CN104614483A - Solid propellant combustion characteristic experimental system - Google Patents
Solid propellant combustion characteristic experimental system Download PDFInfo
- Publication number
- CN104614483A CN104614483A CN201510041082.9A CN201510041082A CN104614483A CN 104614483 A CN104614483 A CN 104614483A CN 201510041082 A CN201510041082 A CN 201510041082A CN 104614483 A CN104614483 A CN 104614483A
- Authority
- CN
- China
- Prior art keywords
- solid propellant
- output unit
- moment output
- testing system
- property testing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Landscapes
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention discloses a solid propellant combustion characteristic experimental system which comprises a torque output device; the output shaft of the torque output device is connected with a solid propellant through an extrusion device; the torque output device drives the extrusion device to realize compression or drawing of the solid propellant; the torque output device is also connected with a control host through a data acquisition unit; the data acquisition unit is used for acquiring deformation information of the solid propellant; the control host is used for receiving the deformation information sent by the data acquisition unit, and adjusting the amount of compression or drawing, generated by the torque output device, of the solid propellant according to the received deformation information; a combustion chamber is arranged outside the solid propellant and the extrusion device hermetically; an image collection device used for collecting the combustion state of the solid propellant is arranged on the combustion chamber. The problems that in the prior art, the performance test of the solid propellant cannot be simulated under the stress action, and the real working condition cannot be accurately simulated to research the combustion characteristics are solved.
Description
Technical field
The invention belongs to rocket engine propellant experimental technique field, relate to SOLID PROPELLANT COMBUSTION property testing system.
Background technology
Research means at present for the Actual combustion performance of propellant under different stress loading, different deformation condition and rule still compares shortage.There is no when loading stress accurate to propellant, carry out the device of combustion experiment.Generally to the research method of problems is mainly independent, burning performance experiment is carried out to propellant, or propellant combustion or structure carry out numerical evaluation.
Propellant mainly stores through nature or artificial acceleration by the more typical test method about problems, then carries out physical property and Mechanics Performance Testing, as fired the performance tests such as speed, density and tensile strength to propellant sampling.The weak point of this method can not simulate propellant to carry out performance test under effect of stress, cannot Reality simulation operating mode accurately.
More typical numerical computation method uses linear viscoelastic model, the stress deformation of operating mode and deformation under research propellant different loads.This method can point out the position of dangerous position in powder column, for practical structures design provides certain reference.Weak point does not consider burning, do not have experimental data to test to it simultaneously.
Summary of the invention
The object of this invention is to provide a kind of solid propellant stress combustion characteristics experimental system, solid propellant can not be simulated under effect of stress, carry out performance test to solve in prior art, Reality simulation operating mode cannot carry out the problem of combustion characteristics research accurately.
The technical solution adopted in the present invention is, SOLID PROPELLANT COMBUSTION property testing system, comprise moment output unit, the output shaft of moment output unit is connected with solid propellant by pressurizing unit, and moment output unit drives pressurizing unit realization to the compression of solid propellant or stretching; Moment output unit is also connected with main control system by data collector, and data collector is for gathering the deformation data of solid propellant; The deformation data that main control system sends for receiving data collector, and adjust moment output unit to the decrement of solid propellant or amount of tension according to the deformation data received; The outside seal of solid propellant and pressurizing unit is provided with combustion chamber, and combustion chamber is provided with the image collecting device for gathering SOLID PROPELLANT COMBUSTION state.
Further, pressurizing unit comprises the leading screw be connected with moment output unit output shaft, the free end of leading screw is connected with the fixing rear fixed plate in maneuvering board, solid propellant and position in turn, solid propellant is clamped by rear fixed plate and maneuvering board, moment output unit drive successively leading screw and maneuvering board reciprocating relative to rear fixed plate to realize the compression of solid propellant or stretching.
Further, maneuvering board is provided with front shoe near the side of moment output unit, and connected by two parallel guide rails between front shoe and rear fixed plate, maneuvering board can be reciprocating along guide rail.
Further, data collector comprises and pasting on solid propellant for gathering the foil gauge of its deformation data and be connected to the strain signal receiver of main control system.
