CN108426976B - Propellant powder charging ignition comprehensive simultaneity evaluation method - Google Patents

Propellant powder charging ignition comprehensive simultaneity evaluation method Download PDF

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CN108426976B
CN108426976B CN201810064087.7A CN201810064087A CN108426976B CN 108426976 B CN108426976 B CN 108426976B CN 201810064087 A CN201810064087 A CN 201810064087A CN 108426976 B CN108426976 B CN 108426976B
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sensor
pressure
ignition
simultaneity
test
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CN108426976A (en
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赵宝明
赵宏立
靳建伟
张衡
何昌辉
张邹邹
杨丽侠
辛凯迪
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Xian Modern Chemistry Research Institute
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    • 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

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Abstract

The invention discloses a method for evaluating the comprehensive simultaneity of propellant powder charging ignition.A sensor bracket for fixing a sensor is manufactured according to the shape and the charging structure of a powder chamber, the sensor is fixed on the sensor bracket, a first stage of the sensor is welded on the sensor bracket, put into the powder chamber and tightly contacted with the powder chamber to be used as a first stage of a signal wire, and the other lead of the sensor is fixedly connected with an insulated sealing electrode on a plug of the powder chamber to form the other stage of the signal wire; loading the propellant charge into a chamber; selecting and installing pressure relief fragments according to the extrusion pressure of the shot and the theoretical pressure of the full-scale ignition of the charged powder; and igniting and testing, and analyzing the test signal to evaluate the overall simultaneity of ignition of the propellant charge. The invention effectively solves the problem of testing the ignition effect (simultaneously and comprehensively) of the propellant charge, solves the key technical problem that a scientific and effective method is lacked in evaluating the ignition design of the propellant charge, and can provide a feasible test and evaluation means for the propellant charge design.

