CN106198849A - A kind of test device for solid propellant combustion rate/combustion temperature and method of testing thereof - Google Patents
A kind of test device for solid propellant combustion rate/combustion temperature and method of testing thereof Download PDFInfo
- Publication number
- CN106198849A CN106198849A CN201610826778.7A CN201610826778A CN106198849A CN 106198849 A CN106198849 A CN 106198849A CN 201610826778 A CN201610826778 A CN 201610826778A CN 106198849 A CN106198849 A CN 106198849A
- Authority
- CN
- China
- Prior art keywords
- propellant
- plug
- combustion
- temperature
- pressure
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N31/00—Investigating or analysing non-biological materials by the use of the chemical methods specified in the subgroup; Apparatus specially adapted for such methods
- G01N31/12—Investigating or analysing non-biological materials by the use of the chemical methods specified in the subgroup; Apparatus specially adapted for such methods using combustion
Abstract
The present invention discloses a kind of test device for solid propellant combustion rate/combustion temperature and method of testing thereof, and this device includes closed burner body, plug one and plug two, the ignitor being arranged on plug one and relief valve and is arranged on the temperature sensor on plug two and pressure transducer；Closed burner body is cylindrical cavity cell structure, one end of closed burner body is threaded connection plug one, the other end is threaded connection plug two, closed burner is the most internal is provided with clamping device, propellant charge it is fixed with in clamping device, closed burner outer body is additionally provided with data acquisition process unit, and data acquisition process unit is connected with described pressure transducer, temperature sensor respectively.Present invention accomplishes the requirement of propellant energy quantification test, the environment under high pressure of solid propellant application can be simulated, and be obtained in that propellant combustion speed data in a high voltage state, combustion temperature data, thus the development for propellant provides relatively reliable design input.
Description
Technical field
The present invention relates to a kind of test device firing speed/combustion temperature, be specifically related to one and can be used for solid in confined conditions
The test device of propellant burning rate/combustion temperature and method of testing thereof, belong to SOLID PROPELLANT COMBUSTION performance test field.
Background technology
Solid propellant propulsion formula fire-fighting technique, as a kind of Halon Replacement fire-fighting technique, is a kind of using solid-state reactants as propelling
Agent, by there being the fast reaction of control, moment produces a large amount of noble gas products (such as nitrogen, steam and CO2Deng) drive
Firing-fighting medium discharges, a set of extinguishing device of the effect that reaches to stamp out a fire.This technology by feat of fast response time, take up room
Little, can preserve, abundant inert media can be produced by normal pressure, and the characteristics such as firing-fighting medium can be discharged in 100ms at aircraft
In material, small space fire extinguishing field achieves extensively application.But, drive the solid in source to push away as solid propellant propulsion formula extinguishing device
Enter agent and there is the shortcomings such as product temperatur is too high, burn rate is unstable always, suppress extinguishing effect, become its development of restriction
Serious hindrance.
First, there is the shortcoming that outlet temperature is high in the inertia firing-fighting medium that solid propellant produces, causes at extinguishing device
Spout forms outer flame flame, and may ignite unburned combustible, can endanger being formed secondary by guard space.Therefore, how to adopt
The combustion temperature of propellant to be measured is effectively measured in the measure that takes becomes an important process.
Secondly, the combustion speed of solid propellant is the important indicator of an assessment performance of propellant.Combustion speed is too fast may be caused
Solid propellant burns uncontrolled in the reactor of extinguishing device, even up to detonation, gives by the personnel of guard space and sets
Standby use brings danger；Combustion speed is too low can make again the gas production rate of propellant be substantially reduced, and slows down the injection of extinguishing chemical, cuts
Weak fire extinguishing effectiveness.
Therefore, the most effectively obtain the combustion temperature of propellant, combustion speed and these three parameters of burning rate pressure exponent to be situated between at propellant
Matter Performance Evaluation seems extremely important.
