CN203365362U - Combustion chamber device used for testing dynamic combustion performance of solid propellant by utilizing multiple thermocouples - Google Patents

Abstract

The utility model relates to a combustion chamber device used for testing dynamic combustion performance of a solid propellant by utilizing multiple thermocouples. The combustion chamber device is characterized by comprising a combustion chamber and a combustion support, wherein the combustion support and the combustion chamber are in rotary seal connection through a threaded port; the combustion support is used for fixing solid propellant medicinal strips in the combustion chamber, and the solid propellant medicinal strips are fixed in the height direction of the combustion chamber in parallel; and the temperature-measuring thermocouples distributed at intervals are arranged on one side of each solid propellant medicinal strip, and the temperature-measuring thermocouples distributed at intervals are electrically connected with a thermocouple signal detection circuit. Compared with a frequently-used combustion speed test system, the system shortens the development and production period of the propellant, reduces consumption of raw materials, reduces manual operation and saves the cost.

Description

The combusting room device of solid propellant multiple thermocouple Dynamic Burning performance test

Technical field

The utility model relates to a kind of Dynamic Burning of Solid Propellants Performance Test System, particularly the combusting room device of solid propellant multiple thermocouple Dynamic Burning performance test.

Background technology

In the research and production of solid propellant, and the solid engines development initial stage, the technical parameters such as propellant burning rate and burning rate pressure exponent, temperature sensitivity of burning rate, directly affect internal ballistics attributes, flying speed and the steady operation of rocket engine.The existing fast Characteristics Detection of static combustion of measuring mainly adopts nitrogen target collimation method or underwateracoustic shooting method.These two kinds of methods are all the combustion speed of test solid propellant sample medicinal strip under constant pressure and temperature conditions, need to carry out respectively the fast test of static combustion to some pressure points, show that the burning rate pressure exponent in particular range needs the single-point combustion speed test repeated for tens of times, testing efficiency is lower, also more to the demand of sample.

It is motor method that the solid of comparative maturity is pushed dynamic combustion speed method of testing, use simulated engine or model engine to be arranged on static test bay, igniting test its motor power curve, pressure curve and the propellant working time, calculate the combustion parameter of propellant, carry out the true or approximate real burning performance that characterizes propellant.But the method propellant consumption is large, cost is too high, and the tester is many, and also there is test safety hidden danger in the test process complexity.

Summary of the invention

The purpose of this utility model be to provide a kind of simply, efficiently, the combusting room device of solid propellant multiple thermocouple Dynamic Burning performance test efficiently, to shorten the development and production cycle of solid propellant.

The purpose of this utility model is to realize like this, the combusting room device of solid propellant multiple thermocouple Dynamic Burning performance test, it is characterized in that: comprising: firing chamber and combustion supporter, described combustion supporter is connected by screw thread mouth rotary seal with firing chamber, combustion supporter fixed solid propellant medicinal strip in firing chamber, the parallel firing chamber short transverse that is fixed on of solid propellant medicinal strip; In solid propellant medicinal strip one side, temperature thermocouple spaced apart is arranged, each temperature thermocouple spaced apart is electrically connected to the thermocouple signal testing circuit.

The locular wall of described firing chamber has around pipeline, connects thermostatic bath; There is the mounting hole of pore and temperature pressure transducer firing chamber, by pore and mounting hole, is connected respectively gas circuit unit and temperature pressure transducer.

Described combustion supporter is provided with location grid, heat-conducting metal silk and the ignition lead of the thermopair that is located by connecting.

There is crucible the lower end of described combustion supporter.

Described pore place is provided with screen pack.

Described combustion supporter is Metallic rod, and the output terminal of ignition lead and thermopair is connected to measurement and control unit by high temperature resistant cable.

