CN102253107A - Device for testing electrostatic sensitivity of solid propellant - Google Patents
Device for testing electrostatic sensitivity of solid propellant Download PDFInfo
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- CN102253107A CN102253107A CN201110093671.3A CN201110093671A CN102253107A CN 102253107 A CN102253107 A CN 102253107A CN 201110093671 A CN201110093671 A CN 201110093671A CN 102253107 A CN102253107 A CN 102253107A
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Abstract
The invention provides a device for testing electrostatic sensitivity of a solid propellant. The device has higher precision and comprises a direct current high voltage power supply, a capacitor, a resistor R1, a resistor R2, a needle electrode, a plate electrode, switches, a first voltage probe, a second voltage probe and a voltage processor, wherein the direct current high voltage power supply, the switches, the resistor R1 and the capacitor are sequentially connected to form a charge circuit; the capacitor, the resistor R1, the switches, the needle electrode, a tested sample (added when being used), the plate electrode and the resistor R2 are sequentially connected to form a discharge circuit; the first voltage probe is connected at the two ends of the capacitor; the second voltage probe is connected at the two ends of the resistor R2; the voltage processor is connected with the two voltage probes respectively; and when being used, the tested sample is put between the needle electrode and the plate electrode and is contacted with the needle electrode and the plate electrode respectively. The device solves the problem that the testing result has systematic error because the existing testing devices take no account of the energy loss of the test circuit.
Description
Technical field
The invention belongs to the testing of materials technical field, relate to a kind of proving installation of material safety property testing technology, particularly solid propellant electrostatic sensitivity.
Background technology
Solid propellant is to utilize self burning to release energy, and for aerospacecrafts such as solid propellant rocket provide a kind of energetic material of the energy, is present topmost guided missile propellant.Solid propellant has certain susceptibility in the sharp source of static to external world.When the energy that is discharged in the static discharge process was enough big, solid propellant had the possibility of being ignited.There is an electrostatic discharge critical energy in propellant for determining to form.Solid propellant be subjected to surpassing this transition energy do just might be ignited the time spent.The electrostatic sensitivity test is exactly by certain experimental provision, determines the numerical value of this transition energy, with this yardstick as measurement solid propellant static danger.Accurately measure the electrostatic sensitivity of solid propellant, for the safe handling of instructing propellant with protect extremely important.If the test value of this energy is bigger than normal, will be not enough to potential danger understanding, might not take corresponding safeguard procedures, finally may cause propellant to ignite and then cause the loss of casualties and weaponry.
Solid propellant electrostatic sensitivity commonly used is at present tested the influence of main testing static discharge process to propellant, and the principle of its device as shown in Figure 1.Circuit connecting mode is: DC high-voltage power supply and electric capacity constitute charge circuit, electric capacity, pin electrode, tested sample (add during test, be positioned on the plate electrode, thickness is 0.5mm), plate electrode (pin, plate two electrode separations are 1mm) constitutes discharge loop, electric capacity two termination electrostatic voltmeters are measured its charging voltage.Use the specific implementation method of this device to test propellant electrostatic sensitivity to be: switch is at first connected charge circuit, connects DC high-voltage power supply and electric capacity (capacitance is C), to the electric capacity charging, uses electrostatic voltmeter to measure charging voltage (U).After the electric capacity charging finished, the gross energy that stores on the electric capacity was
Be the discharge energy that acts on the tested sample.Use the switch connection discharge loop again, tested sample is carried out discharge process.Whether ignite according to tested sample, adjust the charging voltage of electric capacity, act on discharge energy on the tested sample with change according to Bo Luoxidengfa.The continuous discharge energy of corrective action on tested sample, same tested sample is carried out at least 25 tests, test result is handled according to the method among the standard GJB/Z377A-94 " sensitivity test mathematical statistics method ", tries to achieve possibility that tested sample ignites and be 50% critical discharge energy E50.
