CN104237018A - Method for testing stress-strain of composite propellant under condition of intermediate strain rate - Google Patents
Method for testing stress-strain of composite propellant under condition of intermediate strain rate Download PDFInfo
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Abstract
The invention discloses a method for testing stress-strain of composite propellant under the condition of an intermediate strain rate. The method comprises the following steps: fixing the loading speed of an actuator based on a high-speed hydraulic servo test system so as to ensure the intermediate strain rate needed by a sample; buffering the actuator and the sample by an interval of 3mm so as to reach a stable rate needed during loading; and compressing and deforming a cylindrical (Phi20*20mm) propellant sample at a certain loading speed, testing to obtain data of time, pressure and displacement of the sample and mathematically processing the data to obtain a stress-strain relation curve under the condition of the strain rate. The method is simple in step, reasonable in design, convenient to operate and good in use effect; the stress-strain testing problem of a composite solid propellant under the condition of the intermediate strain rate is effectively solved; the loading cost and the development cost of anti-overloading composite solid propellants can be reduced; the development period can be shortened; the launch reliability of a weapon system can be improved.
Description
Technical field
The present invention relates to a kind of stress-strain test method of composite propellant, be specifically related to the stress-strain test method of composite propellant under a kind of mid strain rate condition.
Background technology
Overload-resistant composite propellant powder charge design needs to set up suitable basic, normal, high wide in range rate of strain constitutive model, and by the method for finite element by this type of models applying in numerical evaluation, and then set up and be applicable to overload-resistant composite propellant loaded constitution design theory system.Determine that experimental technique and the device of viscoelastic Constitutive Model parameter are varied, (rate of strain is lower than 10 can be divided into quasi-static tensile or compression experiment according to different strain rate scope
-1/ s), mid strain rate stretches or compression experiment (1-100/s) and high strain rate tensile or compression experiment (10
2-10
4/ s).Low strain dynamic rate test unit MTS testing machine, css series experimental machine etc., split hopkinson bar technology (SHPB) under high strain-rate condition, measures the Dynamic mechanical analysis instrument (DMA) etc. of material viscoelastic parameter with the variation relation of temperature and load frequency.
But the experimental technique of current mid strain rate scope and test unit are ripe not enough comparatively speaking, apply extensive not.University of Akron of the U.S. is for exploring material mechanical behavior under mid strain rate, have studied some mid strain rate tensile test apparatus and measuring technologies, it mainly improves drop impact tensile test device, and have studied the mechanical behavior of some materials under mid strain rate, but there is not been reported to the Mechanics Performance Testing of solid propellant under mid strain rate.Domestic large quantifier elimination is carried out to test unit under low, high strain-rate condition and measuring technology, but the method for testing under mid strain rate condition is not conducted a research, still do not pay close attention to the mechanical property within the scope of composite propellant mid strain rate, a large amount of propellant material constitutive models does not consider the impact of mid strain rate yet.
Summary of the invention
The object of the present invention is to provide a kind of composite propellant stress-strain test method under mid strain rate condition, for overload-resistant composite solidpropellant powder charge development provides reference.