The utility model compared with prior art, has the following advantages:

(1) adopt multiple thermocouple to fire fast test macro, both can carry out the Dynamic Burning performance test, also can carry out static test, two kinds of metering system easy switchings.Obtain firing the variation relation of speed-pressure and combustion speed-temperature, calculate burning rate pressure exponent and temperature sensitivity of burning rate.Low dose of test just can be estimated the burning performance of tested propellant in corresponding pressure/temperature variation range, is highly suitable for, in the propellant production run, every a collection of product is carried out to the work such as quick performance detection, quality control.

(2) with combustion speed test macro commonly used, compare, this system has shortened the development and production cycle of propellant, has reduced raw materials consumption, has reduced manually-operated, has saved cost.

The accompanying drawing explanation

Below in conjunction with the embodiment accompanying drawing, the utility model is described in further detail:

Fig. 1 system architecture schematic diagram;

Fig. 2 the utility model embodiment schematic flow sheet;

Fig. 3 is burning testing process flow diagram;

Fig. 4 is the static test workflow diagram.

Fig. 5 is the medicinal strip schematic diagram

In Fig. 1,1, gas cylinder; 2, buffering gas cylinder; 3, high pressure admission valve; 4, buffering gas admittance valve; 5, vent valve; 6, thermostatic bath; 7, firing chamber; 8, temperature pressure transducer; 9, combustion supporter; 10, solid propellant medicinal strip; 11, thermopair; 12, heat-conducting metal silk; 13, location grid; 14, crucible; 15, ignition lead; 16, valve controling circuit; 17, firing circuit; 18, thermocouple signal testing circuit; 19, filter amplification circuit; 20, treatment circuit; 21, A/D convertor circuit; 22, telecommunication circuit; 23, main frame; 24, display/printer; 25, cable; 26, pipeline; A, aggregation of data processing unit; B, measurement and control unit; C, distribution temperature conditioning unit; D, combustion chamber unit.

Embodiment

As shown in Figure 1, the combusting room device of solid propellant multiple thermocouple Dynamic Burning performance test, comprise: firing chamber 7 and combustion supporter 9, described combustion supporter 9 is connected by screw thread mouth rotary seal with firing chamber 7, combustion supporter 9 fixed solid propellant medicinal strips 10 in firing chamber 7, parallel firing chamber 7 short transverses that are fixed on of solid propellant medicinal strip 10; In solid propellant medicinal strip 10 1 sides, temperature thermocouple spaced apart 11 is arranged, each temperature thermocouple spaced apart 11 is electrically connected to thermocouple signal testing circuit 18.

The locular wall of firing chamber 7 has around pipeline, connects thermostatic bath 6; There is the mounting hole of pore and temperature pressure transducer 8 firing chamber 7, by pore and mounting hole, is connected respectively gas circuit unit and temperature pressure transducer 8.

Combustion supporter is provided with location grid 13, the heat-conducting metal silk 12 of the thermopair 11 that is located by connecting and ignition lead 15.

There is crucible 14 lower end of combustion supporter 9, and crucible 14 is for support solid propellant medicinal strip 10 and collect comburant;

Described pore place is provided with screen pack.

Described combustion supporter 9 is Metallic rod, plays and supports and the ground wire effect, and ignition lead 15 is connected to measurement and control unit B with the output terminal of thermopair 11 by high temperature resistant cable.

Firing chamber 7 and combustion supporter 9 form combustion chamber unit D.

Distribution temperature conditioning unit C, test required pressure/temperature environment for firing chamber is provided.The circulation line of thermostatic bath 6 is looped around chamber wall, and the circulation fluid temperature by adjustable constant-temperature is with the temperature of control combustion chamber 7.The gas circuit unit comprises pipeline, gas cylinder 1, buffering gas cylinder 2, high pressure admission valve 3, buffering gas admittance valve 4, vent valve 5, supercharge pump and pressure gauge, makes firing chamber form constant voltage or closed environment.

