CN104237018B - 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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- CN104237018B CN104237018B CN201410421465.4A CN201410421465A CN104237018B CN 104237018 B CN104237018 B CN 104237018B CN 201410421465 A CN201410421465 A CN 201410421465A CN 104237018 B CN104237018 B CN 104237018B
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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, and in particular under the conditions of a kind of middle strain rate
The stress-strain test method of composite propellant.
Background technology
Overload-resistant composite propellant powder charge design needs to set up suitable basic, normal, high wide in range strain rate constitutive model, and leads to
The method for crossing finite element is applied to this class model in numerical computations, and then sets up suitable for overload-resistant composite propellant powder charge
Structural design theory system.Determine that the experimental technique and device of viscoelastic Constitutive Model parameter are varied, according to differently strained
Rate scope can be divided into quasi-static tensile or compression experiment, and (strain rate is less than 10-1/ s), middle strain rate stretching or compression experiment
(1-100/s) with high strain rate tensile or compression experiment (102-104/s).Low strain dynamic rate assay device MTS testing machines, css series
Experimental machine etc., the split hopkinson bar technology (SHPB) under the conditions of high strain-rate, measurement material viscoelastic parameter with temperature and
Dynamic mechanical analysis instrument (DMA) of the variation relation of load frequency etc..
But the experimental technique and assay device of current middle strain rate scope are comparatively ripe not enough, application is not wide enough
It is general.University of Akron of the U.S. have studied strain rate tension test dress in some to explore material mechanical behavior under middle strain rate
Put and measuring technology, it is mainly improved to drop impact tensile test device, and have studied some materials in middle strain
There is not been reported for the Mechanics Performance Testing of solid propellant under mechanical behavior under rate, but centering strain rate.The country is to low, Gao Ying
The method of testing that assay device and measuring technology have been carried out under the conditions of substantial amounts of research, but centering strain rate under the conditions of variability does not have
Conduct a research, the mechanical property in the range of strain rate in composite propellant is still not concerned with, substantial amounts of this structure of propellant material
Model does not account for the impact of middle strain rate yet.
The content of the invention
It is an object of the invention to provide a kind of composite propellant stress-strain test method under the conditions of middle strain rate, is anti-
The powder charge of overload composite solidpropellant is developed and provides reference.
To solve its technical problem, realize that the object of the invention technical scheme comprises the steps：
Step one, will prepare composite propellant sample (20 × 20mm of Φ) and is put at driven device disk center position, pressing
Control actuator panel go downwards to it is close with sample upper surface, then pressing panel micromatic setting make actuator go downwards to on sample
Surface is fitted, and data actuation interface display pressure is zero, records now shift value；Pressing actuator panel makes actuator up
3mm, reserves servo-hydraulic test systems actuator buffering adjustment area, make cylindrical composite propellant sample (20 × 20mm of Φ) with
Servo-hydraulic test systems actuator is spaced 3mm, to reach even pace required during loading sample；
Step 2, requires according to test strain rate, calculates actuator loading velocity, and loading velocity presses formulaCalculate, whereinTo test strain rate, v is actuator loading velocity, and h is that cylinder sample is long
Degree；
Step 3, setting composite propellant strain stops up to test when 50%, arranges high-speed hydraulic servo-control system and adopts
Collection speed is 1000 points/s, is to eliminate actuator pretightning force to affect result of the test, is not provided with prestrain speed；
Step 4, data collecting system obtains time, displacement, the one-to-one corresponding data of power, and is intended using method of least square
Close out displacement versus time, force-time curve；
Step 5, according to the displacement-time curve that step 4 is fitted, by formulaStrain-time can be obtained
