CN106198849B - It is a kind of for solid propellant combustion rate/combustion temperature test device and its test method - Google Patents
It is a kind of for solid propellant combustion rate/combustion temperature test device and its test method Download PDFInfo
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Abstract
The present invention discloses a kind of for solid propellant combustion rate/combustion temperature test device and its test method, which includes closed burner ontology, plug one and plug two, the ignitor being arranged on plug one and relief valve and the temperature sensor and pressure sensor being arranged on plug two；Closed burner ontology is cylindrical cavity cell structure, one end of closed burner ontology is connected through a screw thread plug one, the other end is connected through a screw thread plug two, clamping device is equipped in closed burner ontology, propellant charge is fixed in clamping device, closed burner outer body is additionally provided with data acquisition process unit, and data acquisition process unit is connect with the pressure sensor, temperature sensor respectively.Present invention accomplishes the requirement of propellant energy quantification test, the hyperbaric environments of analog solid propellant application, and can obtain burn rate data, the warm data of combustion of propellant in a high voltage state, so that the development for propellant provides relatively reliable design input.
Description
Technical field
The present invention relates to a kind of burn rate/combustion temperature test devices, and in particular to one kind can be used for solid in confined conditions
Propellant burning rate/combustion temperature test device and its test method, belong to SOLID PROPELLANT COMBUSTION performance test field.
Background technique
Solid propellant propulsion formula fire-fighting technique is a kind of using solid-state reactants as propulsion as a kind of Halon Replacement fire-fighting technique
Agent, by controlled fast reaction, moment generates a large amount of inert gas product (such as nitrogen, vapor and CO2Deng) drive
Firing-fighting medium release, reaches a set of extinguishing device for the effect that stamps out a fire.The technology is by feat of fast response time, occupied space
It is small, can normal pressure save, can produce inert media abundant, and the characteristics such as firing-fighting medium can be discharged in 100ms in aircraft
Small space fire extinguishing field achieves extensive use in material.However, the solid as solid propellant propulsion formula extinguishing device driving source pushes away
The disadvantages of product temperatur is excessively high, burn rate is unstable is always existed into agent, inhibits extinguishing effect, becomes its development of restriction
Serious hindrance.
Firstly, the inertia firing-fighting medium that solid propellant generates haves the shortcomings that outlet temperature is high, cause in extinguishing device
Spout forms outer flame flame, and may ignite unburned combustible, can form secondary hazards to by guard space.Therefore, how to adopt
The combustion temperature for taking measure effectively to measure propellant to be measured becomes an important process.
Secondly, the burn rate of solid propellant is the important indicator of an assessment performance of propellant.Burn rate is too fast to be may cause
Solid propellant burns uncontrolled, even up to detonation in the reactor of extinguishing device, to by the personnel of guard space and setting
Standby use brings danger；Burn rate is too low and the gas production rate of propellant can be made to substantially reduce, and slows down the injection of extinguishing chemical, cuts
Weak fire extinguishing effectiveness.
Therefore, this three parameters of combustion temperature, burn rate and the burning rate pressure exponent of propellant how are effectively obtained to be situated between in propellant
Seem extremely important in matter Performance Evaluation.
Closed bomb test propellant burning rate method is to test the conventional method of burn rate, it is advantageous that by once testing
It can obtain burn rate of the propellant under whole pressure, a level pressure can just be obtained by needing to test by many experiments compared to other
The test method (such as target collimation method, acoustic-emission) of burn rate in strong range, closed bomb vessel greatly increases test efficiency, behaviour
Make simply, there is very big practicability.But since closed bomb tests need to carry out experimental data complicated processing, and
Test method is based on powder burning theory, need to pass through a series of hypothesis and simplification, thus brings certain error.In addition,
The heat leakage of empirical equation amendment closed bomb tests is commonly used, does not consider propellant combustion staged pressure and radiation
Influence of the variation of heat transfer to heat leakage process, it is less to consider combustion gas and the heat transfer of closed bomb vessel inner wall and heat leakage pair
The influence of propellant flame temperature in closed bomb vessel.It is mentioned in document " Burning Rate Measurement of Propellant at High Pressure by Closed Burner Method research "
Although the closed burner working time is very short out because radiation loss and caused by the pressure loss it is very big, under low pressure very
To reaching 30%.And it is compared by many experiments, mean heat loss's modification method, reverse pushing-type heat-loss correction method, heat transfer
Calculating the radiation losses such as heat-loss correction method amendment is not very accurately that error is larger.Thus calculated based on radiation loss
Burn rate result and the biggish difference of physical presence.Patent " a kind of propellant powder dynamic Burning rate testing device " (CN104048563B)
In, the method using closed bomb vessel measurement solid propellant combustion rate is described in detail, but does not make combustion temperature
The calculating of burn rate is carried out for input parameter.