Measurement and control unit B, firing circuit 17 is converted to ignitable electric current by ignition lead 15 by ignition signal, ignition lead 15 draws burning solid propellant medicinal strip 10 by the nichrome wire connected, valve controling circuit 16 is controlled high pressure admission valve 3, buffering gas admittance valve 4, vent valve 5, by gas cylinder 1, buffering gas cylinder 2, regulates chamber pressure.In solid propellant medicinal strip 10 1 sides, temperature thermocouple spaced apart 11 is arranged, each temperature thermocouple spaced apart 11 is electrically connected to thermocouple signal testing circuit 18, thermocouple signal testing circuit 18 is input to the temperature signal of thermopair the interface end for the treatment of circuit 20, process by treatment circuit 20, obtain respectively the temperature variation of each thermopair 11 in solid propellant medicinal strip 10 combustion processes after ignition order; Be sent to the main frame 23 of aggregation of data processing unit A by telecommunication circuit 22 by the temperature variation signal by diverse location in solid propellant medicinal strip 10 combustion processes, by main frame 23, processed, main frame 23 is controlled display/printer 24 and is provided temperature field time, location map.Simultaneously, temperature pressure transducer 8 in firing chamber 7 carries out filter amplifying processing by the temperature pressure electric signal in firing chamber 7 by filter amplification circuit 19, then obtain temperature value, the pressure values in firing chamber 7 by treatment circuit 20 or A/D convertor circuit 21, temperature value, pressure values in firing chamber 7 are sent to aggregation of data processing unit A and are processed.

Data processing unit A, comprise a control, and the control support moves as lower module:

System module, system module carry out the setting of initial testing parameter and test data collection parameter;

Control module, control module are carried out pressure control, temperature is controlled and the IGNITION CONTROL operation;

Measurement module, measurement module are preserved for pressure sampling, temperature sampling, waveform demonstration and drafting, data;

Data processing module, data processing module carries out the distinguishing validity of test data, and the indoor pressure of analytic combustion, temperature real-time change, in conjunction with the multiple thermocouple technology, obtain the combustion law of medicinal strip, calculating is fired in real time speed, is calculated Pressure Exponent and temperature-sensitivity coefficient and printed report list;

Data management module, data management module carries out data storage, retrieval and derivation operation.

Fig. 2 is Dynamic Burning performance test workflow of the present utility model, and coupling system structural representation Fig. 1 illustrates its course of work.

As shown in Figure 2, step 200, open the test control, is adjusted into the dynamic test mode, in interface input parameters, determines and preserve;

Step 201, open buffering gas admittance valve 4;

Step 202, detect chamber pressure;

Step 203, whether chamber pressure reaches test request, is to continue step 205; , carry out step 204;

Step 204, chamber pressure is greater than test request, is, continues step 206; , do not continue step 207;

Step 205, close the buffering air intake valve, igniting;

Step 206, open vent valve 5 and carry out exhaust, returns to step 202;

Step 207, open high pressure admission valve 3, carries out air inlet, returns to step 202;

Step 208, system take fire solid propellant medicinal strip 10 combustion processes and detection;

Step 209, combustion process and detection finish.

Fig. 3 is take fire solid propellant medicinal strip 10 combustion processes and detecting step flow process of system.

As shown in Figure 3, described step 208, take fire solid propellant medicinal strip 10 combustion processes and detection of system comprises the steps:

Step 301, measurement and control unit B receives order, and firing circuit 17 produces the electric current of the solid propellant medicinal strip burning of igniting, and makes ignition wire 15 heating pilot combustion solid propellant medicinal strips 10;

Step 302, the treatment circuit 20 of measurement and control unit B starts timing;

Step 303, thermocouple signal testing circuit 18 is input to the temperature signal of thermopair the interface end for the treatment of circuit 20, process by treatment circuit 20, obtain respectively the temperature variation of each thermopair 11 in solid propellant medicinal strip 10 combustion processes after ignition order;

Step 304, the temperature pressure transducer 8 in firing chamber 7 carries out filter amplifying processing by the temperature pressure electric signal in firing chamber 7 by filter amplification circuit 19, then by treatment circuit 20 or A/D convertor circuit 21, obtains temperature value, the pressure values in firing chamber 7;