For solving its technical matters, realizing the object of the invention technical scheme and comprising the steps:
Step one, composite propellant sample (Φ 20 × 20mm) will be prepared and put into driven device disk center position, go downwards to sample upper surface close by pressure-controlled actuator panel, press panel micromatic setting again actuator to be gone downwards to fit with sample upper surface, data actuation interface display pressure is zero, records now shift value; Pressing actuator panel makes the up 3mm of actuator, reserved servo-hydraulic test systems actuator buffering adjustment district, make cylindrical composite propellant sample (Φ 20 × 20mm) and servo-hydraulic test systems actuator interval 3mm, with reach load sample time required even pace;
Step 2, according to the requirement of test rate of strain, calculate actuator loading velocity, loading velocity is by formula
calculate, wherein
for test rate of strain, v is actuator loading velocity, and h is cylinder sample length;
Step 3, test when the strain of setting composite propellant reaches 50% and stop, arranging high-speed hydraulic servo-control system picking rate is 1000 points/s, affecting, not arranging prestrain speed for eliminating actuator pretightning force on test findings;
Step 4, data acquisition system (DAS) obtains the one_to_one corresponding data of time, displacement, power, and adopts least square fitting to go out displacement versus time, force-time curve;
Step 5, according to the displacement-time curve that step 4 simulates, by formula
can obtain strain-time curve, in formula, ε is sample axial strain, and s is specimen height, and s' is sample axial displacement knots modification; According to the force-time curve that step 4 simulates, by formula
can obtain stress time curve, in formula, σ is sample axial stress, and F is sample pressure, and R is cylinder sample radius;
Step 6, according to formula
differentiate is carried out to step 5 gained strain-time curve, rate of strain-time curve can be obtained;
Step 7, according to step 5 gained stress time curve, step 6 gained time strain-time, least square fitting goes out stress-strain curve;
Ess-strain experimental test procedures under above-mentioned described composite solidpropellant mid strain rate condition, it is characterized in that: in step one, composite propellant sample is cylindrical (Φ 20 × 20mm), has mainly considered the test findings of equipment and personnel safety and various sample size;
Ess-strain experimental test procedures under above-mentioned described composite solidpropellant mid strain rate condition, it is characterized in that: servo-hydraulic test systems actuator and composite propellant sample interval 3mm in step one, mainly reserved servo-hydraulic test systems actuator buffering adjustment district, with reach load sample time required even pace;
Ess-strain experimental test procedures under above-mentioned described composite solidpropellant mid strain rate condition, when it is characterized in that actuator loads, ensure that test sample lay down location cleans, in actuator motion process, ensure that test sample peripheral region cleans;
Ess-strain experimental test procedures under above-mentioned described composite solidpropellant mid strain rate condition, it is characterized in that for reducing composite solidpropellant sample mismachining tolerance, square billet surrounded surface is at least excised 10mm rear and can be used as sample, and by direction of extrusion sampling, sample is deposited under drying at room temperature environment;
Compared with prior art have the following advantages: the present invention is based on common high-speed hydraulic Servo Testing test system, fixing actuator loading velocity is to ensure mid strain rate needed for test specimen, even pace required when actuator and sample interval 3mm cushion to reach loading, the compression deformation under certain loading velocity of cylindrical (Φ 20 × 20mm) test specimen, test obtains its time, pressure and displacement data, obtain the stress strain curve under mid strain rate condition by mathematics manipulation, efficiently solve a composite propellant stress-strain test difficult problem under mid strain rate condition.If consider mid strain rate experimental data in constitutive model, and by Finite Element Method by this type of models applying in numerical evaluation, greatly will shorten the overload-resistant composite propellant powder charge lead time, significantly reduce development cost, and can set up and be applicable to overload-resistant composite propellant loaded constitution design theory system.
Accompanying drawing explanation
Fig. 1 is method flow block diagram of the present invention;
Fig. 2 loads rate of strain 5 (1/s), Φ 15 × 15mm composite propellant stress-strain diagram;
Fig. 3 loads rate of strain 5 (1/s), Φ 15 × 15mm composite propellant rate of strain time curve;
Fig. 4 loads rate of strain 5 (1/s), Φ 20 × 20mm composite propellant stress-strain diagram;
Fig. 5 loads rate of strain 5 (1/s), Φ 20 × 20mm composite propellant rate of strain time curve;
Fig. 6 loads rate of strain 5 (1/s), Φ 25 × 25mm composite propellant stress-strain diagram;
Fig. 7 loads rate of strain 5 (1/s), Φ 25 × 25mm composite propellant rate of strain time curve;
Fig. 8 loads rate of strain 5 (1/s), Φ 30 × 30mm composite propellant stress-strain diagram;