The main deficiency of existing proving installation is: (1) is gross energy on the electric capacity
Be designated as the discharge energy that acts on the tested sample, this is a kind of simplification processing mode, thinks that promptly the energy on the electric capacity acts on the tested sample fully, does not consider the actual energy loss of discharge loop, therefore there is systematic error in test result, and the general test result is bigger than normal; (2) tested sample does not contact with pin electrode, and a part of loss that causes the capacitor discharge energy causes test result bigger than normal at the air breakdown that makes between pin electrode and the sample; (3) short to the discharge time of tested sample, may cause part propellant sample not ignite, can't test its electrostatic sensitivity.
Summary of the invention
The objective of the invention is: the above-mentioned shortcoming that overcomes existing solid propellant electrostatic sensitivity proving installation, separate consider never between discharge loop energy loss, pin electrode and the tested sample that the air breakdown energy loss causes that test result is bigger than normal, discharge time short-range missile cause problems such as propellant does not ignite, the higher solid propellant electrostatic sensitivity proving installation of a kind of precision is proposed.
The ultimate principle of technical solution of the present invention is: the voltage and current value of test practical function on the propellant tested sample, and then calculate the actual discharge energy that acts on the tested sample.
Technical scheme of the present invention is: a kind of solid propellant electrostatic sensitivity proving installation comprises DC high-voltage power supply, electric capacity, resistance R 1, resistance R 2, pin electrode, plate electrode, switch, first voltage probe, second voltage probe and voltage processor.Wherein, DC high-voltage power supply, switch, resistance R 1 and the electric capacity formation charge circuit that is linked in sequence successively, electric capacity, resistance R 1, switch, pin electrode, tested sample (adding during use), plate electrode, the resistance R 2 formation discharge loop that is linked in sequence successively; First voltage probe is connected on the electric capacity two ends; Second voltage probe is connected on resistance R 2 two ends; Voltage processor is connected with two voltage probes respectively.During use, tested sample is placed between pin electrode and the plate electrode, and contacts with pin electrode and plate electrode respectively.
The invention has the beneficial effects as follows: measure the voltage U at electric capacity two ends respectively by using two voltage probes
CVoltage U with resistance R 2 two ends
2, by further calculating electric current I and the voltage U that directly acts on tested sample
SThereby, can accurately calculate the discharge energy that acts on tested sample, solved existing proving installation and do not considered that the energy loss of test circuit causes test result to have the problem of systematic error; Tested sample contacts with pin electrode and plate electrode respectively, has solved the problem that air breakdown between electrode and the tested sample causes energy loss; By in test circuit, introducing resistance R 1 and resistance R 2, make discharge process time long enough, solved the problem that discharge time, weak point may cause propellant not ignite.
Description of drawings
Fig. 1 is a solid propellant electrostatic sensitivity proving installation circuit diagram commonly used at present;
Fig. 2 is the solid propellant electrostatic sensitivity proving installation circuit diagram that the specific embodiment of the invention one provides;
Fig. 3 is the solid propellant electrostatic sensitivity proving installation circuit diagram that the specific embodiment of the invention two provides.
Embodiment
The invention will be further described below in conjunction with accompanying drawing.
Fig. 2 is the solid propellant electrostatic sensitivity proving installation circuit diagram that the specific embodiment of the invention one provides.As shown in the figure, comprise DC high-voltage power supply, electric capacity, resistance R 1, resistance R 2, pin electrode, plate electrode, first switch, second switch, first voltage probe, second voltage probe and voltage processor.Wherein, DC high-voltage power supply, first switch, resistance R 1 and the electric capacity formation charge circuit that is linked in sequence successively, electric capacity, resistance R 1, second switch, pin electrode, tested sample (add during use, and contact with pin electrode and plate electrode respectively), plate electrode, the resistance R 2 formation discharge loop that is linked in sequence successively; First voltage probe is connected on the electric capacity two ends; Second voltage probe is connected on resistance R 2 two ends; Voltage processor is connected with two voltage probes respectively, the voltage signal of two voltage probes of record.During charging, first switch closure is communicated with charge circuit; During discharge, the second switch closure is communicated with discharge loop.