Step 305, be sent to the data of step 303 and step 304 main frame 23 of aggregation of data processing unit A by telecommunication circuit 22;

Step 306, by last thermocouple location temperature identification, whether perfect combustion of burning solid propellant medicinal strip 10 is complete, does not have, and returns to step 303; To step 307;

Step 307, main frame 23, by the spacing of the time interval and location grid 13, calculates the dynamic combustion speed at fore pressure and temperature; Obtain combustion speed-pressure curve, burning rate pressure exponent and temperature sensitivity of burning rate in test specification;

Step 308, close vent valve 5, buffering gas admittance valve 4, high pressure admission valve 3;

Step 309, the result store that data are processed is to the industrial computer hard disk, and demonstration or print result.

After in the utility model, measurement and control unit B receives order, the data that detect in burning solid propellant medicinal strip 10 combustion processes can be sent to the main frame 23 of aggregation of data processing unit A in real time by telecommunication circuit 22, also can the burning solid propellant medicinal strip after 10 burnings finish, be sent to the main frame 23 of aggregation of data processing unit A, by main frame 23 aftertreatment of being burnt.

After in the utility model, measurement and control unit B receives order, timing can be according to causing that thermopair 11 Temperature jumps start timing.

In the utility model, system module carries out the setting of initial testing parameter and test data collection parameter, generally before measuring igniting, carry out, be mainly submitted sample batch, the relevant information settings such as model, length, tester, censorship date, be convenient to late time data and process and generate report; Control module is carried out pressure control, temperature is controlled and the IGNITION CONTROL operation, and software, by the temperature, the pressure transducer Real-Time Monitoring combustion chamber environment that are arranged on firing chamber, is controlled temperature and pressure by thermostatic bath and air-operated solenoid valve; Measurement module is preserved for pressure sampling, temperature sampling, waveform demonstration and drafting, data; Distinguishing validity, Burning rate calculation, Pressure Exponent and temperature-sensitivity coefficient that data processing module carries out test data calculate and the printed report list; Data management module carries out data storage, retrieval and derivation operation.

The utility model can complete Dynamic Burning performance test and static combustion performance test, as shown in Figure 4.

Step 400, open the test control, is adjusted into static test mode, in interface input parameters, determines and preserve;

Step 401, detect chamber temperature;

Step 403, whether chamber temperature reaches probe temperature, is, continues step 404; Not, carry out step 402, regulate chamber temperature, approach probe temperature, return to step 401;

Step 404, open buffering gas admittance valve 4;

Step 405, detect chamber pressure;

Step 406, whether chamber pressure reaches test request, is, continues step 408; , carry out step 407;

Step 407, chamber pressure is greater than test request, is, continues step 409; , do not continue step 410;

Step 408, open slow gas admittance valve, sends ignition order, to step 411;

Step 409, open vent valve 5 and carry out exhaust, returns to step 405;

Step 410, open high pressure admission valve 3, carries out air inlet, returns to step 405;

Step 411, system take fire solid propellant medicinal strip 10 combustion processes and detection;

Step 412, combustion process and detection finish.

Debugging and the course of work that the utility model dynamic test is total are: test starts, and fixed solid propellant medicinal strip 10 between combustion supporter 9 and crucible 14 is arranged heat-conducting metal silk 12, and it is contacted with solid propellant medicinal strip 10; Connect thermopair 11 and heat conductive filament 12; Combustion supporter 9 inserts firing chamber 7 and rotation makes its sealing.Open control, input parameters arranging under interface, determine and preserve.By the viewing area, firing chamber of control window or the pilot lamp of control box, the break-make of observation point live wire 15, thermopair 11, by detection signal identify whether have obstructed, if you have questions, stop the test, the firing chamber pressure release, open combustion supporter and reinstall.Close all valves of thermostatic bath 6, the circulation fluid of the circulation line of draining.Open gas admittance valve, make combustion chamber pressure reach test request.Close trimmer valve 4, make firing chamber form confined space.Control sends ignition order.