Fig. 9 loads rate of strain 5 (1/s), Φ 30 × 30mm composite propellant rate of strain time curve;
Figure 10 loads rate of strain 1 (1/s), composite propellant stress-strain diagram under the 0mm condition of interval;
Figure 11 loads rate of strain 1 (1/s), composite propellant rate of strain time curve under the 0mm condition of interval;
Figure 12 loads rate of strain 1 (1/s), composite propellant stress-strain diagram under the 2mm condition of interval;
Figure 13 loads rate of strain 1 (1/s), composite propellant rate of strain time curve under the 2mm condition of interval;
Figure 14 loads rate of strain 1 (1/s), composite propellant stress-strain diagram under the 3mm condition of interval;
Figure 15 loads rate of strain 1 (1/s), composite propellant rate of strain time curve under the 3mm condition of interval;
Figure 16 loads rate of strain 10 (1/s), composite propellant stress-strain diagram under the 0mm condition of interval;
Figure 17 loads rate of strain 10 (1/s), composite propellant rate of strain time curve under the 0mm condition of interval;
Figure 18 loads rate of strain 10 (1/s), composite propellant stress-strain diagram under the 2mm condition of interval;
Figure 19 loads rate of strain 10 (1/s), composite propellant rate of strain time curve under the 2mm condition of interval;
Figure 20 loads rate of strain 10 (1/s), composite propellant stress-strain diagram under the 3mm condition of interval;
Figure 21 loads rate of strain 10 (1/s), composite propellant rate of strain time curve under the 3mm condition of interval;
Figure 22 loads rate of strain 5 (1/s), Φ 20 × 20mm composite propellant stress-strain diagram;
Figure 23 loads rate of strain 5 (1/s), Φ 20 × 20mm composite propellant rate of strain time curve;
Figure 24 loads rate of strain 5 (1/s), Φ 20 × 20mm composite propellant stress-strain diagram;
Figure 25 loads rate of strain 5 (1/s), Φ 20 × 20mm composite propellant rate of strain time curve;
Figure 26 loads rate of strain 5 (1/s), Φ 20 × 20mm composite propellant stress-strain diagram;
Figure 27 loads rate of strain 5 (1/s), Φ 20 × 20mm composite propellant rate of strain time curve.
Embodiment
Below by embodiment, technical scheme of the present invention is described in further detail.Composite propellant stress-strain test method under a kind of mid strain rate condition as shown in Figure 1, comprises the steps:
Step one, the cylindrical composite propellant sample (Φ 20 × 20mm) prepared is put into servo-hydraulic test systems and does driven device disk center position, go downwards to sample upper surface close by pressure-controlled actuator panel, press panel micromatic setting again actuator to be gone downwards to fit with sample upper surface, data actuation interface display pressure is zero, records now shift value;
Step 2, reserved servo-hydraulic test systems actuator buffering adjustment district, pressing actuator panel makes the up 3mm of actuator, makes cylindrical composite propellant sample and servo-hydraulic test systems actuator interval 3mm, even pace required during to reach loading sample;
Step 3, according to the requirement of test rate of strain, calculate actuator loading velocity, loading velocity is by formula
calculate, wherein
for test rate of strain, v is actuator loading velocity, and h is cylinder sample length;
Step 4, test when the strain of setting composite propellant reaches 50% and stop, arranging high-speed hydraulic servo-control system picking rate is 1000SPS, affecting, not arranging prestrain speed for eliminating actuator pretightning force on test findings;
Step 5, starts test, after off-test, moves in actuator, displacement transducer and pressure transducer unloading, and then balancing load, makes instrument get back to original state;
Step 6, does three tests, by data such as pressure, time, displacements stored in disk, and the one_to_one corresponding data of extraction time, displacement, power from test data;
Step 7, according to the one_to_one corresponding data of above-mentioned time, displacement, power, mathematics least square fitting goes out displacement versus time, force-time curve;
Step 8, according to displacement versus time, by formula
can obtain strain-time curve, in formula, ε is sample axial strain, and s is specimen height, and s' is sample axial displacement knots modification; According to force-time curve, by formula
can obtain stress time curve, in formula, σ is sample axial stress, and F is sample pressure, and R is cylinder sample radius;
Step 9, according to formula
differentiate is carried out to strain-time curve, rate of strain-time curve can be obtained;
Step 10, according to strain-time, stress time curve, least square fitting stress-strain curve;
Step 11, stress-strain test test result under certain composite propellant mid strain rate condition
(1) composite propellant size definite value test
Consider that composite propellant specimen size mismachining tolerance is large, choose Φ 15 × 15mm, Φ 20 × 20mm, definite value test that Φ 25 × 25mm, Φ 30 × 30mm tetra-kinds of samples carry out size, as Fig. 2 ~ Fig. 9, find its rate of strain scope respectively between 2 ~ 6,3 ~ 6,3 ~ 6,2 ~ 6 (1/s), composite propellant sample dose rate of strain requires is loaded less in satisfied test, in its loading procedure, security will be got well relatively, and final selected Φ 20 × 20mm is as composite propellant stress-strain test code test size under mid strain rate condition.