Closed bomb test propellant burning rate method is the conventional method of test combustion speed, it is advantageous that by once testing
Just can draw propellant combustion speed under whole pressure, need to be tested by many experiments just to obtain a level pressure compared to other
The method of testing (such as target collimation method, acoustic-emission etc.) of strong scope internal combustion speed, closed bomb vessel greatly increases test efficiency, behaviour
Make simple, there is the biggest practicality.But owing to closed bomb tests needs to carry out experimental data the process of complexity, and
Method of testing is theoretical based on powder burning, through a series of hypothesis and simplification, thus need to bring certain error.Additionally,
Commonly use the heat leakage of empirical equation correction closed bomb tests at present, do not consider propellant combustion staged pressure and radiation
The change of the heat transfer impact on heat leakage process, less consideration combustion gas and the heat transfer of closed bomb vessel internal face and heat leakage pair
The impact of propellant flame temperature in closed bomb vessel.Document " Burning Rate Measurement of Propellant at High Pressure by Closed Burner Method research " carries
Although it is the shortest to go out the closed burner working time, but the pressure loss being because radiation loss and causing is very big, under low pressure very
To reaching 30%.And contrasted by great many of experiments, mean heat loss's modification method, reverse pushing-type heat-loss correction method, heat transfer
It is not very accurate for calculating the radiation loss corrections such as heat-loss correction method, and error is bigger.Thus calculate based on radiation loss
The difference that combustion speed result is bigger with physical presence.Patent " a kind of propellant powder dynamic Burning rate testing device " (CN104048563B)
In, the method utilizing closed bomb vessel to measure solid propellant combustion rate is described in detail, but combustion temperature is not made
The calculating of combustion speed is carried out for input parameter.
Therefore, from the technical data of at present retrieval, there is not yet about using the combustion temperature of propellant under airtight condition as defeated
Enter the open report of parameter derivation combustion speed.
Summary of the invention
The problem existed for above-mentioned prior art, the present invention proposes a kind of survey for solid propellant combustion rate/combustion temperature
Electricity testing device and method of testing thereof, it is possible to avoid the error brought by closed burner heat leakage correction, can be the development of propellant
Relatively reliable input data are provided with solid propellant propulsion formula extinguishing device powder charge design.
To achieve these goals, a kind of test device for solid propellant combustion rate/combustion temperature that the present invention uses, bag
The point include closed burner body, the plug one being arranged on closed burner body two ends and plug two, being arranged on plug one
Thermoelectricity pole and relief valve and be arranged on the temperature sensor on plug two and pressure transducer；
Described closed burner body is cylindrical cavity cell structure, and one end of closed burner body is threaded connection stifled
First, the other end is threaded connection plug two, this internal clamping device that is provided with of closed burner, fixing in described clamping device
Propellant charge, described closed burner outer body is had to be additionally provided with data acquisition process unit, described data acquisition process list
Unit is connected with described pressure transducer, temperature sensor respectively.
As improvement, described ignitor is threadedly attached on plug one, and described relief valve is threadedly attached in
On plug one.
As improvement, being provided with insulation sleeve between described ignitor and plug one, described insulation sleeve is wrapped in outside ignitor
Surface.
As improvement, between described plug one, plug two and closed burner body, it is respectively equipped with sealing ring.
As improvement, the inwall of described plug two is threaded connection described pressure transducer, plug two has had
One through hole, connects in described through hole and has described temperature sensor；
When described pressure transducer is used for measuring propellant charge burning, the pressure produced in closed burner, described temperature
Flame temperature when degree sensor is for measuring propellant combustion.
As improvement, described data acquisition process unit is respectively by cable and described pressure transducer, temperature sensor
Connect；
Described data acquisition process unit is for gathering pressure transducer, the pressure of temperature sensor measurement, temperature parameter.
As improvement, described clamping device is arranged on closed burner body interior centre position, described clamping device
Bottom is provided with support, and outside is provided with the fence for preventing propellant charge from toppling over.
It addition, present invention also offers a kind of employing described in any of the above-described item for solid propellant combustion rate/combustion temperature test
The method of testing of device, comprises the following steps:
1) use PMMA acetone soln that the side of propellant charge is coated with, one layer of thin epoxy resin of dried painting,
Measure the physical dimension parameter of propellant charge, then propellant charge is placed in clamping device；
2) ignitor, relief valve are connected with plug one respectively, then by pressure transducer, temperature sensor respectively with
Plug two connects, then plug one, plug two is sealed installation with closed burner body, and guarantee that relief valve is in cut out shape
State；
3) starting ignition electrode ignites propellant charge, and propellant combustion produces a large amount of gases, cavity in closed burner
Internal pressure rises, and triggers pressure transducer and gathers pressure signal, and temperature sensor gathers propellant flame temperature signal；
4) propellant combustion is complete, off-test, after 5-8 minute, opens relief valve, discharges the gas within closed burner
Body product, unloads lower end cap one, removes the solid residue of burner internal residual；
5) data process；
A) pressure-time and the Temperature-time data and curves of closed burner during propellant combustion are read respectively；
B) pressure of closed burner, the flame temperature of propellant, the grain density of propellant meet relationship below:
Sw=2 π (r-w)2+2π(r-w)(h-2w) (2)
W (t)=∫ r (p) dt (4)
In formula:For gaseous mass generating rate, P is pressure, and V is the volume of closed burner, and r (p) is propellant
Combustion speed, TfFor propellant flame temperature, cpFor level pressure thermal capacitance, cvFor constant volume thermal capacitance, R is ideal gas constant, ρpFor COMPOSITE SOLID PROPELLANT
The density of post, w is that the meat of combustion of propellant is thick；
Utilize numerical computation method, pressure-time graph that Binding experiment data obtain, solved by formula (1)-(4)
Combustion speed-pressure curve, can complete data and process.
