection between a computer and a high-pressure combustion chamber, and ensuring normal signal output;
step six: setting ignition voltage, and measuring the resistance of an ignition loop by using a universal meter to ensure normal ignition; starting an ignition power supply, heating an ignition wire to ignite the auxiliary explosive package, increasing the pressure in the closed high-pressure combustor, and successfully igniting the test sample when the pressure rises to an upper limit value; the rupture disk is quickly decompressed after being completely broken under pressure, and absorbs heat released by propellant combustion through the copper platform sample support, so that flameout of the solid propellant is realized.
2. The method for rapid fire extinction using a solid propellant rapid fire extinction device under high pressure conditions as claimed in claim 1, wherein: the pressure screw is a flange pressure point nut with different inner diameters and can be replaced, the pressure release rate of the exhaust hole can be adjusted according to needs, and the inner diameter can be adjusted to be 5-20 mm.
3. The method for rapid fire extinction using a solid propellant rapid fire extinction device under high pressure conditions as claimed in claim 1, wherein: the rupture disk is made of a material with the thickness of 0.2mm and is a 304 stainless steel disk, and the rupture pressure is 7 MPa.
4. The method for rapid fire extinction using a solid propellant rapid fire extinction device under high pressure conditions as claimed in claim 1, wherein: the high-pressure combustor is made of stainless steel, the internal volume is 150 +/-10 ml, the pressure bearing is 120Mpa calculated theoretically, and the constant volume burning rate test result shows that the high-pressure combustor is airtight within 100Mpa pressure bearing.
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| CN109596770B (en) * | 2018-11-27 | 2021-07-23 | 西安近代化学研究所 | Propellant powder explosion fragment pressure relief combustion stopping device |
| CN110596301B (en) * | 2019-10-14 | 2022-12-13 | 西安近代化学研究所 | Test engine and test method for combustion of double-base propellant in different overload directions |
| CN112147268B (en) * | 2020-09-03 | 2022-08-19 | 西安近代化学研究所 | Device and method for nondestructively preparing flameout surface of solid propellant |
| CN112324594B (en) * | 2020-11-06 | 2023-08-18 | 湖北航天技术研究院总体设计所 | Solid rocket engine simulated combustion test equipment |
| CN112324592B (en) * | 2020-11-06 | 2023-08-18 | 湖北航天技术研究院总体设计所 | Solid rocket engine simulated combustion test equipment shell structure |
| CN112324593B (en) * | 2020-11-06 | 2023-08-18 | 湖北航天技术研究院总体设计所 | Heat insulation structure of solid rocket engine simulated combustion test equipment |
| CN112881229B (en) * | 2021-01-06 | 2022-12-06 | 西北工业大学 | Solid propellant high-pressure extinguishing combustion surface acquisition device and acquisition method |
| CN114184642B (en) * | 2022-02-16 | 2022-07-26 | 南京理工大学 | Solid propellant high-pressure ignition and combustion suspension test device |
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| CN101979999B (en) * | 2010-11-04 | 2011-12-28 | 西安近代化学研究所 | Solid propellant depressurizing and extinguishing device |
| CN103697935B (en) * | 2013-10-18 | 2016-01-13 | 南京理工大学 | End row's propellant transient state pressure release burning buckling behaviors proving installation |
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