(2) actuator loads interval test
The impact of pretightning force when sample being loaded for avoiding servo-hydraulic test systems, and make the adjustment of actuator buffering reach required loading velocity, take the scheme of prepared separation between sample and actuator, make composite propellant sample testing rate of strain less with design rate of strain deviation, sample mechanical response oscillation amplitude is less.As Figure 10 ~ Figure 21, according to different interval test figure, when being spaced apart 3mm, rate of strain-time curve fluctuation is less, and deviation is less between design rate of strain, consider that the larger security threat to equipment and personnel in interval is larger, final selected cylindrical composite propellant sample (Φ 20 × 20mm) and servo-hydraulic test systems actuator interval 3mm simultaneously.
(3) mid strain rate replica test
Choose Φ 20 × 20mm composite propellant sample, to its carry out rate of strain be 5 (1/s) rate of strain repeatability load test, test result curve as shown in Figure 22 ~ Figure 27, as can be seen from test result, rate of strain-time curve, stress-strain curve are stable, reproducible.
The above; it is only preferred embodiment of the present invention; not the present invention is imposed any restrictions, every above embodiment is done according to the technology of the present invention essence any simple modification, change and equivalent structure change, all still belong in the protection domain of technical solution of the present invention.
Claims (1)
1. a composite solidpropellant ess-strain experimental test procedures under mid strain rate condition, it is characterized in that, this method of testing comprises the steps:
Step one, reserved servo-hydraulic test systems actuator buffering adjustment district, makes cylindrical composite propellant sample (Φ 20 × 20mm) and servo-hydraulic test systems actuator interval 3mm;
Step 2, according to
calculate actuator loading velocity, wherein
for test rate of strain, v is actuator loading velocity, and h is cylinder sample length, and t is the time;
Step 3, test when the strain of setting composite propellant reaches 50% and stop, arranging servo hydraulic control system picking rate is 1000 points/s, does not arrange prestrain speed;
Step 4, data acquisition system (DAS) obtains the one_to_one corresponding data of time, displacement, power, and adopts least square fitting to go out displacement versus time, force-time curve;
Step 5, according to the displacement-time curve that step 4 simulates, by formula
can obtain strain-time curve, in formula, ε is sample axial strain, and s is specimen height, and s' is sample axial displacement knots modification; According to the force-time curve that step 4 simulates, by formula
can obtain stress time curve, in formula, σ is sample axial stress, and F is sample pressure, and R is cylinder sample radius;
Step 6, according to formula
differentiate is carried out to step 5 gained strain-time curve, rate of strain-time curve can be obtained;
Step 7, according to step 5 gained stress time curve, step 6 gained time strain-time, least square fitting goes out stress-strain curve.