Further, data collector also comprises displacement transducer, and the read head of displacement transducer is close to maneuvering board, displacement transducer by read head gather solid propellant by compression or stretch time produce deformation quantity.
Further, moment output unit is motor, and data collector comprises and being arranged on motor for gathering the motor encoder of motor corner and rotating speed.
Further, leading screw is connected to the output shaft of moment output unit successively by hinge and shaft coupling, moment output unit is connected on the fixing base in position by slide block guide rail mechanism, and moment output unit realizes the straight reciprocating motion relative to base by slide block guide rail mechanism.
Further, the side of combustion chamber is connected with the jet pipe for discharging burning gases.
Further, image collecting device is included in the view window that combustion chamber outer wall is offered, and at the other high-speed camera arranged of view window.
The invention has the beneficial effects as follows, the accurate control of the amount of drawing high arbitrarily to solid propellant or decrement can be realized by moment output unit, propellant is enable to carry out burning performance experiment under the stress loading and deformation quantity of regulation, and can 0.002mm be reached to the control accuracy of solid propellant deformation quantity, this invention has filled up solid propellant when being compressed or draw high, the blank of burning performance experimental study.
Accompanying drawing explanation
Fig. 1 is the structural representation of SOLID PROPELLANT COMBUSTION property testing system of the present invention.
In figure, 1. base, 5. motor, 6. motor encoder, 7. shaft coupling, 8. hinge, 9. displacement transducer, 10. read head, 11. main control systems, 13. strain signal receivers, 14. combustion chambers, 15. view windows, 16. jet pipes, 17. solid propellants, 18. rear fixed plates, 20. maneuvering boards, 21. guide rails, 22. front shoes, 23. leading screws, 24. high-speed cameras.
Embodiment
Below in conjunction with the drawings and specific embodiments, the present invention is described in detail.
The invention provides a kind of SOLID PROPELLANT COMBUSTION property testing system, as shown in Figure 1, comprise moment output unit, the output shaft of moment output unit is connected with solid propellant 17 by pressurizing unit, and moment output unit drives pressurizing unit realization to the compression of solid propellant 17 or stretching; Moment output unit is also connected with main control system 11 by data collector, and data collector is for gathering the deformation data of solid propellant 17; The deformation data that main control system 11 sends for receiving data collector, and adjust moment output unit to the decrement of solid propellant 17 or amount of tension according to the deformation data received; The outside seal of solid propellant 17 and pressurizing unit is provided with combustion chamber 14, and combustion chamber 14 is provided with the image collecting device for gathering solid propellant 17 fired state.
Wherein, pressurizing unit comprises the leading screw 23 be connected with moment output unit output shaft, the free end of leading screw 23 is connected with the fixing rear fixed plate 18 in maneuvering board 20, solid propellant 17 and position in turn, solid propellant 17 is clamped by rear fixed plate 18 and maneuvering board 20, moment output unit drive successively leading screw 23 and maneuvering board 20 reciprocating relative to rear fixed plate 18 to realize the compression of solid propellant 17 or stretching.
Leading screw 23 is connected to the output shaft of motor 5 successively by hinge 8 and shaft coupling 7, motor 5 is connected on the fixing base 1 in position by slide block guide rail mechanism, and motor 5 realizes the straight reciprocating motion relative to base 1 by slide block guide rail mechanism.
With hinge 8, motor is connected with leading screw 23, opens motor 5 supply power 220V, use solid propellant 17 deformation quantity controlling touch-screen 12 input and need, control motor 5 and move, make the deformation quantity of solid propellant 17 reach experimental design requirement by leading screw 23.And then disconnecting the connection of hinge 8 and leading screw 23, sealing combustion chamber 14 takes fire experiment, uses high-speed camera 24 to burn image at view window 15 place record.
Maneuvering board 20 is provided with front shoe 22 near the side of motor 5, and connected by two parallel guide rails 21 between front shoe 22 and rear fixed plate 18, maneuvering board 20 can be reciprocating along guide rail 21.
Leading screw 23 and the joint of maneuvering board 20 use 51104 type single direction thrust ball bearings to be connected, and use LB10192 type linear ball bearing to connect between maneuvering board 20 and guide rail 21.Solid propellant 17 is fixed between maneuvering board 20 and fixed head 18, and is slightly clamped by solid propellant 17.