Curve, ε is sample axial strain in formula, and s is specimen height, and s' is sample axial displacement knots modification；Fitted according to step 4
Force-time curve, by formulaStress time curve can be obtained, σ is sample axial stress in formula, F is examination
Sample pressure, R is cylinder sample radius；
Step 6, according to formulaDerivation is carried out to step 5 gained strain-time graph, you can answered
Variability-time graph；
Step 7, according to step 5 gained stress time curve, step 6 gained time strain-time, least square
Method fits load-deformation curve；
Ess-strain experimental test procedures under the conditions of strain rate in above-mentioned described composite solidpropellant, its feature exists
In：Composite propellant sample is cylindrical (20 × 20mm of Φ) in step one, has mainly considered equipment and personnel safety
With the result of the test of various sample size；
Ess-strain experimental test procedures under the conditions of strain rate in above-mentioned described composite solidpropellant, its feature exists
In：Servo-hydraulic test systems actuator is spaced 3mm with composite propellant sample in step one, mainly reserves servo-hydraulic and surveys
Test system actuator buffering adjustment area, to reach even pace required during loading sample；
Ess-strain experimental test procedures under the conditions of strain rate in above-mentioned described composite solidpropellant, its feature exists
When actuator is loaded, it is ensured that test sample lay down location is cleaned, in actuator motor process, it is ensured that test sample peripheral region
Clean in domain；
Ess-strain experimental test procedures, its feature under the conditions of strain rate in above-mentioned described composite solidpropellant
It is, to reduce composite solidpropellant sample mismachining tolerance, square billet surrounded surface at least to be cut off into 10mm rears and can be used as examination
Sample, and sample by the direction of extrusion, sample is deposited under drying at room temperature environment；
There is compared with prior art advantages below：The present invention is based on common high-speed hydraulic servo test system, fixed to make
Dynamic device loading velocity middle strain rate needed for ensure test specimen, actuator is required during loading to reach with sample interval 3mm bufferings
Even pace, cylindrical (20 × 20mm of Φ) test specimen compression under certain loading velocity, test obtains its time, pressure
And displacement data, the stress strain curve in being obtained by Mathematical treatment under the conditions of strain rate, efficiently solve middle strain
A composite propellant stress-strain test difficult problem under the conditions of rate.If strain rate experimental data in considering in constitutive model, and pass through
Finite Element Method is applied to this class model in numerical computations, will greatly shorten the overload-resistant composite propellant powder charge lead time,
Development cost is greatly reduced, and can be set up suitable for overload-resistant composite propellant charge constitution design theory system.
Description of the drawings
Fig. 1 is method of the present invention FB(flow block)；
Fig. 2 is to load strain rate 5 (1/s), Φ 15 × 15mm composite propellant stress-strain diagrams；
Fig. 3 is to load strain rate 5 (1/s), Φ 15 × 15mm composite propellant strain rate time graphs；
Fig. 4 is to load strain rate 5 (1/s), Φ 20 × 20mm composite propellant stress-strain diagrams；
Fig. 5 is to load strain rate 5 (1/s), Φ 20 × 20mm composite propellant strain rate time graphs；
Fig. 6 is to load strain rate 5 (1/s), Φ 25 × 25mm composite propellant stress-strain diagrams；
Fig. 7 is to load strain rate 5 (1/s), Φ 25 × 25mm composite propellant strain rate time graphs；
Fig. 8 is to load strain rate 5 (1/s), Φ 30 × 30mm composite propellant stress-strain diagrams；
Fig. 9 is to load strain rate 5 (1/s), Φ 30 × 30mm composite propellant strain rate time graphs；
Figure 10 is loading strain rate 1 (1/s), is spaced composite propellant stress-strain diagram under the conditions of 0mm；
Figure 11 is loading strain rate 1 (1/s), is spaced composite propellant strain rate time graph under the conditions of 0mm；
Figure 12 is loading strain rate 1 (1/s), is spaced composite propellant stress-strain diagram under the conditions of 2mm；
Figure 13 is loading strain rate 1 (1/s), is spaced composite propellant strain rate time graph under the conditions of 2mm；
Figure 14 is loading strain rate 1 (1/s), is spaced composite propellant stress-strain diagram under the conditions of 3mm；
Figure 15 is loading strain rate 1 (1/s), is spaced composite propellant strain rate time graph under the conditions of 3mm；