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Cited By (9)
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| CN104820083A (en) * | 2015-05-04 | 2015-08-05 | 西安近代化学研究所 | Predicting method of large-size NEPE propellant loading storage life |
| CN106567792A (en) * | 2016-10-27 | 2017-04-19 | 上海新力动力设备研究所 | Device for measuring axial displacement of solid rocket engine grain in launching process |
| CN109829222A (en) * | 2019-01-24 | 2019-05-31 | 北京理工大学 | A kind of composite propellant Compressive Mechanical this structure method of the wide temperature range of width strain rate |
| CN109870356A (en) * | 2019-01-28 | 2019-06-11 | 北京理工大学 | Multi-channel wide should broaden the propellant compression stress test device of temperature range high security |
| CN110514581A (en) * | 2019-09-10 | 2019-11-29 | 哈尔滨工业大学 | A kind of resisting medium Evaluating Mechanical Properties device and evaluation method |
| CN112432604A (en) * | 2020-10-30 | 2021-03-02 | 西安近代化学研究所 | Rotary dynamic strain testing system and method for propellant grain winding and wrapping |
| CN113343465A (en) * | 2021-06-09 | 2021-09-03 | 四川长虹空调有限公司 | Method for calculating stress-strain data of EPS foam sample piece at high compression rate |
| CN115032076A (en) * | 2022-08-11 | 2022-09-09 | 中国人民解放军国防科技大学 | Solid propellant tension and compression mechanical property integrated test device and method |
| CN116754211A (en) * | 2023-08-22 | 2023-09-15 | 中国人民解放军火箭军工程大学 | Method and related device for acquiring mechanical property information of solid rocket propeller |
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Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104820083A (en) * | 2015-05-04 | 2015-08-05 | 西安近代化学研究所 | Predicting method of large-size NEPE propellant loading storage life |
| CN104820083B (en) * | 2015-05-04 | 2016-08-24 | 西安近代化学研究所 | A kind of predictor method of large scale NEPE propellant loading storage life |
| CN106567792A (en) * | 2016-10-27 | 2017-04-19 | 上海新力动力设备研究所 | Device for measuring axial displacement of solid rocket engine grain in launching process |
| WO2018076958A1 (en) * | 2016-10-27 | 2018-05-03 | 上海新力动力设备研究所 | Apparatus for measuring axial displacement of a solid rocket motor grain in launching process |
| CN106567792B (en) * | 2016-10-27 | 2018-09-07 | 上海新力动力设备研究所 | The device of solid rocket motor grain axial displacement in a kind of measurement ejection process |
| CN109829222B (en) * | 2019-01-24 | 2021-01-19 | 北京理工大学 | Compression mechanics constitutive method of composite propellant with wide strain rate and wide temperature range |
| CN109829222A (en) * | 2019-01-24 | 2019-05-31 | 北京理工大学 | A kind of composite propellant Compressive Mechanical this structure method of the wide temperature range of width strain rate |
| CN109870356A (en) * | 2019-01-28 | 2019-06-11 | 北京理工大学 | Multi-channel wide should broaden the propellant compression stress test device of temperature range high security |
| CN110514581A (en) * | 2019-09-10 | 2019-11-29 | 哈尔滨工业大学 | A kind of resisting medium Evaluating Mechanical Properties device and evaluation method |
| CN110514581B (en) * | 2019-09-10 | 2021-08-31 | 哈尔滨工业大学 | Viscous medium mechanical property evaluation device and evaluation method |
| CN112432604A (en) * | 2020-10-30 | 2021-03-02 | 西安近代化学研究所 | Rotary dynamic strain testing system and method for propellant grain winding and wrapping |
| CN113343465A (en) * | 2021-06-09 | 2021-09-03 | 四川长虹空调有限公司 | Method for calculating stress-strain data of EPS foam sample piece at high compression rate |
| CN113343465B (en) * | 2021-06-09 | 2022-04-01 | 四川长虹空调有限公司 | Method for calculating stress-strain data of EPS foam sample piece at high compression rate |
| CN115032076A (en) * | 2022-08-11 | 2022-09-09 | 中国人民解放军国防科技大学 | Solid propellant tension and compression mechanical property integrated test device and method |
| CN115032076B (en) * | 2022-08-11 | 2022-11-04 | 中国人民解放军国防科技大学 | Solid propellant tension and compression mechanical property integrated test device and method |
| CN116754211A (en) * | 2023-08-22 | 2023-09-15 | 中国人民解放军火箭军工程大学 | Method and related device for acquiring mechanical property information of solid rocket propeller |
| CN116754211B (en) * | 2023-08-22 | 2023-12-19 | 中国人民解放军火箭军工程大学 | Method and related device for acquiring mechanical property information of solid rocket propeller |
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