Fig. 3 is the solid propellant electrostatic sensitivity proving installation circuit diagram that the specific embodiment of the invention two provides.As shown in the figure, comprise DC high-voltage power supply, electric capacity, resistance R 1, resistance R 2, pin electrode, plate electrode, single-pole double-throw switch (SPDT), first voltage probe, second voltage probe and a voltage processor.Wherein, DC high-voltage power supply, switch, resistance R 1 and the electric capacity formation charge circuit that is linked in sequence successively, electric capacity, resistance R 1, switch, pin electrode, tested sample (add during use, and contact with pin electrode and plate electrode respectively), plate electrode, the resistance R 2 formation discharge loop that is linked in sequence successively; First voltage probe is connected on the electric capacity two ends; Second voltage probe is connected on resistance R 2 two ends; Voltage processor is connected with two voltage probes respectively, the voltage signal of two voltage probes of record.During charging, the single-pole double-throw switch (SPDT) closure is communicated with charge circuit; During discharge, the single-pole double-throw switch (SPDT) closure is communicated with discharge loop.
Comprise the charging and two processes of discharging during test.At first carry out charging process, be communicated with charge circuit.After the electric capacity charging finishes, disconnecting charge circuit, carry out discharge process again, connect discharge loop, is that tested sample is carried out discharge process to solid propellant, uses two voltage probes to measure the voltage U at electric capacity two ends respectively
CVoltage U with resistance R 2 two ends
2, two voltage signals are by the voltage processor record.The electric current I of the tested sample of flowing through is by formula I=U
2/ R
2Calculate the voltage U at tested sample two ends
SBy formula U
S=U
C-I (R
1+ R
2) calculate, act on discharge energy on the tested sample by formula
Calculate wherein initial moment t
sFor connecting the moment of discharge loop; Stop t constantly
dBe the moment of discharge loop end discharge, i.e. U
SThe value of I becomes for zero the moment again.Whether ignite according to survey propellant tested sample, adjust the charging voltage of electric capacity according to Bo Luoxidengfa, act on discharge energy on the tested sample with change, same tested sample is carried out at least 25 tests, test result is according to the disposal route among the standard GJB/Z377A-94 (sensitivity test mathematical statistics method), try to achieve possibility that the propellant tested sample ignites and be 50% discharge energy E50, as the test value of this propellant electrostatic sensitivity.
Compare experiment in the laboratory, the electrostatic sensitivity of certain class HTPB (Hydroxy Terminated Polybutadiene, end hydroxy butadiene) composite solidpropellant is tested.Experiment 1 is adopted identical tested sample with experiment 2.
The solid propellant electrostatic sensitivity proving installation commonly used that experiment 1 is adopted as shown in Figure 1, according to the method for setting forth in the background technology, the electrostatic sensitivity value E50=154.0 milli that obtains this propellant is burnt.
The solid propellant electrostatic sensitivity proving installation that experiment 2 adopts the specific embodiment of the invention two as shown in Figure 3 to provide.Wherein, DC high-voltage power supply output voltage range: 0-20000 volt; Electric capacity adopts high pressure resistant electric capacity, and capacitance is 0.1 microfarad; Resistance R 1 and R2 adopt noninductive resistance, and as ceramic resistor or wire resistor, R1 is 500 ohm, and R2 is 1 ohm; First voltage probe adopts high-voltage probe, and second voltage probe adopts ordinary ultrasonic probe; Voltage processor adopts oscillograph in this experiment, also can adopt other energy recording voltage voltage of signals processors.The experiment 2 electrostatic sensitivity test values that obtain this propellant are that 66.4 millis are burnt.
Can find by above-mentioned two experiments:
(1) test the 1 solid propellant electrostatic sensitivity proving installation commonly used that is adopted, because do not consider the various energy losses in the whole test circuit, measured sensitivity numerical value is higher, can not accurately reflect the electrostatic sensitivity of solid propellant.