Compared with prior art, the invention has the beneficial effects as follows:
1) test device and the method for testing thereof of solid propellant combustion rate/combustion temperature of present invention offer are used, from calculating public affairs
It can be seen that fast and the propellant in closed burner combustion temperature Tf of the combustion of the present invention has relation, by the combustion of propellant in formula (1)
Temperature, as input parameter, is included in Burning rate calculation, is eliminated the impact that traditional heat leakage corrected Calculation is brought.Therefore, can have
Effect solves conventional containment burner method under low pressure because heat loss ratio is big, and is difficult to accurately to estimate that the Burning rate testing that causes is not
Accurate problem, the present invention is without being modified ignition temperature by the method for heat leakage correction, and survey calculation is accurate.
2) present invention passes through single test, can obtain the combustion speed-pressure data in wider pressure limit and combustion temperature data,
The data obtained can be used for evaluating the combustibility of propellant in solid propellant propulsion formula extinguishing device, it is judged that it is low whether the side of being measured meets
Combustion temperature, the requirement of high combustion speed.Data are reliable, convenience of calculation.
Accompanying drawing explanation
Fig. 1 is the test apparatus structure schematic diagram of solid propellant combustion rate of the present invention/combustion temperature；
Fig. 2 is the structural representation of clamping device in the present invention；
Fig. 3 is the structural representation of solid propellant grain in the present invention；
Fig. 4 is the pressure-time graph of the present invention；
Combustion speed-pressure curve that Fig. 5 is the present invention；
In figure: 1, closed burner body, 2, plug one, 3, plug two, 4, sealing ring, 5, ignitor, 6, insulation sleeve,
7, relief valve, 8, pressure transducer, 9, temperature sensor, 10, clamping device, 11, fence, 12, propellant charge, 13, data
Acquisition process unit.
Detailed description of the invention
Following embodiment is to further illustrate using as the explaination to the technology of the present invention content for present invention, but
The flesh and blood of the present invention is not limited in described in following embodiment, those of ordinary skill in the art can and should know appoint
What simple change based on true spirit or replacement all should belong to protection domain of the presently claimed invention.
As shown in Figure 1 and Figure 2, a kind of test device for solid propellant combustion rate/combustion temperature, including closed burner originally
Body 1, the plug 1 being arranged on closed burner body 1 two ends and plug 23, ignitor 5 and being arranged on plug 1
Relief valve 7 and the temperature sensor 9 being arranged on plug 23 and pressure transducer 8；
Described closed burner body 1 is cylindrical cavity cell structure, uses supertension high strength steel processing and manufacturing, and volume is
70ml, the highest pressure-bearing 100MPa, one end of closed burner body 1 is threaded connection plug 1, and the other end is by screw thread even
Connect plug 23, wherein, preferably use trapezoidal thread to connect, in closed burner body 1, be provided with clamping device 10, described folder
It is fixed with propellant charge 12 in holding device 10, outside described closed burner body 1, is additionally provided with data acquisition process unit 13,
Described data acquisition process unit 13 is connected with described pressure transducer 8, temperature sensor 9 respectively.
As the improvement of embodiment, described ignitor 5 is threadedly attached on plug 1, and described relief valve 7 passes through
It is threaded on plug 1.Easy to connect, dismounting is simple, is discharged by the relief valve 7 waste gas after test.
As the improvement of embodiment, being provided with insulation sleeve 6 between described ignitor 5 and plug 1, described insulation sleeve 6 wraps up
At ignitor 5 outer surface.Ignitor 5 uses bridge wire form nichrome wire to light a fire, and match board head, bridge silk use nichrome,
Diameter takes 0.05mm, and the initial firing current of lighter is 8A.
As the improvement of embodiment, between described plug 1, plug 23 and closed burner body 1, it is respectively equipped with sealing ring
4, it is beneficial to dismounting, cleans and pressure-bearing.