Moment output unit is generally motor 5, and main control system 11 is connected with touch-screen, uses NOVA MCX314 motion control chip 6 to be connected 11 with PC main control system.Motor 5 realizes presetting solid propellant 17 shape strain and stress by main control system 11 or touch-screen.Use hinge 8 to drive leading screw 23, the rotation of motor 5 is converted into the translation of leading screw 23, leading screw 23 brought into motion plate 20 applies stress loading to solid propellant 17.Solid propellant 17 both sides are fixedly connected between maneuvering board 20 and rear fixed plate 18, maneuvering board 20 can near or away from the motion of solid propellant 17 direction, to realize compression to solid propellant 17 or stretching.
After the stress loading applied solid propellant 17 is satisfied the demand, leading screw 23 can be separated with hinge 8, be passed to motor 5 to avoid high temperature violent in combustion chamber 14 and make it burn.Meanwhile, by the appropriate design to leading screw 23 lead angle, the heterodromous self-locking of maneuvering board 20 can be realized.
The side of combustion chamber 14 is connected with the jet pipe 16 for discharging burning gases, the case material of combustion chamber 14 adopts 45# steel, overall length 360mm, image collecting device is included in the view window 15 that combustion chamber 14 outer wall is offered, and at the outer high-speed camera 24 arranged of view window 15.
The combustion chamber 14 placing solid propellant 17 can be airtight form burner or interrupted-burning test device.Combustion chamber 14 can control the operating pressure of combustion chamber 14 by the larynx footpath size of the jet pipe 16 connected outside it, uses high-speed camera 24 to carry out record to combustion process, for the observation analysis to fired state at view window 15 place in combustion process.
In combustion characteristics experiment, key job parameter is solid propellant 17 stress loading, deformation quantity and deformation course etc.Novel high-precision moment output unit provides stress accurately to export and shape control to propellant, and concrete control procedure is as follows:
Moment output unit uses high-precision motor 5 as propulsion system, and its loading force is that 0 ~ 1000N is adjustable, and load keeps precision to be better than 1% of reading, and displacement absolute precision is not less than 2 μm, can meet in experiment and export needs to the load of propellant.
Data collector comprises to be pasted on solid propellant 17 for gathering the foil gauge of its deformation data and being connected to the strain signal receiver 13 of main control system 11.In order to ensure that solid propellant 17 starts the accurate judgement compressed or stretch, carry out pasting foil gauge on solid propellant 17 surface, the compliance voltage signal of foil gauge is by feeding back to main control system 11 after strain signal receiver 13 amplification.
Data collector also comprises displacement transducer 9, and the read head 10 of displacement transducer 9 is close to maneuvering board 20, displacement transducer 9 by read head 10 gather solid propellant 17 by compression or stretch time produce deformation quantity.The TR/TRS Series grating scale displacement transducer using measuring accuracy to reach 0.002mm is measured as the deformation of displacement transducer 9 pairs of solid propellants 17.Grating displacement sensor read head 10 is by measuring the shift value before and after solid propellant 17 deformation, and then obtain the deformation values of solid propellant 17, and this deformation values is transmitted back to main control system 11 by displacement transducer 9, main control system 11 sends pulse signal instruction according to this deformation values to motor 5, control motor 5 to move forward or backwards, the stress loading of adjustment maneuvering board 20 pairs of solid propellants 17.
Data collector also comprises and being arranged on motor 5 for gathering the motor encoder 6 of motor 5 corner and rotating speed.Main control system 11 receives the signal from motor encoder 6, and the data of two signals motor encoder 6 and displacement transducer 9 received contrast, self can verify displacement, carry out the correction of displacement, thus ensure precision and the accuracy of maneuvering board 20 displacement, and ensure the shape strain and stress of solid propellant 17.So mutually verified by motor encoder 6 and displacement transducer 9, form closed loop and accurately control, reliable full accuracy can be provided to reach the deformation quantity control accuracy of 2 μm.