Therefore, from the technical data retrieved at present, there is not yet in relation to the combustion temperature using propellant under confined conditions as defeated
Enter the open report of parameter derivation burn rate.
Summary of the invention
In view of the above-mentioned problems of the prior art, the present invention propose it is a kind of for the survey of solid propellant combustion rate/combustion temperature
Trial assembly is set and its test method, can be avoided and corrects bring error by closed burner heat leakage, can be the development of propellant
Relatively reliable input data is provided with solid propellant propulsion formula extinguishing device powder charge design.
To achieve the goals above, what the present invention used is a kind of for solid propellant combustion rate/combustion temperature test device, packet
Include closed burner ontology, the plug one that closed burner ontology both ends are set and plug two, the point being arranged on plug one
Thermoelectricity pole and relief valve and the temperature sensor and pressure sensor being arranged on plug two；
The closed burner ontology is cylindrical cavity cell structure, and one end of closed burner ontology is connected through a screw thread stifled
First, the other end is connected through a screw thread plug two, and clamping device is equipped in closed burner ontology, is fixed in the clamping device
There is propellant charge, the closed burner outer body is additionally provided with data acquisition process unit, the data acquisition process list
Member is connect with the pressure sensor, temperature sensor respectively.
As an improvement, the ignitor is threadedly attached on plug one, the relief valve is threadedly attached in
On plug one.
As an improvement, being equipped with insulation sleeve between the ignitor and plug one, the insulation sleeve is wrapped in outside ignitor
Surface.
As an improvement, being respectively equipped with sealing ring between the plug one, plug two and closed burner ontology.
As an improvement, being connected through a screw thread the pressure sensor on the inner wall of the plug two, it is provided on plug two
One through-hole is connected with the temperature sensor in the through-hole；
When the pressure sensor is for measuring propellant charge burning, the pressure generated in closed burner, the temperature
Degree sensor is used to measure flame temperature when propellant combustion.
As an improvement, the data acquisition process unit passes through cable and the pressure sensor, temperature sensor respectively
Connection；
The data acquisition process unit is for acquiring pressure sensor, the pressure of temperature sensor measurement, temperature parameter.
As an improvement, the clamping device is arranged in closed burner body interior middle position, the clamping device
Bottom is equipped with bracket, and outside is equipped with the fence for preventing propellant charge from toppling over.
In addition, being tested using described in any of the above-described for solid propellant combustion rate/combustion temperature the present invention also provides a kind of
The test method of device, comprising the following steps:
1) it is coated using side of the PMMA acetone soln to propellant charge, applies one layer of thin epoxy resin after dry,
The geometric dimension parameter of propellant charge is measured, then propellant charge is placed in clamping device；
2) ignitor, relief valve are connect with plug one respectively, then by pressure sensor, temperature sensor respectively with
Plug two connects, then plug one, plug two and the sealing of closed burner ontology are installed, and ensures that relief valve is in and close shape
State；
3) starting ignition electrode ignites propellant charge, and propellant combustion generates bulk gas, cavity in closed burner
Internal pressure rises, and triggering pressure sensor acquires pressure signal, and temperature sensor acquires propellant flame temperature signal；
4) propellant combustion finishes, off-test, after 5-8 minutes, opens relief valve, the gas inside closed burner is discharged
Body product unloads lower end cap one, removes the remaining solid residue of burner internal；
5) data processing；
A) respectively read propellant combustion during closed burner pressure-time and Temperature-time data and curves；
B) pressure of closed burner, the flame temperature of propellant, propellant grain density meet following relationship:
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
Burn rate, 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 column, w are that the meat of combustion of propellant is thick；
Pressure-the time graph obtained using numerical computation method, Binding experiment data is solved by formula (1)-(4)
Burn rate-pressure curve, can be completed data processing.