(2) example 2 adopts device involved in the present invention, measure practical function voltage and current on sample, calculate the practical function energy again, the energy loss of test circuit and the energy loss of air breakdown have been got rid of, therefore to the test value of same sample result, can measure the electrostatic sensitivity value of propellant comparatively exactly less than experiment 1.
Because the test philosophy of energetic material electrostatic sensitivitys such as propellant, fiery explosive is identical, this device is applicable to the electrostatic sensitivity test of various energetic materials fully; The present invention adopts resistance-capacitance discharge simulation static discharge, the electrostatic sensitivity of test solid propellant, and the scope of application of this device is not limited to the electrostatic sensitivity test, everyly applies the relevant security test of electric energy effect, all can adopt this device to test.
Claims (2)
1. a solid propellant electrostatic sensitivity proving installation comprises DC high-voltage power supply, electric capacity, pin electrode, plate electrode, switch, it is characterized in that, also comprises resistance R 1, resistance R 2, first voltage probe, second voltage probe and voltage processor; Wherein, DC high-voltage power supply, switch, resistance R 1 and the electric capacity formation charge circuit that is linked in sequence successively, the tested sample that adds when electric capacity, resistance R 1, switch, pin electrode, use, plate electrode, the resistance R 2 formation discharge loop that is linked in sequence successively; First voltage probe is connected on the electric capacity two ends; Second voltage probe is connected on resistance R 2 two ends; Voltage processor is connected with two voltage probes respectively; During use, tested sample is placed between pin electrode and the plate electrode, and contacts with pin electrode and plate electrode respectively.
2. solid propellant electrostatic sensitivity proving installation according to claim 1 is characterized in that, described switch is a single-pole double-throw switch (SPDT).
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| Application Number | Priority Date | Filing Date | Title |
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| CN201110093671.3A CN102253107A (en) | 2011-04-14 | 2011-04-14 | Device for testing electrostatic sensitivity of solid propellant |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201110093671.3A CN102253107A (en) | 2011-04-14 | 2011-04-14 | Device for testing electrostatic sensitivity of solid propellant |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106124895A (en) * | 2016-06-28 | 2016-11-16 | 西安航天动力技术研究所 | A kind of solid engines Electrostatic Safety test device and method |
| CN110018287A (en) * | 2019-05-17 | 2019-07-16 | 中国工程物理研究院化工材料研究所 | A kind of explosive electrostatic test instrument for simulating static electricity on human body's spark discharge |
| CN110969972A (en) * | 2019-12-27 | 2020-04-07 | Tcl华星光电技术有限公司 | Display panel detection method and device, controller and storage medium |
| CN113376210A (en) * | 2021-05-28 | 2021-09-10 | 襄阳新舟自动化科技有限公司 | Electrostatic loading quick drying device |
| CN114754638A (en) * | 2022-04-19 | 2022-07-15 | 华东光电集成器件研究所 | Digital detonator sensitivity test device and method |
-
2011
- 2011-04-14 CN CN201110093671.3A patent/CN102253107A/en active Pending
Non-Patent Citations (1)
| Title |
|---|
| 《含能材料》 20100831 鲍桐等 复合固体推进剂静电危险性研究进展 第2部分 1-2 第18卷, 第4期 * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106124895A (en) * | 2016-06-28 | 2016-11-16 | 西安航天动力技术研究所 | A kind of solid engines Electrostatic Safety test device and method |
| CN110018287A (en) * | 2019-05-17 | 2019-07-16 | 中国工程物理研究院化工材料研究所 | A kind of explosive electrostatic test instrument for simulating static electricity on human body's spark discharge |
| CN110969972A (en) * | 2019-12-27 | 2020-04-07 | Tcl华星光电技术有限公司 | Display panel detection method and device, controller and storage medium |
| CN113376210A (en) * | 2021-05-28 | 2021-09-10 | 襄阳新舟自动化科技有限公司 | Electrostatic loading quick drying device |
| CN114754638A (en) * | 2022-04-19 | 2022-07-15 | 华东光电集成器件研究所 | Digital detonator sensitivity test device and method |
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Application publication date: 20111123 |