Measurement and control unit B receives order, and firing circuit 17 produces the electric current of solid propellant medicinal strip 10 burnings of igniting, and makes ignition wire 15 heatings draw burning solid propellant medicinal strip 10; Along with combustion face moves down, successively by each hot conducting filament 12, the temperature signal of thermopair 11 is undergone mutation, the jump signal of each thermopair is delivered to treatment circuit 18 through high temperature resistant cable 25, by treatment circuit 18, the digital signal obtained is delivered to industrial computer 23 by telecommunication circuit 22, industrial computer 23 pairs of temperature signals that obtain, pressure signal, interval time and parameters arrange the parameter of interface input and carry out computing.The medicinal strip parameter as shown in Figure 5.

In solid propellant medicinal strip 10 combustion processes, the burning pressure of inside, firing chamber when t can be expressed as following relational expression:

P(t)·V(t)=N(t)·R·T _V（t） (1)

In formula, P (t): the pressure that in firing chamber, t records constantly; V (t): t is the free volume in firing chamber constantly; N (t): t is the interior combustion gas total mole number of burner constantly; R: universal gas constant; T _v(t): t is chamber temperature constantly.

Calculate and obtain t solid propellant medicinal strip 10 spent length l (t) constantly according to the free volume V in firing chamber (t):

$l\left(t\right)=\frac{K_1\·P\left(t\right)-K_2\·T\left(t\right)}{K_3\·P\left(t\right)-T\left(t\right)}---\left(2\right)$

In Fig. 5, △ L _a: medicinal strip top is to the distance of ignition lead; P ₀| T ₀: combustion face is during to the ignition lead place, the pressure of airtight firing chamber and temperature value; △ L ₀: ignition lead is to the distance of target line a1; △ L ₁～△ L ₅: the target distance between centers of tracks; P ₁| T ₁～P ₆| T ₆: combustion face is during to the target line a1 of thermopair～target line a6 place, the pressure of airtight firing chamber and temperature value; △ L _b: the target line a6 of thermopair is to the distance of medicinal strip end; P ₇| T ₇: medicinal strip burns when complete, the pressure of airtight firing chamber and temperature, K ₁, K ₂, K ₃it is constant.

$\left\{\begin{array}{c}\mathrm{\Δ}{L}_a+\mathrm{\Δ}{L}_0=\frac{K_1\·P\left(t_1\right)-K_2\·T\left(t_1\right)}{K_3\·P\left(t_1\right)-T\left(t_1\right)}\\ \mathrm{\Δ}{L}_a+\mathrm{\Δ}{L}_0+\mathrm{\Δ}{L}_1=\frac{K_1\·P\left(t_2\right)-K_2\·T\left(t_2\right)}{K_3\·P\left(t_2\right)-T\left(t_2\right)}\\ \mathrm{\Δ}{L}_a+\mathrm{\Δ}{L}_0+\mathrm{\Δ}{L}_1+\mathrm{\Δ}{L}_2=\frac{K_1\·P\left(t_3\right)-K_2\·T\left(t_3\right)}{K_3\·P\left(t_3\right)-T\left(t_3\right)}\\ \mathrm{\Δ}{L}_a+\mathrm{\Δ}{L}_0+\mathrm{\Δ}{L}_1+\mathrm{\Δ}{L}_2+\mathrm{\Δ}{L}_3=\frac{K_1\·P\left(t_4\right)-K_2\·T\left(t_4\right)}{K_3\·P\left(t_4\right)-T\left(t_4\right)}\\ \mathrm{\Δ}{L}_a+\mathrm{\Δ}{L}_0+\mathrm{\Δ}{L}_1+\mathrm{\Δ}{L}_2+\mathrm{\Δ}{L}_3+\mathrm{\Δ}{L}_4=\frac{K_1\·P\left(t_5\right)-K_2\·T\left(t_5\right)}{K_3\·P\left(t_5\right)-T\left(t_5\right)}\\ \mathrm{\Δ}{L}_a+\mathrm{\Δ}{L}_0+\mathrm{\Δ}{L}_1+\mathrm{\Δ}{L}_2+\mathrm{\Δ}{L}_3+\mathrm{\Δ}{L}_4+\mathrm{\Δ}{L}_5=\frac{K_1\·P\left(t_6\right)-K_2\·T\left(t_6\right)}{K_3\·P\left(t_6\right)-T\left(t_6\right)}\end{array}\right.---\left(3\right)$