Compared with prior art, the beneficial effects of the present invention are:
1) solid propellant combustion rate provided by the invention/combustion temperature test device and its test method are used, it is public from calculating
As can be seen that the combustion temperature Tf of the propellant in burn rate and closed burner of the invention has relationship, by the combustion of propellant in formula (1)
Temperature is included in Burning rate calculation as input parameter, and eliminating traditional heat leakage corrected Calculation bring influences.Therefore, can have
Effect solves conventional containment burner method under low pressure because heat loss ratio is big, and is difficult to Burning rate testing caused by accurately estimating not
Quasi- problem, for the present invention without being modified by the modified method of heat leakage to ignition temperature, survey calculation is accurate.
2) present invention passes through and once tests, and can be obtained burn rate-pressure data in wider pressure limit and fires warm data,
The data obtained can be used for evaluating the combustibility of propellant in solid propellant propulsion formula extinguishing device, and it is low to judge whether the side of being measured meets
The requirement of combustion temperature, high burn rate.Data are reliable, convenience of calculation.
Detailed description of the invention
Fig. 1 is solid propellant combustion rate of the present invention/combustion temperature schematic structural diagram of testing device；
Fig. 2 is the structural schematic diagram of clamping device in the present invention；
Fig. 3 is the structural schematic diagram of solid propellant grain in the present invention；
Fig. 4 is pressure-time graph of the invention；
Fig. 5 is burn rate-pressure curve of the invention；
In figure: 1, closed burner ontology, 2, plug one, 3, plug two, 4, sealing ring, 5, ignitor, 6, insulation sleeve,
7, relief valve, 8, pressure sensor, 9, temperature sensor, 10, clamping device, 11, fence, 12, propellant charge, 13, data
Acquisition process unit.
Specific embodiment
Following embodiments are further explanations for the content of present invention using as the explaination to the technology of the present invention content, but
Substantive content of the invention is not limited in described in following embodiments, those skilled in the art can with and should know appoint
What simple change or replacement based on true spirit should belong to protection scope of the presently claimed invention.
As shown in Figure 1 and Figure 2, a kind of for solid propellant combustion rate/combustion temperature test device, including closed burner sheet
Body 1, the plug 1 that 1 both ends of closed burner ontology are set and plug 23,5 and of ignitor being arranged on plug 1
Relief valve 7 and the temperature sensor 9 and pressure sensor 8 being arranged on plug 23；
The closed burner ontology 1 is cylindrical cavity cell structure, is fabricated using super-pressure high strength steel, and volume is
70ml, highest pressure-bearing 100MPa, one end of closed burner ontology 1 are connected through a screw thread plug 1, and the other end is connected by screw thread
Connect plug 23, wherein preferably connect using trapezoidal thread, clamping device 10, the folder are equipped in closed burner ontology 1
It holds and is fixed with propellant charge 12 in device 10, be additionally provided with data acquisition process unit 13 on the outside of the closed burner ontology 1,
The data acquisition process unit 13 is connect with the pressure sensor 8, temperature sensor 9 respectively.
As the improvement of embodiment, the ignitor 5 is threadedly attached on plug 1, and the relief valve 7 passes through
It is threaded on plug 1.Easy to connect, disassembly is simple, and the exhaust gas after being used to test by relief valve 7 discharges.
As the improvement of embodiment, insulation sleeve 6 is equipped between the ignitor 5 and plug 1, the insulation sleeve 6 wraps up
In 5 outer surface of ignitor.Ignitor 5 is lighted a fire using igniter wire formula nichrome wire, and match board head, igniter wire use nichrome,
Diameter takes 0.05mm, and the initial firing current of igniter is 8A.
As the improvement of embodiment, sealing ring is respectively equipped between the plug 1, plug 23 and closed burner ontology 1
4, it is conducive to disassembly, cleaning and pressure-bearing.
As the improvement of embodiment, it has been connected through a screw thread the pressure sensor 8 on the inner wall of the plug 23, has blocked up
It is provided with a through-hole on first 23, the temperature sensor 9 is connected in the through-hole；
When the pressure sensor 8 burns for measuring propellant charge 12, the pressure generated in closed burner is described
Temperature sensor 9 is used to measure flame temperature when propellant combustion.Pressure sensor 8 is CY400 high-frequency pressure, pressure drag formula weight
Journey 20MPa, the natural frequency of vibration are greater than 400kHz.Since there are the feature of strong transient state, inner wall temperatures for propellant combustion in burner
Measurement uses the temperature sensor 9 of the package thickness minimum (H=0.298mm) specially designed, and when installation, temperature sensor 9
End be located at the top of propellant charge 12, the thermocouple wire end of temperature sensor 9 and big envelope are the form of face contact, can
Meet the acquisition feature of high dynamic.