Description

Propellant powder charging ignition comprehensive simultaneity evaluation method
Technical Field
The invention belongs to the technical field of explosives and powders, and mainly relates to a propellant powder charging evaluation method.
Background
The barrel weapon is still the main equipment on the battlefield at present, and the barrel weapon generally relies on the propellant powder charge to provide the kinetic energy of transmission, utilizes the propellant powder charge design control powder charge energy release process, makes it accomplish the shooting task under the prerequisite of transmission safety, satisfies propellant powder charge and trajectory design index.
The complete and simultaneous ignition of the propellant powder charges means that after the propellant powder charges receive the energy generated by the combustion of the ignition system, the initial combustion surfaces of each propellant powder on each geometric point of the charge structure simultaneously achieve the ignition combustion condition and simultaneously combust. The complete simultaneous ignition of the propellant charges is the premise of the ballistic and charge design in the firearm, and the incomplete simultaneous ignition of the propellant charges is also the main inducement of abnormal ballistic phenomena (ballistic index reduction, pressure initial velocity abnormality and the like) and even hearth explosion. Therefore, testing the overall simultaneity of propellant charge ignition is of particular importance. The existing testing method for the comprehensive simultaneity of propellant powder charging ignition mainly comprises a multipoint pressure measurement method, a transparent ignition simulation device method and shooting in a shooting range.
The multipoint pressure measurement method is characterized in that a plurality of pressure sensors are axially arranged on the side wall of a powder charging chamber and used for monitoring the axial pressure change condition of the powder charging chamber in the point ignition process. Although the method can reflect the synchronism of the pressure of the medicine chamber in the axial growth and change, whether axial pressure fluctuation and pressure nonuniformity exist in the medicine chamber in the axial direction is judged according to the obtained change curve result of the pressure along with time. Pressure is the macroscopic expression of gunpowder gas molecules, and has high-speed fluidity under higher pressure, if the loading density of the powder loading chamber is not high, the axial pressure of the powder loading chamber is basically consistent, and the quality of the overall simultaneity of the ignition of the propellant powder loading is difficult to judge according to pressure signals.
The transparent ignition simulation device method is to observe the charge ignition combustion process by using a transparent combustion chamber and analyze the overall simultaneity of the charge ignition and the fire transfer of the propellant. However, the manufacturing material of the combustion chamber is only limited to transparent materials such as plastics or glass, so that the compression strength is limited, the testing method is not suitable for testing the comprehensive simultaneity of high-filling-density charging ignition, and the testing process has potential danger.
The shooting range is to judge the quality of the overall simultaneity of certain charging ignition by the repeated stability of chamber pressure and initial speed through a grouped artillery test. Generally, the difference between the chamber pressure and the initial velocity jump is not large, so that the charging has better overall ignition simultaneity and is suitable for the charging structure. The method has the following defects: 1) the ignition design effect of the charge is indirectly checked through the repeatability and consistency of the shooting of the barrel weapon, and whether the actual charge is completely and simultaneously ignited or not is not really mastered; 2) for large-caliber barrel weapons, the cost of the full-bullet shooting test is high; 3) the initial ignition performance is highly dangerous in the experiment, and a plurality of times of bore explosion accidents occur.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention provides a method capable of actually testing the simultaneity and comprehensiveness of the ignition of the propellant charge, and provides support and guarantee for the use safety and the trajectory stability of the propellant charge.
In order to solve the technical problems, the device adopted by the test method provided by the invention comprises a medicine chamber, a sensor support, a propellant powder charge, a left plug and a right plug, wherein the left plug and the right plug are used for connecting the medicine chamber to form a simulated barrel weapon medicine chamber environment and have the sealing and pressure-resistant functions of the medicine chamber, and the medicine chamber, the left plug and the right plug are matched and tightly connected in a threaded structure. The sensor is used for testing ignition signals of a plurality of test points of the explosive chamber and providing data for evaluating the comprehensive simultaneity of ignition of the explosive charge;
the method specifically comprises the following steps:
A. manufacturing a sensor bracket for fixing a sensor according to the geometric structure of a barrel weapon medicine chamber, and arranging a plurality of test points in the medicine chamber in the axial direction and the radial direction; on the premise that the sensor meets the measuring range, a high-temperature resistant miniaturized instrument is preferentially adopted. According to the design of the ignition structure, the radial direction is not necessarily at the axis, and the axial direction meets the geometric uniformity of the explosive chamber. The sensor comprises a thermocouple, a photoelectric sensor and a sound sensor; the axial test points of the medicine chamber are more than 3 groups, and the radial test points are more than 2 points.
B. Fixing a sensor at each test point of a sensor bracket; one of the two leads is connected to the sensor support to form a pole, and the sensor support is arranged in the medicine chamber and then is in close contact with the wall of the medicine chamber; and the other electrode is connected to the insulated sealing electrode of the left plug to form the other electrode of the sensor.
C. According to barrel weapon projectile penetration pressure PExtrusion processAnd the theoretical pressure P at which the charge is fully ignited simultaneouslyTheory of the inventionSelecting a pressure relief fragment with a corresponding specification, and loading the pressure relief fragment into a pressure relief fragment mechanism, wherein the pressure relief fragment mechanism is assembled on the right plug; maximum pressure resistance P of pressure relief fragmentCrushing deviceThe principle of pressure relief and fragment selection is as follows: pCrushing device＝PExtrusion process+PTheory of the invention(ii) a The adopted pressure relief fragment can resist pressure P when the pressure reaches the maximum pressureCrushing deviceThe pressure is released by breaking to ensure the completion of the experimentOn the premise of prolonging the service life of the medicine chamber and increasing the test safety.
Assembling an igniter on the left plug; the propellant charge is loaded into the chamber and all the parts are installed; c, operating an igniter, igniting the propellant charge, collecting signals by a sensor, and when the pressure reaches the maximum pressure resistance P of the pressure relief fragment in the step C in the testCrushing deviceWhen the pressure is released, the pressure releasing fragment is broken to release the pressure, and the test is finished; and evaluating the ignition overall simultaneity of the propellant charge through the change consistency of the axial signal and the radial signal.
