CN101979999A - Solid propellant depressurizing and extinguishing device - Google Patents
Solid propellant depressurizing and extinguishing device Download PDFInfo
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- CN101979999A CN101979999A CN 201010531622 CN201010531622A CN101979999A CN 101979999 A CN101979999 A CN 101979999A CN 201010531622 CN201010531622 CN 201010531622 CN 201010531622 A CN201010531622 A CN 201010531622A CN 101979999 A CN101979999 A CN 101979999A
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- burner
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Abstract
The invention discloses a solid propellant depressurizing and extinguishing device. The device comprises a burner; one side of the burner is provided with a pressure sensor which is connected with a computer and a control system of the computer; a burner base is arranged in the burner; an electric heating wire is arranged on the burner base and connected with an ignition power supply outside the burner; the ignition power supply is connected with the computer control system; a sample bracket for arranging a test sample is arranged in the burner base; the top of the burner is also connected with a high-pressure switch electromagnetic valve and an air displacement regulator, wherein the high-pressure switch electromagnetic valve is connected with the computer control system; a filter screen is arranged between the burner and the high-pressure switch electromagnetic valve; the other side of the burner is also provided with a photoelectric sensor connected with the computer control system; and a gas inlet is also formed on the burner and connected with a booster pump and a high-pressure gas cylinder in turn through a pipeline, wherein the booster pump is also connected with the computer control system. The solid propellant depressurizing and extinguishing device can identify whether the sample is extinguished or not and when the sample is extinguished during experiment.
Description
Technical field
The invention belongs to the solid propellant experimental apparatus for capability, be specifically related to a kind of solid propellant step-down blanket.
Background technology
For improving maneuverability, penetration ability and the accuracy at target of guided missile, need have thrust ability controlled and that repeatedly start as the rocket engine of propulsion system.Realize that rocket engine thrust is controlled and repeatedly start the flame-out engine technology of needs research, the key of flame-out engine technology is the research of solid propellant burn-out condition, and flame-out minimum rate of pressure reduction is the critical performance parameters of burn-out condition research under the certain pressure intensity.
Existing step-down blanket is mainly used in the flame-out fast of propellant powder, its objective is to obtain the gun propellant combustion combustion surface information of moment, and be one of important means of gun propellant combustion mechanism research.Its experimental provision is referring to shown in Figure 1, mainly by forming with the lower part: 1, burner; 2, screen pack; 3, pressure containing disk; 4, air capacity regulator; 5, build the pressing bag; 6, priming supply; 7, computing machine and control system thereof; 8, burner base; 9, sample holder; 10, specimen; 11, heating wire; 12, pressure transducer.
Its principle of work is: build pressing bag 5 and lighted by priming supply 6, make pressure in the burner body 1 surpass the pressure-bearing limit of pressure containing disk 3, pressure containing disk 3 breaks, and the pressure of burner 1 is from air capacity regulator 4 quick pressure releasing, and the specimen 10 of burning is extinguished because of the pressure bust.
When utilizing this device to experimentize, according to the pressure of experiment defined, what be installed with heating wire 11 in the middle of the propellant powder that need take by weighing respective quality is made builds pressing bag 5, selects and install the pressure containing disk 3 of respective thickness simultaneously; The mass M of weighing testing sample 10
0, be installed on the sample holder 9, build pressing bag 5 and place testing sample upper end, with sample holder 9 burner 1 of packing into; Start computing machine and control system 7 thereof, confirm that pressure transducer 12 is working properly after, starting ignition power supply 6, heating wire 11 light after electric and build pressing bag 5; The pressure change that pressure transducer 12 detects in the whole process, experiment finishes.Unload sample holder 9, the mass M of weighing specimen once more 10
1, if M
1Less than M
0, think that specimen burning back is extinguished.
But there are some problems in existing propellant powder step-down blanket:
1, the original pressure fluctuation is big.The pressure containing disk 3 that existing apparatus is selected is aluminium flake or copper sheet, and pressure containing disk 3 process can not guarantee the homogeneity and the consistance of its thickness; Simultaneously, pressure containing disk 3 suffered extruding force and the shearing forces that manually are in place also can't guarantee consistance.That is to say that the uncertainty of pressure containing disk 3 intensity can cause burner 1 interior original pressure to be difficult to regulation and control in tolerance band, the original pressure fluctuation ratio of each experiment is bigger.