As the improvement of embodiment, the data acquisition process unit 13 respectively by cable and the pressure sensor 8,
Temperature sensor 9 connects；
Pressure, the temperature that the data acquisition process unit 13 is used to acquire pressure sensor 8, temperature sensor 9 measures
Parameter.The data acquisition process unit 13 uses TST6250 high-speed data recording instrument, data actuation sample rate 20Msps.
As the improvement of embodiment, the clamping device 10 setting is described in 1 bosom position of closed burner ontology
The bottom of clamping device 10 is equipped with bracket, and outside is equipped with the fence 11 for preventing propellant charge 12 from toppling over.The bottom of use
The contact area of bracket and propellant charge 12 is small, so that propellant charge 12, which meets, returns combustion law.
When being measured using above-mentioned apparatus, specifically includes the following steps:
1) it in this embodiment, is coated using side of the PMMA acetone soln to propellant charge 12, is applied after dry
One layer of thin epoxy resin；Then powder column quality 12.1g, height 17.2mm, diameter 25.5mm after processing are measured again, then by propellant
Powder column 12 is placed in clamping device 10；
2) ignitor 5, relief valve 7 are connect with plug 1 respectively, then by pressure sensor 8, temperature sensor 9
It connect, then plug 1, plug 23 and the sealing of closed burner ontology 1 is installed, and ensure relief valve 7 with plug 23 respectively
It is in close state；
3) before testing, log-on data acquisition process unit 13, setting signal triggering mode is internal trigger；
4) when testing, starting ignition electrode 5 ignites propellant charge 12, and propellant combustion generates bulk gas, constant volume combustion
Inside cavity pressure rises in burner, and triggering pressure sensor 8 acquires pressure signal, and temperature sensor 9 acquires propellant flame
Temperature signal, 13 synchronous acquisition pressure signal of data acquisition process unit and temperature signal, and according to collected pressure, temperature
Signal, data acquisition process unit 13 draw out pressure-time, Temperature-time data and curves；
4) propellant combustion finishes, off-test, after 5-8 minutes, opens relief valve 7, is discharged inside closed burner
Gaseous product unloads lower end cap 1, removes the remaining solid residue of burner internal；
5) data processing；
1) it can be obtained according to The Ideal-Gas Equation,
2) it can be obtained according to law of conservation of energy,
3) above-mentioned two formula, available following formula are combined
4) following parameter: the volume of V- closed burner, the burn rate of r (p)-propellant, T is inputtedfPropellant flame temperature
Degree, cpLevel pressure thermal capacitance, cvConstant volume thermal capacitance, R- ideal gas constant, ρpThe density of propellant charge.It is pressure change rate
(derivative of pressure versus time),It is heat gradient,It is gas constant change rate,Constant volume thermal capacitance change rate.
" gaseous mass generating rate-time " data can be obtained by " pressure versus time " data.Wherein, in order to keep away
Exempt from the influence of irregular combustion bring, the starting point of resulting " pressure versus time " data of pressure sensor proceeds as follows choosing
It takes:
Starting point is selected in the point for having fired mass percent for 15%, and terminal is selected at (dp/dt)maxPlace, i.e. Pressure versus Time
Derivative maximum value point.
5) since the burning of propellant follows recurrence combustion law, the propellant charge surface area that has burnt off with
Firing thickness, there are following relationships:
Sw=2 π (r-w)2+2π(r-w)(h-2w)
6) the propellant charge surface area that has burnt off has fired thickness and burn rate and there is following relationship again:
W (t)=∫ r (p) dt
7) combine above-mentioned two formula can be derived from by " gaseous mass generating rate-time " relationship " burn rate-when
Between " relationship, and then " burn rate-pressure " relationship is obtained, to complete Data Processing in Experiment.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all in essence of the invention
Made any modification, equivalent replacement or improvement etc., should all be included in the protection scope of the present invention within mind and principle.