As the improvement of embodiment, the inwall of described plug 23 is threaded connection described pressure transducer 8, stifled
Having a through hole on 23, connecting in described through hole has described temperature sensor 9；
Described pressure transducer 8 is used for measuring propellant charge 12 when burning, and the pressure produced in closed burner is described
Flame temperature when temperature sensor 9 is for measuring propellant combustion.Pressure transducer 8 is CY400 high-frequency pressure, pressure drag formula weight
Journey 20MPa, the natural frequency of vibration is more than 400kHz.Owing in burner, propellant combustion exists the feature of strong transient state, inner wall temperature
Measure the temperature sensor 9 using custom-designed package thickness minimum (H=0.298mm), and when installing, temperature sensor 9
End be positioned at the top of propellant charge 12, the thermocouple wire end of temperature sensor 9 is the form that face contacts with big envelope, can
Meet the collection feature of high dynamic.
As the improvement of embodiment, described data acquisition process unit 13 respectively by cable and described pressure transducer 8,
Temperature sensor 9 connects；
Described data acquisition process unit 13 is for gathering pressure transducer 8, the pressure of temperature sensor 9 measurement, temperature
Parameter.This data acquisition process unit 13 uses TST6250 high-speed data recording instrument, data actuation sample rate 20Msps.
As the improvement of embodiment, described clamping device 10 is arranged on closed burner body 1 bosom position, described
The bottom of clamping device 10 is provided with support, and outside is provided with the fence 11 for preventing propellant charge 12 from toppling over.The bottom used
Support is little with the contact area of propellant charge 12 so that propellant charge 12 meets recurrence combustion law.
Use said apparatus when measuring, specifically include following steps:
1) in this embodiment, use PMMA acetone soln that the side of propellant charge 12 is coated with, be coated with after drying
One layer of thin epoxy resin；Powder column quality 12.1g, highly 17.2mm after mensuration processes the most again, diameter 25.5mm, then by propellant
Powder column 12 is placed in clamping device 10；
2) ignitor 5, relief valve 7 are connected with plug 1 respectively, then by pressure transducer 8, temperature sensor 9
It is connected with plug 23 respectively, then plug 1, plug 23 with closed burner body 1, are sealed installation, and guarantee relief valve 7
It is closed；
3) before experiment, starting data acquisition process unit 13, arranging Signal trigger mode is internal trigger；
4) during experiment, starting ignition electrode 5 ignites propellant charge 12, and propellant combustion produces a large amount of gases, and constant volume fires
In burner, inside cavity pressure rises, and triggers pressure transducer 8 and gathers pressure signal, and temperature sensor 9 gathers propellant flame
Temperature signal, data acquisition process unit 13 synchronous acquisition pressure signal and temperature signal, and according to the pressure collected, temperature
Signal, data acquisition process unit 13 draws out pressure-time, Temperature-time data and curves；
4) propellant combustion is complete, off-test, after 5-8 minute, opens relief valve 7, discharges within closed burner
Gaseous product, unloads lower end cap 1, removes the solid residue of burner internal residual；
5) data process；
1) can obtain according to The Ideal-Gas Equation,
2) can obtain according to law of conservation of energy,
3) combine above-mentioned two formula, equation below can be obtained
4) following parameter is inputted: the volume of V-closed burner, the combustion speed of r (p)-propellant, Tf-propellant flame temperature
Degree, cp-level pressure thermal capacitance, cv-constant volume thermal capacitance, R-ideal gas constant, ρpThe density of-propellant charge.It it is pressure change rate
(derivative of pressure versus time),It is heat gradient,It is gas constant rate of change,Constant volume thermal capacitance rate of change.
Just " gaseous mass generating rate-time " data can be obtained by " pressure versus time " data.Wherein, in order to keep away
Exempting from the impact that irregular combustion brings, the starting point of " pressure versus time " data of pressure transducer gained proceeds as follows choosing
Take:
Playing point selection and firing the point that mass percent is 15%, terminal selects at (dp/dt)maxPlace, i.e. Pressure versus Time
The point of derivative maximum.
5) follow recurrence combustion law due to the burning of propellant, therefore, the propellant charge surface area burnt off with
There is following relation in combustion thickness:
Sw=2 π (r-w)2+2π(r-w)(h-2w)
6) the propellant charge surface area that burnt off, fire thickness and combustion speed and there is again following relation:
W (t)=∫ r (p) dt
7) combine above-mentioned two formulas and just can pass through " gaseous mass generating rate-time " relation, be derived from " combustion speed-time
Between " relation, and then obtain " combustion speed-pressure " relation, thus complete Data Processing in Experiment.
The foregoing is only presently preferred embodiments of the present invention, not in order to limit the present invention, all essences in the present invention
Any amendment, equivalent or the improvement etc. made within god and principle, should be included within the scope of the present invention.