The use procedure of SOLID PROPELLANT COMBUSTION property testing system of the present invention is, first apply stress loading by moment output unit drive leading screw 23, maneuvering board 20 pairs of solid propellants 17, stress loading, the data such as deformation quantity and deformation course of solid propellant 17 are obtained again by foil gauge, displacement transducer 9 and motor encoder 6, and by this data feedback to main control system 11 in order to export the stress of moment output unit and the deformation of solid propellant 17 controls, to ensure the control accuracy to solid propellant 17 deformation quantity; Then be separated with leading screw 23 by hinge 8, lighted by the solid propellant 17 be sealed in combustion chamber 14, record fired state by high-speed camera 24, the gas that burning produces is discharged from trunnion 16.
SOLID PROPELLANT COMBUSTION property testing system of the present invention controls convenient, simple to operate.The accurate control of the amount of drawing high arbitrarily to solid propellant 17 or decrement can be realized by moment output unit.Make solid propellant 17 can carry out burning performance experiment under the stress loading of regulation and deformation quantity.And the present invention can reach 0.002mm to propellant deformation quantity control accuracy.The present invention has filled up propellant when being compressed or draw high, the blank of burning performance experimental study.
Claims (9)
1. SOLID PROPELLANT COMBUSTION property testing system, it is characterized in that, comprise moment output unit, the output shaft of described moment output unit is connected with solid propellant (17) by pressurizing unit, and described moment output unit drives pressurizing unit realization to the compression of solid propellant (17) or stretching;
Described moment output unit is also connected with main control system (11) by data collector, and described data collector is for gathering the deformation data of solid propellant (17); The deformation data that described main control system (11) sends for receiving data collector, and adjust moment output unit to the decrement of solid propellant (17) or amount of tension according to the described deformation data received;
Described solid propellant (17) and the outside seal of pressurizing unit are provided with combustion chamber (14), and described combustion chamber (14) is provided with the image collecting device for gathering solid propellant (17) fired state.
2. SOLID PROPELLANT COMBUSTION property testing system as claimed in claim 1, it is characterized in that, described pressurizing unit comprises the leading screw (23) be connected with moment output unit output shaft, the free end of described leading screw (23) is connected with maneuvering board (20) in turn, the rear fixed plate (18) that solid propellant (17) and position are fixed, described solid propellant (17) is by rear fixed plate (18) and maneuvering board (20) clamping, described moment output unit drive successively leading screw (23) and maneuvering board (20) reciprocating relative to rear fixed plate (18) to realize the compression of solid propellant (17) or stretching.
3. SOLID PROPELLANT COMBUSTION property testing system as claimed in claim 2, it is characterized in that, at described maneuvering board (20), the side of moment output unit is provided with front shoe (22), connected by two parallel guide rails (21) between described front shoe (22) and rear fixed plate (18), described maneuvering board (20) can be reciprocating along guide rail (21).
4. as the SOLID PROPELLANT COMBUSTION property testing system in claims 1 to 3 as described in any one, it is characterized in that, described data collector comprises to be pasted on solid propellant (17) for gathering the foil gauge of its deformation data and being connected to the strain signal receiver (13) of main control system (11).
5. SOLID PROPELLANT COMBUSTION property testing system as claimed in claim 4, it is characterized in that, described data collector also comprises displacement transducer (9), the read head (10) of described displacement transducer (9) is close to maneuvering board (20), described displacement transducer (9) by read head (10) gather solid propellant (17) by compression or stretch time produce deformation quantity.
6. SOLID PROPELLANT COMBUSTION property testing system as claimed in claim 5, it is characterized in that, described moment output unit is motor (5), and described data collector comprises and being arranged on motor (5) for gathering the motor encoder (6) of motor (5) corner and rotating speed.
7. SOLID PROPELLANT COMBUSTION property testing system as claimed in claim 2 or claim 3, it is characterized in that, described leading screw (23) is connected to the output shaft of moment output unit successively by hinge (8) and shaft coupling (7), described moment output unit is connected on the fixing base (1) in position by slide block guide rail mechanism, and described moment output unit realizes the straight reciprocating motion relative to base (1) by slide block guide rail mechanism.
8. SOLID PROPELLANT COMBUSTION property testing system as claimed in claim 1 or 2, it is characterized in that, the side of described combustion chamber (14) is connected with the jet pipe (16) for discharging burning gases.