Claims (6)
1. a kind of using for solid propellant combustion rate/combustion temperature test device test method, which is characterized in that including following step
It is rapid:
1) side of propellant charge (12) is coated using PMMA acetone soln, applies one layer of thin epoxy resin after dry,
The geometric dimension parameter of propellant charge (12) is measured, then propellant charge (12) is placed in clamping device (10)；
2) ignitor (5), relief valve (7) are connect with plug one (2) respectively, then by pressure sensor (8), temperature sensing
Device (9) is connect with plug two (3) respectively, then plug one (2), plug two (3) and closed burner ontology (1) sealing are installed,
And ensure that relief valve (7) is in close state；
3) starting ignition electrode (5) ignites propellant charge (12), and propellant combustion generates bulk gas, closed burner lumen
Body internal pressure rises, and triggering pressure sensor (8) acquires pressure signal, and temperature sensor (9) acquires propellant flame temperature
Signal；
4) propellant combustion finishes, off-test, after 5-8 minutes, opens relief valve (7), the gas inside closed burner is discharged
Body product unloads lower end cap one (2), removes the remaining solid residue of burner internal；
5) data processing；
A) respectively read propellant combustion during closed burner pressure-time and Temperature-time data and curves；
B) pressure of closed burner, the flame temperature of propellant, propellant grain density meet following relationship:
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 combustion meat of propellant is thick；M is the gaseous mass in closed burner, P·It is pressure change rate,It is heat
Change rate,It is gas constant change rate,Constant volume thermal capacitance change rate, T are the gas temperature in closed burner, and r is to promote
The initial radium of agent powder column cross section, h are the elemental height of propellant charge, SwFor the spent surface area of propellant charge,
Pressure-the time graph obtained using numerical computation method, Binding experiment data solves burn rate-by formula (1)-(4)
Data processing can be completed in pressure curve；
Solid propellant combustion rate/combustion temperature the test device, including closed burner ontology (1), setting of being used for is in constant volume combustion
The plug one (2) and plug two (3) at burner ontology (1) both ends, the ignitor (5) and relief valve being arranged on plug one (2)
(7) and temperature sensor (9) and pressure sensor (8) on plug two (3) be set；
The closed burner ontology (1) is cylindrical cavity cell structure, and one end of closed burner ontology (1) is connected through a screw thread
Plug one (2), the other end are connected through a screw thread plug two (3), are equipped with clamping device (10) in closed burner ontology (1), institute
It states and is fixed with propellant charge (12) in clamping device (10), data acquisition is additionally provided on the outside of the closed burner ontology (1)
Processing unit (13), the data acquisition process unit (13) connect with the pressure sensor (8), temperature sensor (9) respectively
It connects；
It has been connected through a screw thread on the inner wall of the plug two (3) pressure sensor (8), it is logical that one is provided on plug two (3)
Hole is connected with the temperature sensor (9) in the through-hole；
When the pressure sensor (8) is for measuring propellant charge (12) burning, the pressure generated in closed burner is described
Temperature sensor (9) is used to measure flame temperature when propellant combustion.
2. a kind of use according to claim 1 is used for solid propellant combustion rate/combustion temperature test device test method,
It is characterized in that, the ignitor (5) is threadedly attached on plug one (2), and the relief valve (7) is threadedly attached in
On plug one (2).
3. a kind of use according to claim 2 is used for solid propellant combustion rate/combustion temperature test device test method,
It is characterized in that, be equipped with insulation sleeve (6) between the ignitor (5) and plug one (2), the insulation sleeve (6) is wrapped in ignition power
Pole (5) outer surface.
4. a kind of use according to claim 1 is used for solid propellant combustion rate/combustion temperature test device test method,
It is characterized in that, is respectively equipped with sealing ring (4) between the plug one (2), plug two (3) and closed burner ontology (1).
5. a kind of use according to claim 1 is used for solid propellant combustion rate/combustion temperature test device test method,
It is characterized in that, the data acquisition process unit (13) passes through cable and the pressure sensor (8), temperature sensor respectively
(9) it connects；
The data acquisition process unit (13) is used to acquire pressure, the temperature of pressure sensor (8), temperature sensor (9) measurement
Spend parameter.
6. a kind of use according to claim 1 is used for solid propellant combustion rate/combustion temperature test device test method,
It is characterized in that, the clamping device (10) is arranged in closed burner ontology (1) bosom position, the clamping device (10)
Bottom be equipped with bracket, outside is equipped with fence (11) for preventing propellant charge (12) from toppling over.
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