Claims (8)
1. one kind for the warm test device of solid propellant combustion rate/combustion, it is characterised in that include closed burner body (1),
The ignitor be arranged on the plug one (2) at closed burner body (1) two ends and plug two (3), being arranged on plug one (2)
And relief valve (7) and the temperature sensor (9) being arranged on plug two (3) and pressure transducer (8) (5)；
Described closed burner body (1) is cylindrical cavity cell structure, and one end of closed burner body (1) is threaded connection
Plug one (2), the other end is threaded connection plug two (3), is provided with clamping device (10), institute in closed burner body (1)
Being fixed with propellant charge (12) in stating clamping device (10), described closed burner body (1) outside is additionally provided with data acquisition
Processing unit (13), described data acquisition process unit (13) is respectively with described pressure transducer (8), temperature sensor (9) even
Connect.
A kind of test device for solid propellant combustion rate/combustion temperature the most according to claim 1, it is characterised in that institute
Stating ignitor (5) to be threadedly attached on plug one (2), described relief valve (7) is threadedly attached in plug one (2)
On.
A kind of test device for solid propellant combustion rate/combustion temperature the most according to claim 2, it is characterised in that institute
Stating and be provided with insulation sleeve (6) between ignitor (5) and plug one (2), described insulation sleeve (6) is wrapped in ignitor (5) outer surface.
A kind of test device for solid propellant combustion rate/combustion temperature the most according to claim 1, it is characterised in that institute
State and be respectively equipped with sealing ring (4) between plug one (2), plug two (3) and closed burner body (1).
A kind of test device for solid propellant combustion rate/combustion temperature the most according to claim 1, it is characterised in that institute
State and on the inwall of plug two (3), be threaded connection described pressure transducer (8), plug two (3) has a through hole, described
Connect in through hole and have described temperature sensor (9)；
When described pressure transducer (8) is used for measuring propellant charge (12) burning, the pressure produced in closed burner, described
Flame temperature when temperature sensor (9) is for measuring propellant combustion.
A kind of test device for solid propellant combustion rate/combustion temperature the most according to claim 1, it is characterised in that institute
State data acquisition process unit (13) to be connected with described pressure transducer (8), temperature sensor (9) by cable respectively；
Described data acquisition process unit (13) is used for pressure, the temperature gathering pressure transducer (8), temperature sensor (9) is measured
Degree parameter.
A kind of test device for solid propellant combustion rate/combustion temperature the most according to claim 1, it is characterised in that institute
Stating clamping device (10) and be arranged on closed burner body (1) bosom position, the bottom of described clamping device (10) is provided with
Support, outside is provided with the fence (11) for preventing propellant charge (12) from toppling over.
8. use the method for testing for solid propellant combustion rate/combustion temperature test device described in any one of claim 1-7,
It is characterized in that, comprise the following steps:
1) use PMMA acetone soln that the side of propellant charge (12) is coated with, one layer of thin epoxy resin of dried painting,
Measure the physical dimension parameter of propellant charge (12), then propellant charge (12) is placed in clamping device (10)；
2) ignitor (5), relief valve (7) are connected with plug one (2) respectively, then by pressure transducer (8), temperature sensing
Device (9) is connected with plug two (3) respectively, then with closed burner body (1), plug one (2), plug two (3) are sealed installation,
And guarantee that relief valve (7) is closed；
3) starting ignition electrode (5) ignites propellant charge (12), and propellant combustion produces a large amount of gases, closed burner lumen
Body internal pressure rises, and triggers pressure transducer (8) and gathers pressure signal, and temperature sensor (9) gathers propellant flame temperature
Signal；
4) propellant combustion is complete, off-test, after 5-8 minute, opens relief valve (7), discharges the gas within closed burner
Body product, unloads lower end cap one (2), removes the solid residue of burner internal residual；
5) data process；
A) pressure-time and the Temperature-time data and curves of closed burner during propellant combustion are read respectively；