2, existing apparatus can not ensure that the specimen 10 of building in the pressure process of burner 1 is not lighted, can not ensure burner 1 build press finish after specimen 10 can be lighted, the pressure when specimen 10 takes fire is uncertain.
3, existing apparatus can only be after experiment finishes, take out sample holder 9, come judgement sample whether burn-out has taken place by forward and backward of poor quality of weighing and calculation sample experiment, and can not be in experimentation, the variation of identification specimen 10 combustion cases when burner 1 internal pressure descends.
4, existing apparatus can obtain flame-out sample, but can not record the burn-out condition parameter.
Summary of the invention
Defective or deficiency at above-mentioned existing apparatus existence, the objective of the invention is to, a kind of new solid propellant step-down blanket is provided, and this device can make sample be lighted under stable original pressure, and in real time in the detected pressures decline process sample whether extinguish.
In order to realize above-mentioned task, the present invention takes following technical solution:
A kind of solid propellant step-down blanket comprises burner, and burner one side is equipped with pressure transducer, and pressure transducer is connected with computing machine and control system thereof; Burner base is arranged in the burner, have heating wire, heating wire to pass burner base on the burner base and be connected with the priming supply of combustor external, priming supply is connected with computer control system; Be useful on installation testing sample sample holder in the burner base; It is characterized in that also be connected with high-voltage switch gear solenoid valve and air capacity regulator at the top of burner, wherein the high-voltage switch gear solenoid valve is connected with computer control system, between burner and the high-voltage switch gear solenoid valve screen pack is arranged; At the burner opposite side, also be provided with the photoelectric sensor that is connected with computer control; Burner also has air intake opening, is connected with supercharge pump and gas cylinder in turn by pipeline on air intake opening, and wherein, supercharge pump also is connected with computer control system.
The present invention has cancelled on existing step-down blanket and has built the pressing bag, having increased gas cylinder is source of the gas, make the burner internal pressure be increased to setting value by supercharge pump, and then utilize direct supply starting ignition power supply, the heating heating wire, testing sample in the ignition combustion device, the combustion gas that the testing sample burning produces raises the burner internal pressure, pressure transducer detects the burner internal pressure and rises to threshold value, send to computer control system, make high-pressure solenoid valve open, by the exhaust of air capacity regulator.The pressure transducer and the photoelectric sensor that are installed in combustor sidewalls write down pressure and the intensity variations in the burner in the experimentation by computer control system.Calculate the pressure decline rate by the computer control system saved software, the process that whether sample extinguishes, when extinguishes in the identification experimentation.
Compare with existing step-down blanket, utilize supercharge pump can be provides any needs in the burner original pressure, the original pressure fluctuation range of each experiment is 0.5%, solved the big problem of existing apparatus original pressure fluctuation, and can guarantee testing sample under the original pressure that needs arbitrarily by reliable ignition.Simultaneously, since pressure transducer and photoelectric sensor can the dynamic test experimentation in the variation of sample combustion situation, therefore, can test the minimum rate of pressure reduction that the different formulations propellant stops working under certain pressure intensity, also can record the flame-out critical pressure of the solid propellant under the certain condition, expand the function of existing apparatus.On national defence, can be used for the test of energy management type tactical missile and rocket projectile with solid propellant step-down extinguishment characteristics.
Description of drawings
Fig. 1 is existing propellant powder step-down blanket structural drawing;
Fig. 2 is an experimental provision structural drawing of the present invention;
Fig. 3 adopts device of the present invention to carry out the result of experiment curve one time.
Label among the figure is represented respectively: 1, burner, 2, screen pack, 3, pressure containing disk, 4, the extraction flow regulator, 5, build the pressing bag, 6, priming supply, 7, computer control system; 8, burner base; 9, sample holder; 10, specimen; 11, heating wire; 12, pressure transducer, 13, air intake opening, 14, supercharge pump, 15, gas cylinder, 16, the high-voltage switch gear solenoid valve, 17, photoelectric sensor.