Solving equations (3), segmentation draws the K value.

Dynamically combustion is fast in real time:

$\begin{array}{c}r\left(t\right)=\frac{\mathrm{dl}\left(t\right)}{\mathrm{dt}}=\frac{K_1{P}^{\′}\left(t\right)-K_2{T}^{\′}\left(t\right)}{K_{3}P\left(t\right)-T\left(t\right)}+\frac{(K_3{P}^{\′}\left(t\right)-T^{\′}\left(t\right))(K_{1}P\left(t\right)-K_{2}T\left(t\right))}{{(K_{3}P\left(t\right)-T\left(t\right))}^2}\\ =\frac{(K_1{P}^{\′}\left(t\right)-K_2{T}^{\′}\left(t\right))(K_{3}P\left(t\right)-T\left(t\right))+(K_3{P}^{\′}\left(t\right)-T^{\′}\left(t\right))(K_{1}P\left(t\right)-K_{2}T\left(t\right))}{{(K_{3}P\left(t\right)-T\left(t\right))}^2}\end{array}---\left(4\right)$

Obtain testing dynamic combustion speed, Pressure Exponent, the temperature-sensitivity coefficient of medicinal strip.The result store that data are processed is to the industrial computer hard disk, and is presented on interface.

The parts that the present embodiment does not describe in detail and structure belong to well-known components and common structure or the conventional means of the industry, here not narration one by one.

Claims (6)

1. the combusting room device of solid propellant multiple thermocouple Dynamic Burning performance test, it is characterized in that: comprising: firing chamber (7) and combustion supporter (9), described combustion supporter (9) is connected by screw thread mouth rotary seal with firing chamber (7), combustion supporter (9) fixed solid propellant medicinal strip (10) in firing chamber (7), parallel firing chamber (7) short transverse that is fixed on of solid propellant medicinal strip (10); In solid propellant medicinal strip (10) one sides, temperature thermocouple spaced apart (11) is arranged, each temperature thermocouple spaced apart (11) is electrically connected to thermocouple signal testing circuit (18).

2. the combusting room device of solid propellant multiple thermocouple Dynamic Burning according to claim 1 performance test, it is characterized in that: the locular wall of described firing chamber (7) has around pipeline, connects thermostatic bath (6); There is the mounting hole of pore and temperature pressure transducer (8) firing chamber (7), by pore and mounting hole, is connected respectively gas circuit unit and temperature pressure transducer (8).

3. the combusting room device of solid propellant multiple thermocouple Dynamic Burning according to claim 1 performance test, it is characterized in that: described combustion supporter (9) is provided with location grid (13), the heat-conducting metal silk (12) of the thermopair that is located by connecting (11) and ignition lead (15).

4. the combusting room device of solid propellant multiple thermocouple Dynamic Burning according to claim 1 performance test, it is characterized in that: there is crucible (14) lower end of described combustion supporter (9).

5. the combusting room device of solid propellant multiple thermocouple Dynamic Burning according to claim 2 performance test, it is characterized in that: described pore place is provided with screen pack.

6. the combusting room device of solid propellant multiple thermocouple Dynamic Burning according to claim 3 performance test, it is characterized in that: described combustion supporter (9) is Metallic rod, and ignition lead (15) is connected to measurement and control unit (B) with the output terminal of thermopair (11) by high temperature resistant cable.

Images