B) pressure of closed burner, the flame temperature of propellant, the grain density of propellant meet relationship below:
Sw=2 π (r-w)2+2π(r-w)(h-2w) (2)
W (t)=∫ r (p) dt (4)
In formula:For gaseous mass generating rate, P is pressure, and V is the volume of closed burner, and r (p) is the combustion of propellant
Speed, TfFor propellant flame temperature, cpFor level pressure thermal capacitance, cvFor constant volume thermal capacitance, R is ideal gas constant, ρpFor propellant charge
Density, w is that the meat of combustion of propellant is thick；
Utilize numerical computation method, pressure-time graph that Binding experiment data obtain, by formula (1)-(4) solve combustion speed-
Pressure curve, can complete data and process.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610826778.7A CN106198849B (en) | 2016-09-14 | 2016-09-14 | It is a kind of for solid propellant combustion rate/combustion temperature test device and its test method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610826778.7A CN106198849B (en) | 2016-09-14 | 2016-09-14 | It is a kind of for solid propellant combustion rate/combustion temperature test device and its test method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106198849A true CN106198849A (en) | 2016-12-07 |
| CN106198849B CN106198849B (en) | 2019-04-26 |
Family
ID=58067940
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610826778.7A Active CN106198849B (en) | 2016-09-14 | 2016-09-14 | It is a kind of for solid propellant combustion rate/combustion temperature test device and its test method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106198849B (en) |
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107191292A (en) * | 2017-04-25 | 2017-09-22 | 西北工业大学 | A kind of local fuel regression rate method of testing of hybrid motor fuel |
| CN107656031A (en) * | 2016-12-12 | 2018-02-02 | 湖北航天化学技术研究所 | Gases at high pressure Impulsive load Testing Method of Safety for energetic material |
| CN108663475A (en) * | 2018-05-18 | 2018-10-16 | 西北工业大学 | A kind of real-time Burning rate testing apparatus and method of micro- powder column |
| CN109100147A (en) * | 2018-07-24 | 2018-12-28 | 北京理工大学 | A kind of experimental provision for assessing solid engines slow cook-off responsiveness |
| CN109387542A (en) * | 2018-12-28 | 2019-02-26 | 公安部天津消防研究所 | Multiple sources pond fire combustion simulation experiment porch and experimental method |
| CN109521142A (en) * | 2019-01-07 | 2019-03-26 | 大连理工大学 | A kind of device and method for the measurement solid propellant velocity of sound under the conditions of pressure change |
| CN109596770A (en) * | 2018-11-27 | 2019-04-09 | 西安近代化学研究所 | A kind of propellant powder explosion fragment pressure release extinction device |
| CN109655576A (en) * | 2019-02-18 | 2019-04-19 | 湖北航天化学技术研究所 | A kind of device of the roasting combustion responsiveness of rapid evaluation solid propellant |
| CN109884267A (en) * | 2019-01-29 | 2019-06-14 | 北京理工大学 | The experimental provision and method measured for propellant multi-angle burn rate under overload condition |
| CN110231363A (en) * | 2019-05-23 | 2019-09-13 | 西安交通大学 | A method of research energetic material reaction mechanism and safety evaluation |
| CN110486192A (en) * | 2019-08-18 | 2019-11-22 | 南京理工大学 | The connection of dipulse engine ablation test and test device |
| CN110886669A (en) * | 2019-11-25 | 2020-03-17 | 湖北三江航天江河化工科技有限公司 | Test engine for testing solid rocket propellant |
| CN112523901A (en) * | 2020-12-11 | 2021-03-19 | 上海航天化工应用研究所 | Medicine device is tied up in test of electrically conductive solid propellant burning rate of residue |
| 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 |
| CN115618171A (en) * | 2022-06-06 | 2023-01-17 | 北京理工大学 | Propellant combustion balance product solving method based on homotopy algorithm |
| CN116026981A (en) * | 2023-03-27 | 2023-04-28 | 中国科学技术大学 | Device and method for detecting efficacy of solid fire extinguishing agent |
Citations (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4430885A (en) * | 1982-06-01 | 1984-02-14 | The United States Of America As Represented By The Secretary Of The Army | Apparatus for determining the burn rate of uncured propellant |
| US20030192364A1 (en) * | 2002-04-12 | 2003-10-16 | Khadduri Farid M. | Propellant test apparatus and method |
| JP2004225678A (en) * | 2003-01-20 | 2004-08-12 | Katsuya Hasegawa | Burnt-out wire type burning velocity measuring method |
| CN1888897A (en) * | 2006-07-13 | 2007-01-03 | 西安电子科技大学 | Rocket solid propellant burning velocity testing system |
| JP2010236425A (en) * | 2009-03-31 | 2010-10-21 | Nof Corp | Combustion speed measurement device, and measurement method using the same |