The beneficial effects of the invention are shown in the following aspects:
in the invention, a plurality of test points are arranged in the explosive chamber, and the test points are geometrically and uniformly distributed, so that the omnibearing three-dimensional test of the ignition process is structurally ensured, and the comprehensive and simultaneous ignition effect of explosive charge can be judged and evaluated.
In the invention, the three-dimensional test points are arranged in the medicine chamber, then the medicine is loaded into the medicine chamber according to the medicine loading design, the sensor design hardly influences the ignition combustion process of the medicine, and the truth and reliability of the test result are ensured.
And thirdly, one lead of the sensor is connected to the sensor bracket to form a first stage, and the other lead is connected to the insulated sealing electrode of the left plug, so that the sealing and signal leading-out of the sensor in the medicine chamber are realized, and the complete test of the ignition process signal under the sealing condition is further ensured.
And (IV) the test method provided by the invention stops the test in a pressure relief and fragment rupture mode. On the basis of completing the test purpose and data acquisition, because the pressure of the explosive chamber does not reach the maximum combustion pressure of the explosive to be tested, the ablation of the device is reduced, the service life is prolonged, and in addition, the test pressure is greatly reduced, so that the test safety is improved.
Drawings
FIG. 1 is a schematic diagram of a test point sensor, charge and ignition layout of the invention, 1-an igniter, 2-an insulated sealing electrode, 3-a charge chamber, 4-a sensor, 5-a charge for propellant, 6-a pressure relief fragment mechanism, 7-a sensor bracket, 8-a left plug and 9-a right plug.
Fig. 2 is a schematic view of the connection of the sensor with the sensor holder and the chamber stopper.
FIG. 3 is a schematic view of an insulated electrode, 2-1 is a central enameled wire, and 2-2 is a pressing screw.
FIG. 4 is a schematic view of a pressure relief and rupture mechanism, where 6-1 is a pressure relief and rupture disk, 6-2 is a sealing metal washer, and 6-3 is a rupture disk pressing screw.
Detailed Description
The invention is described in further detail below with reference to the drawings and preferred embodiments.
As shown in FIG. 1, in the implementation of the preferred embodiment of the present invention, the device comprises a medicine chamber 3, a sensor 4, a propellant charge 5, a sensor support 7, a left plug 8 and a right plug 9. An igniter 1 and an insulated sealing electrode 2 connected with one of two-stage wiring of a sensor are assembled on a left plug 8, and a pressure relief fragment mechanism 6 is installed on a right plug 9.
The left plug 8 and the right plug 9 are used for connecting the medicine chamber 3 to form a simulated barrel weapon medicine chamber environment and have the functions of sealing and pressure resistance of the medicine chamber, the medicine chamber 3, the left plug 8 and the right plug 9 are all made of PCRNiMoV steel, and the left plug 8, the right plug 9, the medicine chamber 3, the left plug 8 and the right plug are matched and fastened and connected through thread structures. An igniter 1 is installed on the left plug 8, 23 # electric shock primer is selected for the igniter 1, 30V direct current is conducted to the two poles of the primer, the igniter 1 fires, and then the propellant powder charge 5 is ignited. The right plug 9 is provided with a pressure relief fragment mechanism 6 which adopts a pressure relief fragment to achieve the maximum pressure resistance P when the pressure reaches the maximum pressure resistanceCrushing deviceThe pressure relief is broken in the process, the service life of the medicine chamber is prolonged on the premise of ensuring the completion of the experiment, and the safety of the experiment is improved. The sensor 4 selects a platinum-rhodium thermocouple for testing ignition signals of a plurality of test points of the explosive chamber 3 and providing data for evaluating the comprehensive simultaneity of explosive charging ignition; the sensors 4 are fixed on the fulcrums of the sensor support 7, one sensor is fixed on one fulcrum and fixed in a welding mode, the lead of one sensor is welded on the sensor support 7 to serve as the first stage, and the lead of the other sensor is connected to the insulating sealing electrode 2 of the left plug 8.
Sensor support 7 uses the steel wire preparation of diameter 3mm, makes the structure shown in fig. 2 according to the studios structure size, and the axial is equipped with 3 sets of test surfaces, is equipped with 3 fulcrums on every axial cross section, respectively stretches out certain length around two axial cross sections around support 7, on the one hand with the left end cap 8 and the right end cap 9 in close contact with on 3 both sides of studios, on the other hand guarantees that the one-level as sensor 4 can stabilize output signal. Thermocouple sensors are fixedly connected to the supporting points in the figure 2.
The structure of the insulated sealing electrode 2 is shown in figure 3, a central enameled wire 2-1 is fixed in a central hole of a cone by using sealant, and the cone is pressed by a pressing screw 2-2 to ensure sealing after being placed into a plug.
The pressure relief fragment mechanism 6 is shown in figure 4, a pressure relief fragment 6-1 and a sealing metal washer 6-2 are sequentially placed, a fragment pressing screw 6-3 is used for pressing to ensure sealing, and then the pressure relief fragment mechanism 6 is arranged in a right plug 9.
The propellant charge parameters tested in the preferred embodiment of the invention were as follows: the diameter of the medicine chamber 3 is 80mm, the length is 100mm, the propellant charge 5 is 5/7 mono camphor powder, and the filling density is 0.2g/cm3The test method comprises the following steps:
1) the length of the sensor support 7 is 100mm, the axial sections are respectively located at 25mm, 50mm and 75mm, each axial section is provided with 3 testing supporting points which respectively form 120 degrees, and the radial distances are 0, 15mm and 30 mm.
2) Thermocouples were fixed to the respective fulcrums and one stage thereof was welded to the holder and the other stage was connected to the insulated sealing electrode 2.
3) The left plug 8 and igniter 1 are installed.
4) Putting the weighed safrole into a medicine chamber.
5) According to the extrusion pressure of 30MPa and the overall ignition theoretical pressure of 10MPa, according to the pressure relief fragment selection principle: pCrushing device＝PExtrusion process+PTheory of the inventionTherefore, a pressure relief fragment with the pressure resistance of 40MPa is selected;
6) and a right plug 9 is installed and connected with a sensor connecting wire.
7) Igniting after the ignition is ready, testing ignition signals and analyzing to obtain ignition comprehensive simultaneity test results of all ignition points, wherein the test is expressed by four dispersivity of time when the pressure reaches 5MPa, 10MPa, 20MPa and 30 MPa.
It is obvious from the above preferred embodiment that the core content of the present invention is to directly introduce a sensor to test ignition process signals in the propellant charge of a pharmacy, analyze and compare the test signals of a plurality of geometric points, and finally comprehensively evaluate the ignition comprehensive simultaneity of the propellant charge by the consistency of the signal change process. The obtained experimental result is real, the evaluation parameters are scientific, and the ignition effect of the propellant powder charge can be objectively evaluated.