9. SOLID PROPELLANT COMBUSTION property testing system as claimed in claim 1 or 2, it is characterized in that, described image collecting device is included in the view window (15) that combustion chamber (14) outer wall is offered, and at the other high-speed camera (24) arranged of view window (15).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510041082.9A CN104614483B (en) | 2015-01-27 | 2015-01-27 | SOLID PROPELLANT COMBUSTION property testing system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510041082.9A CN104614483B (en) | 2015-01-27 | 2015-01-27 | SOLID PROPELLANT COMBUSTION property testing system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104614483A true CN104614483A (en) | 2015-05-13 |
| CN104614483B CN104614483B (en) | 2016-05-11 |
Family
ID=53149025
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510041082.9A Expired - Fee Related CN104614483B (en) | 2015-01-27 | 2015-01-27 | SOLID PROPELLANT COMBUSTION property testing system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104614483B (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105201689A (en) * | 2015-09-09 | 2015-12-30 | 西北工业大学 | Variable-geometry RBCC (rocket based combined cycle) engine for ground experiment |
| CN105466498A (en) * | 2016-01-12 | 2016-04-06 | 清华大学 | Material three-dimensional deformation and temperature synchronous measurement and control device and method under high temperature environments |
| CN105974049A (en) * | 2016-05-06 | 2016-09-28 | 西北工业大学 | Apparatus and method for measuring instantaneous burning rate of solid propellant |
| CN109521142A (en) * | 2019-01-07 | 2019-03-26 | 大连理工大学 | A kind of device and method for the measurement solid propellant velocity of sound under the conditions of pressure change |
| CN110412205A (en) * | 2019-07-05 | 2019-11-05 | 安徽建筑大学 | A kind of solid material combustion measurement device |
| CN113075353A (en) * | 2021-04-01 | 2021-07-06 | 上海交通大学 | Solid propellant combustion testing device |
| CN113075352A (en) * | 2021-04-01 | 2021-07-06 | 上海交通大学 | Solid propellant combustion testing device |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS639861A (en) * | 1986-06-30 | 1988-01-16 | Nippon Steel Corp | Method and instrument for analyzing carbon of solid sample |
| CN101285747A (en) * | 2008-04-25 | 2008-10-15 | 哈尔滨工业大学 | In situ nanometer stretching experiment measuring detection device |
| CN102519817A (en) * | 2011-12-28 | 2012-06-27 | 上海大学 | Reciprocating motion friction experiment device |
| CN203350235U (en) * | 2013-07-31 | 2013-12-18 | 湖北航天化学技术研究所 | Propellant burning speed test device |
| CN104020250A (en) * | 2014-06-24 | 2014-09-03 | 西安近代化学研究所 | Propellant powder volume variation combustion speed testing device |
| CN104075948A (en) * | 2014-07-03 | 2014-10-01 | 中国工程物理研究院化工材料研究所 | Test method of tensile and compression strength of explosive under temperature condition higher than 100 DEG C |
-
2015
- 2015-01-27 CN CN201510041082.9A patent/CN104614483B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS639861A (en) * | 1986-06-30 | 1988-01-16 | Nippon Steel Corp | Method and instrument for analyzing carbon of solid sample |
| CN101285747A (en) * | 2008-04-25 | 2008-10-15 | 哈尔滨工业大学 | In situ nanometer stretching experiment measuring detection device |
| CN102519817A (en) * | 2011-12-28 | 2012-06-27 | 上海大学 | Reciprocating motion friction experiment device |
| CN203350235U (en) * | 2013-07-31 | 2013-12-18 | 湖北航天化学技术研究所 | Propellant burning speed test device |
| CN104020250A (en) * | 2014-06-24 | 2014-09-03 | 西安近代化学研究所 | Propellant powder volume variation combustion speed testing device |
| CN104075948A (en) * | 2014-07-03 | 2014-10-01 | 中国工程物理研究院化工材料研究所 | Test method of tensile and compression strength of explosive under temperature condition higher than 100 DEG C |
Non-Patent Citations (4)
| Title |
|---|
| 胡松启等: "复合推进剂应变条件下燃速变化实验研究", 《固体火箭技术》 * |
| 胡松启等: "复合推进剂应变条件下燃速变化实验研究", 《固体火箭技术》, vol. 36, no. 2, 30 April 2013 (2013-04-30) * |
| 胡松启等: "复合推进剂拉伸应变条件下燃速变化计算分析", 《固体火箭技术》 * |