Figure 16 is loading strain rate 10 (1/s), is spaced composite propellant stress-strain diagram under the conditions of 0mm；
Figure 17 is loading strain rate 10 (1/s), is spaced composite propellant strain rate time graph under the conditions of 0mm；
Figure 18 is loading strain rate 10 (1/s), is spaced composite propellant stress-strain diagram under the conditions of 2mm；
Figure 19 is loading strain rate 10 (1/s), is spaced composite propellant strain rate time graph under the conditions of 2mm；
Figure 20 is loading strain rate 10 (1/s), is spaced composite propellant stress-strain diagram under the conditions of 3mm；
Figure 21 is loading strain rate 10 (1/s), is spaced composite propellant strain rate time graph under the conditions of 3mm；
Figure 22 is to load strain rate 5 (1/s), Φ 20 × 20mm composite propellant stress-strain diagrams；
Figure 23 is to load strain rate 5 (1/s), Φ 20 × 20mm composite propellant strain rate time graphs；
Figure 24 is to load strain rate 5 (1/s), Φ 20 × 20mm composite propellant stress-strain diagrams；
Figure 25 is to load strain rate 5 (1/s), Φ 20 × 20mm composite propellant strain rate time graphs；
Figure 26 is to load strain rate 5 (1/s), Φ 20 × 20mm composite propellant stress-strain diagrams；
Figure 27 is to load strain rate 5 (1/s), Φ 20 × 20mm composite propellant strain rate time graphs.
Specific embodiment
Below by embodiment, technical scheme is described in further detail.In one kind as shown in Figure 1
Composite propellant stress-strain test method, comprises the steps under the conditions of strain rate：
Step one, by the cylindrical composite propellant sample (20 × 20mm of Φ) for preparing servo-hydraulic test systems are put into
Make at driven device disk center position, pressing control actuator panel go downwards to it is close with sample upper surface, then pressing panel fine setting
Device goes downwards to actuator to fit with sample upper surface, and data actuation interface display pressure is zero, record now shift value；
Step 2, reserves servo-hydraulic test systems actuator buffering adjustment area, and pressing actuator panel is made in actuator
Row 3mm, makes cylindrical composite propellant sample be spaced 3mm with servo-hydraulic test systems actuator, to reach during loading sample
Required even pace；
Step 3, requires according to test strain rate, calculates actuator loading velocity, and loading velocity presses formulaCalculate, whereinTo test strain rate, v is actuator loading velocity, and h is that cylinder sample is long
Degree；
Step 4, setting composite propellant strain stops up to test when 50%, arranges high-speed hydraulic servo-control system and adopts
Integrate speed as 1000SPS, be to eliminate actuator pretightning force to affect result of the test, be not provided with prestrain speed；
Step 5, starts test, after off-test, will move in actuator, and displacement transducer and pressure transducer are unloaded, so
Afterwards balancing load, makes instrument return to original state；
Step 6, does three tests, the data such as pressure, time, displacement is stored in into disk, when extracting from test data
Between, displacement, the one-to-one corresponding data of power；
Step 7, according to the above-mentioned time, displacement, power one-to-one corresponding data, mathematics least square fitting go out displacement-
Time, force-time curve；
Step 8, according to displacement versus time, by formulaStrain-time graph can be obtained, ε is sample axial direction in formula
Strain, s is specimen height, and s' is sample axial displacement knots modification；According to force-time curve, by formulaCan be answered
Force-time curve, σ is sample axial stress in formula, and F is sample pressure, and R is cylinder sample radius；
Step 9, according to formulaDerivation is carried out to strain-time graph, you can obtain strain rate-time
Curve；
Step 10, according to strain-time, stress time curve, least square fitting load-deformation curve；
Step 11, stress-strain test test result under the conditions of strain rate in certain composite propellant
(1) composite propellant size definite value test
It is big in view of composite propellant specimen size mismachining tolerance, selection 15 × 15mm of Φ, 20 × 20mm of Φ, Φ 25 ×
30 × 30mm of 25mm, Φ, tetra- kinds of samples carry out the definite value test of size, and such as Fig. 2~Fig. 9 has found its strain rate scope respectively 2
Between~6,3~6,3~6,2~6 (1/s), composite propellant sample medicine in the case that test loading strain rate is required is being met
Amount is less, and safety is relative in its loading procedure will get well, and finally selected 20 × 20mm of Φ are pushed away as being combined under the conditions of middle strain rate
Enter agent stress-strain test code test size.