The present invention is described in more detail below in conjunction with drawings and Examples.
Embodiment
Referring to Fig. 2, solid propellant step-down blanket of the present invention comprises burner 1, and burner 1 one sides are equipped with pressure transducer 12, and pressure transducer 12 is connected with computer control system 7; Burner base 8 is arranged in the burner 1, heating wire 11 is arranged on the burner base 8, heating wire 11 passes burner base 8 and is connected with the priming supply 6 of burner 1 outside, and priming supply 6 is connected with computer control system 7; Be useful on installation testing sample 10 sample holders 9 in the burner base 8;
Also be connected with high-voltage switch gear solenoid valve 16 and air capacity regulator 4 at the top of burner 1, wherein high-voltage switch gear solenoid valve 16 is connected with computer control system 7, between burner 1 and the high-voltage switch gear solenoid valve 16 screen pack 2 is arranged; At burner 1 opposite side, also be provided with the photoelectric sensor 17 that is connected with computer control system 7;
On burner 1 sidewall, have the aperture of test pressure and test light intensity, respectively setting pressure sensor 12 and photoelectric sensor 17.It is CYG41000 that pressure transducer 12 adopts model, and range is the pressure unit of 0～30MPa; Photoelectric sensor 17 adopts the photomultiplier of infrared band, the output of 0～10V direct current.Burner 1 bottom has air intake opening 13, and air intake opening 13 usefulness stainless steel pipes are connected with gas cylinder 15 with supercharge pump 14, and supercharge pump 14 is selected HN100 high pressure nitrogen supercharger for use, and gas cylinder 15 is selected high-pressure nitrogen bottle for use, storage pressure: 13.5 ± 0.5MPa, purity: N
2〉=99.5%.Burner 1 top is a gas vent, and the exit is equipped with screen pack 2, prolongs airflow direction and connects high-pressure solenoid valve 16 and air capacity regulator 4.Screen pack 2 is stainless steel, and mesh diameter is not more than 200 μ m; High-pressure solenoid valve 16 adopts the German Pumason GYB091459X of company type switching regulator solenoid valve, and air capacity regulator 4 is the ring plate of one group of stainless steel, and the annular distance diameter can be selected between 0.5 ~ 10mm.Sample holder 9 places in the burner base 8, and heating wire 11 is connected with the priming supply 6 of combustor external.Computer control system 7 has connected supercharge pump 14, priming supply 6, pressure transducer 12, photoelectric sensor 17 and high-pressure solenoid valve 16, be used to control the unlatching of supercharge pump 14, the excitation of priming supply 6 and the open and close of high-pressure solenoid valve 16, gather the pressure of pressure transducer 12 and photoelectric sensor and the light intensity data line data of going forward side by side simultaneously and handle.
In order to guarantee measuring accuracy of the present invention, pressure transducer 12 needs annual the demarcation once, and photoelectric sensor 17 is carrying out needing cleaning once after five experiments.
The using method of solid propellant step-down blanket of the present invention is as follows:
1, testing sample 10 is fixed on the sample holder 9, connects heating wire 11 in testing sample 10 upper ends, sample holder 9 is loaded on the burner base 8.
2, the photosensitive head of clear light electric transducer 17 is installed in the sidewall of burner 1, guarantees sealing.
3, choose the ring plate of air capacity regulator 4 and installing.
4, computer control system 7 is provided with original pressure P
0, pressure rising threshold value (is generally P
0+ 0.5MPa) and acquisition speed (be generally 50kH
Z).
5, open gas cylinder 15, computer control system 7 starts supercharge pump 14 for providing original pressure in the burner 1, and pressure transducer 12 detects original pressure and reaches setting value P
0, computer control system 7 instruction supercharge pumps 14 stop automatically.
6, computer control system 7 instructions, light specimen 10 after heating wire 11 heatings, burner 1 internal pressure rises to threshold value, computer control system 7 instruction high-pressure solenoid valve 16 are opened exhaust automatically, and data acquisition system (DAS) is noted the pressure-time curve and the light intensity-time curve of whole process.Data acquisition finishes back high-pressure solenoid valve 16 and closes automatically.
7, calculate the rate of pressure reduction of this experiment:
8, contrast pressure-time curve and light intensity-time curve obtains whether specimen 10 is extinguished, the information such as pressure when extinguishing.
9, unload sample holder 9, clean out.
10, according to this experimental result, suitably choose the ring plate of air capacity regulator 4, prepare experiment next time.
For example certain modified double base propellant sample 10 is fixed on the sample holder 9, connects heating wire 11, place on the burner base 8.The ring plate aperture of choosing air capacity regulator 4 is 5mm and installs.Original pressure P is set
0For 24MPa, pressure rising threshold value are that 24.5MPa, sampling rate are 50kHz.Start supercharge pump 14 and be pressurized to 24Mpa in the burner 1, supercharge pump 14 stops.Priming supply 6 is connected heating wire 11 and is lighted double base propellant sample 10, and burner 1 internal pressure rises to 24.5MPa, and computer control system 7 instruction high-pressure solenoid valve 16 are opened exhaust.Computer control system 7 is finished data acquisition.Fig. 3 is the pressure-time curve and the light intensity-time curve of this experimentation.Pressure-time curve is calculated the rate of pressure reduction of this experiment
=1873MPa/s; Contrast pressure-time curve and light intensity-time curve obtain: double base propellant sample 10 is lighted at 24.06MPa, and the double base propellant sample does not extinguish in the pressure decline process.According to this experimental result, make double base propellant sample 10 burn-outs, need rate of pressure reduction faster, therefore choose more wide-aperture air capacity regulator 4, other condition is constant, recording this double base propellant sample 10 flame-out minimum rate of pressure reduction under 24MPa after repeatedly testing is 2640MPa/s, and flame-out critical pressure is 1.5MPa.
Claims (6)
1. a solid propellant step-down blanket comprises burner (1), and burner (1) one side is equipped with pressure transducer (12), and pressure transducer (12) is connected with computer control system (7); Burner base (8) is arranged in the burner (1), heating wire (11) is arranged on the burner base (8), heating wire (11) passes burner base (8) and is connected with the priming supply (6) of burner (1) outside, and priming supply (6) is connected with computer control system (7); Be useful on the sample holder (9) of installation testing sample (10) in the burner base (8); It is characterized in that, also be connected with high-voltage switch gear solenoid valve (16) and air capacity regulator (4) at the top of burner (1), wherein high-voltage switch gear solenoid valve (16) is connected with computer control system (7), between burner (1) and the high-voltage switch gear solenoid valve (16) screen pack (2) is arranged; At burner (1) opposite side, also be provided with the photoelectric sensor (17) that is connected with computer control system (7); Burner (1) also has air intake opening (13), goes up at air intake opening (13) and is connected with supercharge pump (14) and gas cylinder (15) in turn by pipeline, and wherein, supercharge pump (14) also is connected with computer control system (7).
2. solid propellant step-down blanket as claimed in claim 1 is characterized in that, it is CYG41000 that described pressure transducer (12) adopts model, and range is the pressure unit of 0～30MPa.
3. solid propellant step-down blanket as claimed in claim 1 is characterized in that, described photoelectric sensor (17) adopts the photomultiplier of infrared band.
4. solid propellant step-down blanket as claimed in claim 1 is characterized in that described supercharge pump (14) is selected HN100 high pressure nitrogen supercharger for use.
5. solid propellant step-down blanket as claimed in claim 1 is characterized in that, described high-pressure solenoid valve (16) adopts the Pumason GYB091459X of company type switching regulator solenoid valve.
6. solid propellant step-down blanket as claimed in claim 1 is characterized in that described screen pack (2) is stainless steel, and mesh diameter is not more than 200 μ m.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201010531622A CN101979999B (en) | 2010-11-04 | 2010-11-04 | Solid propellant depressurizing and extinguishing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201010531622A CN101979999B (en) | 2010-11-04 | 2010-11-04 | Solid propellant depressurizing and extinguishing device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101979999A true CN101979999A (en) | 2011-02-23 |
| CN101979999B CN101979999B (en) | 2011-12-28 |
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|---|---|---|---|
| CN201010531622A Expired - Fee Related CN101979999B (en) | 2010-11-04 | 2010-11-04 | Solid propellant depressurizing and extinguishing device |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103697935A (en) * | 2013-10-18 | 2014-04-02 | 南京理工大学 | Device for testing transient-state pressure release combustion instability characteristic of base bleed propellant |
| CN104950070A (en) * | 2015-07-14 | 2015-09-30 | 西安近代化学研究所 | Solid propellant flameout critical pressure reduction rate testing method |
| CN108548754A (en) * | 2018-05-09 | 2018-09-18 | 西北工业大学 | The quick blanket of solid propellant and method under a kind of condition of high voltage |
| CN112147268A (en) * | 2020-09-03 | 2020-12-29 | 西安近代化学研究所 | Device and method for nondestructively preparing flameout surface of solid propellant |
| CN112881229A (en) * | 2021-01-06 | 2021-06-01 | 西北工业大学 | Solid propellant high-pressure extinguishing combustion surface acquisition device and acquisition method |
| CN114184642A (en) * | 2022-02-16 | 2022-03-15 | 南京理工大学 | Solid propellant high-pressure ignition and combustion suspension test device |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4715260A (en) * | 1986-12-22 | 1987-12-29 | General Electric Company | Seal |
| GB2265085A (en) * | 1992-03-19 | 1993-09-22 | George Anthony Webster | Hyperbaric fire extinguisher |
| CN200972140Y (en) * | 2006-11-16 | 2007-11-07 | 乳源东阳光磁性材料有限公司 | Self-control burning machine |
| CN101650358A (en) * | 2009-09-17 | 2010-02-17 | 西安近代化学研究所 | Gunpowder combustion property test device under pressure reduction condition |
-
2010
- 2010-11-04 CN CN201010531622A patent/CN101979999B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4715260A (en) * | 1986-12-22 | 1987-12-29 | General Electric Company | Seal |
| GB2265085A (en) * | 1992-03-19 | 1993-09-22 | George Anthony Webster | Hyperbaric fire extinguisher |
| CN200972140Y (en) * | 2006-11-16 | 2007-11-07 | 乳源东阳光磁性材料有限公司 | Self-control burning machine |
| CN101650358A (en) * | 2009-09-17 | 2010-02-17 | 西安近代化学研究所 | Gunpowder combustion property test device under pressure reduction condition |
Non-Patent Citations (2)
| Title |
|---|
| 《宇航学报》 19920131 殷金其等 《液体喷射作用下固体推进剂熄火研究》 68-74 1-6 , 第1期 2 * |
| 《航空动力学报》 19900430 王峻晔等 《降压熄火过程复合推进剂燃速的测试研究》 173-176 1-6 第5卷, 第2期 2 * |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103697935A (en) * | 2013-10-18 | 2014-04-02 | 南京理工大学 | Device for testing transient-state pressure release combustion instability characteristic of base bleed propellant |
| 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 |
| CN104950070A (en) * | 2015-07-14 | 2015-09-30 | 西安近代化学研究所 | Solid propellant flameout critical pressure reduction rate testing method |
| CN108548754A (en) * | 2018-05-09 | 2018-09-18 | 西北工业大学 | The quick blanket of solid propellant and method under a kind of condition of high voltage |
| CN112147268A (en) * | 2020-09-03 | 2020-12-29 | 西安近代化学研究所 | Device and method for nondestructively preparing flameout surface of solid propellant |
| CN112881229A (en) * | 2021-01-06 | 2021-06-01 | 西北工业大学 | Solid propellant high-pressure extinguishing combustion surface acquisition device and acquisition method |
| CN114184642A (en) * | 2022-02-16 | 2022-03-15 | 南京理工大学 | Solid propellant high-pressure ignition and combustion suspension test device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN101979999B (en) | 2011-12-28 |
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