| 范徽等: "基于FPGA的推进剂药柱应变测试装置研究", 《测控技术》 * |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105201689A (en) * | 2015-09-09 | 2015-12-30 | 西北工业大学 | Variable-geometry RBCC (rocket based combined cycle) engine for ground experiment |
| CN105466498A (en) * | 2016-01-12 | 2016-04-06 | 清华大学 | Material three-dimensional deformation and temperature synchronous measurement and control device and method under high temperature environments |
| CN105974049A (en) * | 2016-05-06 | 2016-09-28 | 西北工业大学 | Apparatus and method for measuring instantaneous burning rate of solid propellant |
| CN105974049B (en) * | 2016-05-06 | 2018-01-16 | 西北工业大学 | A kind of device and measuring method for measuring the instantaneous burn rate of solid propellant |
| CN109521142A (en) * | 2019-01-07 | 2019-03-26 | 大连理工大学 | A kind of device and method for the measurement solid propellant velocity of sound under the conditions of pressure change |
| CN110412205A (en) * | 2019-07-05 | 2019-11-05 | 安徽建筑大学 | A kind of solid material combustion measurement device |
| CN113075353A (en) * | 2021-04-01 | 2021-07-06 | 上海交通大学 | Solid propellant combustion testing device |
| CN113075352A (en) * | 2021-04-01 | 2021-07-06 | 上海交通大学 | Solid propellant combustion testing device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104614483B (en) | 2016-05-11 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104614483B (en) | SOLID PROPELLANT COMBUSTION property testing system | |
| CN103175728B (en) | The power true triaxil tester of soil | |
| CN106525577B (en) | Test the device and method of material dynamic mechanical performance under stretching/shearing Combined Loading | |
| WO2018195919A1 (en) | Intelligent numerically-controlled extra-high pressure true three-dimensional non-uniform loading and unloading and pressure regulating model test system | |
| CN108226441B (en) | Quantitative simulation test system and method capable of realizing rock-door roadway tunneling induction coal and gas outburst | |
| CN108982264B (en) | P-y curve measuring device based on soil body shear band development | |
| CN109001051A (en) | Seepage experimental apparatus and its method are sheared suitable for the L-type of joint or crack rock | |
| CN201983985U (en) | Device for measuring thickness and pressure of multi-component fiber battery separator under moist state | |
| CN107101881B (en) | The impact experiment apparatus and its experimental method of a kind of brace pre axial force, moment of flexure | |
| CN105865922B (en) | Double track tunnel excavates face and unloading model is added to test system | |
| CN105606453A (en) | Experimental test system for axial compression property of large-size composite lenticular tube | |
| CN110243513A (en) | Ball screw assembly, efficiency detection device | |
| Reddy et al. | Development of a true triaxial testing apparatus | |
| Choi et al. | Development of a true triaxial apparatus for sands and gravels | |
| CN202153223U (en) | Simulated loading and measurement system for complex deformation of geologic soft material | |
| CN106840919A (en) | A kind of Rock And Soil direct shear test instrument for quick and precisely pressurizeing | |
| CN113310799A (en) | In-situ mechanics dynamic observation equipment under ultralow strain rate | |
| CN112326476A (en) | Testing method and device for rock multi-field coupling rheological test under action of dynamic load | |
| CN209148460U (en) | Penetration stress test system based on Hopkinson bar | |
| CN105675205B (en) | Vacuum thrust original position self-checking device | |
| CN111257163A (en) | Aircraft landing gear buffer oil liquid gas solubility test device and test method thereof | |
| CN114659897A (en) | Solid propellant confining pressure in-situ tensile test device and test method | |
| CN104237118A (en) | Novel micro-control dynamic friction coefficient tester | |
| CN111413026B (en) | On-line detection device of multifunctional pressure measurement monitoring system | |
| CN206362626U (en) | A kind of high polymer dehumidification point device for accurately measuring |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160511 Termination date: 20170127 |