(2) actuator loading interval test
The impact of pretightning force during to avoid servo-hydraulic test systems from loading sample, and reach actuator buffering adjustment
Required loading velocity, takes the scheme of prepared separation between sample and actuator, makes composite propellant sample testing strain rate
Less with design strain rate deviation, sample mechanical response oscillation amplitude is less.Such as Figure 10~Figure 21, tested according to different interval
Data understand, when at intervals of 3mm, strain rate-time graph fluctuation is less, and deviation is less between design strain rate, while
In view of being spaced, the bigger security threat to equipment and personnel is bigger, finally selected cylindrical composite propellant sample (Φ 20 ×
20mm) it is spaced 3mm with servo-hydraulic test systems actuator.
(3) strain rate replica test in
Φ 20 × 20mm composite propellant samples are chosen, the strain rate repeatability loading that strain rate is 5 (1/s) is carried out to it
Test, test result curve as shown in Figure 22~Figure 27, from test result as can be seen that strain rate-time graph, stress-
Strain curve is stablized, reproducible.
The above, is only presently preferred embodiments of the present invention, and not the present invention is imposed any restrictions, every according to the present invention
Any simple modification, change and equivalent structure change that technical spirit is made to above example, still fall within skill of the present invention
In the protection domain of art scheme.
Claims (1)
1. a kind of composite solidpropellant ess-strain experimental test procedures under the conditions of middle strain rate, it is characterised in that the test
Method comprises the steps：
Step one, reserves servo-hydraulic test systems actuator buffering adjustment area, makes cylindrical composite propellant sample and servo
Hydraulic test system actuator is spaced 3mm, and the cylindrical composite propellant specimen size is：Φ20×20mm；
Step 2, according toActuator loading velocity is calculated, whereinTo test strain rate, v is work
Dynamic device loading velocity, h is cylinder sample length, and t is the time；
Step 3, setting composite propellant strain stops up to test when 50%, arranges servo hydraulic control system picking rate and is
1000 points/s, it is not provided with prestrain speed；
Step 4, data collecting system obtains time, displacement, the one-to-one corresponding data of power, and is gone out using least square fitting
Displacement versus time, force-time curve；
Step 5, according to the displacement-time curve that step 4 is fitted, by formula- time song can be strained
Line, ε is sample axial strain in formula, and s is specimen height, and s' is sample axial displacement knots modification；Fitted according to step 4
Force-time curve, by formulaStress time curve can be obtained, σ is sample axial stress in formula, F is sample institute
It is stressed, R is cylinder sample radius；
Step 6, according to formulaDerivation is carried out to step 5 gained strain-time graph, you can acquisition strain rate-
Time graph；
Step 7, according to step 5 gained stress time curve, step 6 gained strain-time, least square fitting goes out
Load-deformation curve.
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| 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 |
| 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 |
| 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 |
| CN110514581B (en) * | 2019-09-10 | 2021-08-31 | 哈尔滨工业大学 | Viscous medium mechanical property evaluation device and evaluation method |
| CN112432604B (en) * | 2020-10-30 | 2022-05-24 | 西安近代化学研究所 | Rotary dynamic strain testing system and method for winding and coating propellant grains |
| 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 |
| 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 |
| 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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| US4523475A (en) * | 1983-09-19 | 1985-06-18 | The United States Of America As Represented By The Secretary Of The Air Force | Simultaneous incremental strain/incremental temperature analog device for, and method, of testing for stress response |
| US5038295A (en) * | 1989-12-28 | 1991-08-06 | The United States Of America As Represented By The Secretary Of The Air Force | Solid propellant service life analysis via nondestructive testing |
| CN103217335B (en) * | 2012-10-12 | 2015-05-06 | 湖北航天化学技术研究所 | Method for rapidly detecting main curve of tensile strength for unidirectional stretching of solid propellant |
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