| CN102967526A (en) * | 2012-11-28 | 2013-03-13 | 西北工业大学 | Method for measuring relationship between actual temperature and pressure in combustion process through constant volume combustor method |
| CN102980970A (en) * | 2012-11-28 | 2013-03-20 | 西北工业大学 | Method for obtaining propelling agent combustion speed by utilizing constant-capacity combustor |
| CN103439360A (en) * | 2013-07-29 | 2013-12-11 | 江苏中科国腾科技有限公司 | Solid propellant multi-thermocouple dynamic combustion performance testing system and method |
| CN203350235U (en) * | 2013-07-31 | 2013-12-18 | 湖北航天化学技术研究所 | Propellant burning speed test device |
| CN203365362U (en) * | 2013-07-29 | 2013-12-25 | 西安电子科技大学 | Combustion chamber device used for testing dynamic combustion performance of solid propellant by utilizing multiple thermocouples |
| CN104330520A (en) * | 2014-10-30 | 2015-02-04 | 西北工业大学 | Testing device and testing method of constant volume combustion of solid propellant |
| CN104345118A (en) * | 2013-07-29 | 2015-02-11 | 西安电子科技大学 | Solid propellant multi-target wire dynamic combustion performance testing system and method thereof |
| CN104374865A (en) * | 2014-11-14 | 2015-02-25 | 西北工业大学 | Test device and method for solid propellant burning rate |
| CN104950007A (en) * | 2015-07-14 | 2015-09-30 | 西安近代化学研究所 | Solid-propellant ignition and burning speed integrated testing device |
| CN206096055U (en) * | 2016-09-14 | 2017-04-12 | 中国科学技术大学 | A testing arrangement that is used for solid propellant to fire invite / firing temperature |
-
2016
- 2016-09-14 CN CN201610826778.7A patent/CN106198849B/en active Active
Patent Citations (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4430885A (en) * | 1982-06-01 | 1984-02-14 | The United States Of America As Represented By The Secretary Of The Army | Apparatus for determining the burn rate of uncured propellant |
| US20030192364A1 (en) * | 2002-04-12 | 2003-10-16 | Khadduri Farid M. | Propellant test apparatus and method |
| JP2004225678A (en) * | 2003-01-20 | 2004-08-12 | Katsuya Hasegawa | Burnt-out wire type burning velocity measuring method |
| CN1888897A (en) * | 2006-07-13 | 2007-01-03 | 西安电子科技大学 | Rocket solid propellant burning velocity testing system |
| JP2010236425A (en) * | 2009-03-31 | 2010-10-21 | Nof Corp | Combustion speed measurement device, and measurement method using the same |
| CN102980970A (en) * | 2012-11-28 | 2013-03-20 | 西北工业大学 | Method for obtaining propelling agent combustion speed by utilizing constant-capacity combustor |
| CN102967526A (en) * | 2012-11-28 | 2013-03-13 | 西北工业大学 | Method for measuring relationship between actual temperature and pressure in combustion process through constant volume combustor method |
| CN103439360A (en) * | 2013-07-29 | 2013-12-11 | 江苏中科国腾科技有限公司 | Solid propellant multi-thermocouple dynamic combustion performance testing system and method |
| CN203365362U (en) * | 2013-07-29 | 2013-12-25 | 西安电子科技大学 | Combustion chamber device used for testing dynamic combustion performance of solid propellant by utilizing multiple thermocouples |
| CN104345118A (en) * | 2013-07-29 | 2015-02-11 | 西安电子科技大学 | Solid propellant multi-target wire dynamic combustion performance testing system and method thereof |
| CN203350235U (en) * | 2013-07-31 | 2013-12-18 | 湖北航天化学技术研究所 | Propellant burning speed test device |
| CN104330520A (en) * | 2014-10-30 | 2015-02-04 | 西北工业大学 | Testing device and testing method of constant volume combustion of solid propellant |
| CN104374865A (en) * | 2014-11-14 | 2015-02-25 | 西北工业大学 | Test device and method for solid propellant burning rate |
| CN104950007A (en) * | 2015-07-14 | 2015-09-30 | 西安近代化学研究所 | Solid-propellant ignition and burning speed integrated testing device |
| CN206096055U (en) * | 2016-09-14 | 2017-04-12 | 中国科学技术大学 | A testing arrangement that is used for solid propellant to fire invite / firing temperature |
Cited By (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107656031A (en) * | 2016-12-12 | 2018-02-02 | 湖北航天化学技术研究所 | Gases at high pressure Impulsive load Testing Method of Safety for energetic material |
| CN107191292B (en) * | 2017-04-25 | 2019-02-01 | 西北工业大学 | A kind of hybrid motor fuel part fuel regression rate test method |
| CN107191292A (en) * | 2017-04-25 | 2017-09-22 | 西北工业大学 | A kind of local fuel regression rate method of testing of hybrid motor fuel |
| CN108663475A (en) * | 2018-05-18 | 2018-10-16 | 西北工业大学 | A kind of real-time Burning rate testing apparatus and method of micro- powder column |
| CN109100147A (en) * | 2018-07-24 | 2018-12-28 | 北京理工大学 | A kind of experimental provision for assessing solid engines slow cook-off responsiveness |
| CN109596770A (en) * | 2018-11-27 | 2019-04-09 | 西安近代化学研究所 | A kind of propellant powder explosion fragment pressure release extinction device |