Claims (2)

1. A propellant powder charging ignition comprehensive simultaneity evaluation method is characterized by comprising the following steps:
A. manufacturing a sensor bracket (7) for fixing a sensor according to the geometric structure of a barrel weapon medicine chamber, and arranging a plurality of test points in the axial direction and the radial direction of the medicine chamber;
B. fixing a sensor (4) at the test point, connecting one of two lead wires of the sensor with a sensor support (7), and tightly contacting the sensor support (7) with the wall of the medicine chamber (3) after the sensor support is arranged in the medicine chamber; the other lead is connected to the insulated sealing electrode (2) of the left plug (8);
C. according to barrel weapon projectile penetration pressure PExtrusion processAnd the theoretical pressure P at which the charge is fully ignited simultaneouslyTheory of the inventionSelecting a pressure relief fragment to be loaded into a pressure relief fragment mechanism (6), wherein the pressure relief fragment mechanism (6) is assembled on the right plug (9); pressure relief and fragment selection principle: maximum pressure resistance P of pressure relief fragmentCrushing device＝PExtrusion process+PTheory of the invention；
D. Assembling the igniter (1) on the left plug (8); the propellant charge (5) is loaded into the charge chamber (3) and all the parts are installed;
E. the igniter (1) works to ignite the propellant charge (5), the sensor (4) collects signals, and when the pressure reaches P in the testCrushing deviceWhen the pressure is released, the pressure releasing fragment is broken to release the pressure, and the test is finished; and evaluating the ignition overall simultaneity of the propellant charge through the change consistency of the axial signal and the radial signal.
2. The method of claim 1 for overall simultaneity assessment of propellant charge ignition, wherein: the axial test points of the medicine chamber (3) are more than 3 groups, and the radial test points are more than 2 points.
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CN108982050B (en) * 2018-08-28 2020-05-05 西安近代化学研究所 Explosive charge falling model experiment device and method

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CN2411473Y (en) * 1998-12-14 2000-12-20 中国工程物理研究院应用电子学研究所 Impact wave pressure testing device
CN1873411A (en) * 2005-06-03 2006-12-06 中国科学院力学研究所 Device for testing deflagrability of condensed fire detonator under condition of high termerature and high pressure
CN104089736A (en) * 2014-06-23 2014-10-08 中国石油大学(华东) Gunpowder detonation loading stress distribution law testing system

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CN101907426B (en) * 2010-07-15 2015-03-25 西安近代化学研究所 Propellant powder variable capacity burning rate testing device
CN101907427B (en) * 2010-07-15 2015-06-24 西安近代化学研究所 Device for testing transfiguration burning rate of gun propellant
CN104048563B (en) * 2014-06-24 2016-03-02 西安近代化学研究所 The dynamic Burning rate testing device of a kind of propellant powder

Patent Citations (3)

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Publication number Priority date Publication date Assignee Title
CN2411473Y (en) * 1998-12-14 2000-12-20 中国工程物理研究院应用电子学研究所 Impact wave pressure testing device
CN1873411A (en) * 2005-06-03 2006-12-06 中国科学院力学研究所 Device for testing deflagrability of condensed fire detonator under condition of high termerature and high pressure
CN104089736A (en) * 2014-06-23 2014-10-08 中国石油大学(华东) Gunpowder detonation loading stress distribution law testing system

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