| CN109387542B (en) * | 2018-12-28 | 2023-09-29 | 应急管理部天津消防研究所 | Multi-point source pool fire combustion simulation experiment platform and experiment method |
| CN109387542A (en) * | 2018-12-28 | 2019-02-26 | 公安部天津消防研究所 | Multiple sources pond fire combustion simulation experiment porch and experimental method |
| CN109521142A (en) * | 2019-01-07 | 2019-03-26 | 大连理工大学 | A kind of device and method for the measurement solid propellant velocity of sound under the conditions of pressure change |
| CN109884267A (en) * | 2019-01-29 | 2019-06-14 | 北京理工大学 | The experimental provision and method measured for propellant multi-angle burn rate under overload condition |
| CN109655576A (en) * | 2019-02-18 | 2019-04-19 | 湖北航天化学技术研究所 | A kind of device of the roasting combustion responsiveness of rapid evaluation solid propellant |
| CN110231363A (en) * | 2019-05-23 | 2019-09-13 | 西安交通大学 | A method of research energetic material reaction mechanism and safety evaluation |
| CN110486192A (en) * | 2019-08-18 | 2019-11-22 | 南京理工大学 | The connection of dipulse engine ablation test and test device |
| CN110886669A (en) * | 2019-11-25 | 2020-03-17 | 湖北三江航天江河化工科技有限公司 | Test engine for testing solid rocket propellant |
| CN112523901A (en) * | 2020-12-11 | 2021-03-19 | 上海航天化工应用研究所 | Medicine device is tied up in test of electrically conductive solid propellant burning rate of residue |
| 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 |
| CN115618171A (en) * | 2022-06-06 | 2023-01-17 | 北京理工大学 | Propellant combustion balance product solving method based on homotopy algorithm |
| CN115618171B (en) * | 2022-06-06 | 2023-10-24 | 北京理工大学 | Method for solving propellant combustion balance product based on homotopy algorithm |
| CN116026981A (en) * | 2023-03-27 | 2023-04-28 | 中国科学技术大学 | Device and method for detecting efficacy of solid fire extinguishing agent |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106198849B (en) | 2019-04-26 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106198849A (en) | A kind of test device for solid propellant combustion rate/combustion temperature and method of testing thereof | |
| CN206096055U (en) | A testing arrangement that is used for solid propellant to fire invite / firing temperature | |
| CN201156037Y (en) | Pyrotechnic compound combustion and explosion performance detector | |
| Falempin et al. | Recent experimental results obtained on continuous detonation wave engine | |
| CN108548754B (en) | Device and method for quickly extinguishing solid propellant under high pressure condition | |
| CN103558118B (en) | Based on the method for testing of the temperature and pressure explosive temperature and pressure effect quantitative evaluation of implode test | |
| Zhang et al. | Influence of nitromethane concentration on ignition energy and explosion parameters in gaseous nitromethane/air mixtures | |
| CN108088949B (en) | A kind of experimental provision that COMBUSTION TO DETONATION TRANSITION is influenced for convective burning and method | |
| CN104155341B (en) | A kind of boron powder combustion heat value test device | |
| NO338902B1 (en) | Thermal erosion testing apparatus and a method for testing thermally protective materials in solid fuel thrusters. | |
| CN104374865A (en) | Test device and method for solid propellant burning rate | |
| CN103697935B (en) | End row's propellant transient state pressure release burning buckling behaviors proving installation | |
| CN201607417U (en) | Unit for measuring ignition temperature of gunpowder | |
| CN107656031A (en) | Gases at high pressure Impulsive load Testing Method of Safety for energetic material | |
| CN103196910B (en) | A kind of temperature variant method of test Loading Materials for Initiating Explosive Devices performance | |
| Mogi et al. | Explosion and detonation characteristics of dimethyl ether | |
| Kuracina et al. | A new 365-litre dust explosion chamber: Design and testing | |
| CN109596770B (en) | Propellant powder explosion fragment pressure relief combustion stopping device | |
| CN104457457B (en) | Testing delay of detonator delay element new method | |
| CN111271195B (en) | High-precision solid propellant gas generation amount testing device | |
| Birk et al. | Interrupted‐Burning Tests of Plasma‐Ignited JA2 and M30 Grains in a Closed Chamber | |
| CN106124895B (en) | A kind of solid engines electrostatic safety system safety testing device and method | |
| RU2324926C2 (en) | Method of research of conditions of powder charge ignition with explosive fuel and air mixture during mixture blasting and device for its implementation | |
| CN112067741A (en) | Device for testing high-temperature and high-pressure environment in oxygen bomb | |
| CN101738146B (en) | Gunpowder ignition temperature measuring device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |