CN112304759A - Solid propellant stretching device based on synchrotron radiation test - Google Patents
Solid propellant stretching device based on synchrotron radiation test Download PDFInfo
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- CN112304759A CN112304759A CN202011158435.0A CN202011158435A CN112304759A CN 112304759 A CN112304759 A CN 112304759A CN 202011158435 A CN202011158435 A CN 202011158435A CN 112304759 A CN112304759 A CN 112304759A
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- 238000012360 testing method Methods 0.000 title claims abstract description 24
- 239000004449 solid propellant Substances 0.000 title claims abstract description 22
- 230000005469 synchrotron radiation Effects 0.000 title claims abstract description 12
- 239000011521 glass Substances 0.000 claims abstract description 35
- 230000004323 axial length Effects 0.000 claims description 4
- 238000000034 method Methods 0.000 abstract description 5
- 230000008569 process Effects 0.000 abstract description 5
- 238000009864 tensile test Methods 0.000 abstract description 5
- 230000001360 synchronised effect Effects 0.000 abstract description 4
- 230000008859 change Effects 0.000 abstract description 2
- 239000003814 drug Substances 0.000 description 4
- 239000003380 propellant Substances 0.000 description 4
- 238000011065 in-situ storage Methods 0.000 description 3
- 238000005096 rolling process Methods 0.000 description 3
- 230000005855 radiation Effects 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- GDDNTTHUKVNJRA-UHFFFAOYSA-N 3-bromo-3,3-difluoroprop-1-ene Chemical compound FC(F)(Br)C=C GDDNTTHUKVNJRA-UHFFFAOYSA-N 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 239000011230 binding agent Substances 0.000 description 1
- 238000004140 cleaning Methods 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 230000003111 delayed effect Effects 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000009472 formulation Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 description 1
- 239000000843 powder Substances 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000002216 synchrotron radiation X-ray diffraction Methods 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/08—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/02—Details
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/02—Details
- G01N3/04—Chucks
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2203/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N2203/0014—Type of force applied
- G01N2203/0016—Tensile or compressive
- G01N2203/0017—Tensile
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- Physics & Mathematics (AREA)
- Health & Medical Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Chemical & Material Sciences (AREA)
- Analytical Chemistry (AREA)
- Biochemistry (AREA)
- General Health & Medical Sciences (AREA)
- General Physics & Mathematics (AREA)
- Immunology (AREA)
- Pathology (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention provides a solid propellant stretching device based on synchrotron radiation test, wherein a sensor fixing support and a base are fixed on a bottom plate, a tension sensor is fixedly arranged on the upper surface of the sensor fixing support, an inner glass cover is arranged in two thirds of circular grooves of the base and a top cover, and an outer glass cover is arranged in a whole circle of circular grooves of the base and the top cover and can slide; the upper clamp and the lower clamp two ends of a test piece; the upper fixture penetrates through the top cover, the upper end of the upper fixture is connected with the head of the stepping motor push rod in a matched mode, the stepping motor push rod is fixedly connected with the stepping motor support, and the stepping motor support is fixedly installed on the top cover. The invention drives the upper clamp tensile test piece to move along the axial direction of the push rod of the stepping motor through the push rod of the stepping motor, can realize stepless speed change in the pulling-up process and has better accuracy. The invention can avoid the deflection of the clamp in the stretching process and ensure that the center of the test piece is in the test area of the synchronous light source.
Description
Technical Field
The invention relates to a solid propellant stretching device based on synchrotron radiation testing, belongs to the technical field of solid propellant testing, and is used for mechanical property research of solid propellants.
Background
At present, microscopic damage tests of propellants in a stretching state are mostly carried out through a scanning electron microscope, but the scanning electron microscope can only observe the surface condition of the propellants and does not have real-time performance, and synchronous radiation X rays can realize in-situ observation of dynamic processes of propellant damage generation and evolution, so that an in-situ stretching device of the solid propellants needs to be designed based on a synchronous radiation platform. Chinese patent 201320673859.X proposes "a synchrotron radiation X-ray diffraction normal position stretching device", including the bottom plate, a pedestal, the push rod, linear bearing, servo motor, the cam, the rolling bearing axle, the connecting rod, a spring, the bottom plate passes through the cross gomphosis of bottom on the platform of synchrotron radiation light source, the base is fixed at the bottom plate center, the push rod passes through linear bearing and installs two walls about the base, servo motor installs in bottom plate upper surface left side, the cam is installed on servo motor axle, the left end trompil of push rod links to each other with the rolling bearing axle, rolling bearing and cam right side edge contact, the push rod middle part is articulated with the connecting rod lower extreme, the right-hand member of push rod passes through the spring.
When the stretching device works, the data processing and control system controls the servo motor to rotate at a certain frequency to drive the cam to rotate, and then the lower clamp is driven by the push rod, the connecting rod and the driven rod to reciprocate up and down to apply numerical reciprocating displacement load to the sample.
The in-situ stretching apparatus disclosed in this document has the following drawbacks:
1. the lower clamp is moved by driving the push rod, the connecting rod and the driven rod through the cam, and friction force exists between the rods, so that the movement of the clamp is delayed when the cam rotates; furthermore the distance the clamp moves is limited by the cam shape, which requires replacement of the cam to achieve when changing the strain of the test conditions.
2. The organic glass of individual layer passes through the fix with screw between base and the apron, need dismantle parts such as apron and tension sensor when changing the sample, and the execution needs the more time of spending.
Disclosure of Invention
In order to solve the problems in the prior art, the invention provides a solid propellant stretching device based on synchrotron radiation testing, which comprises a stepping motor push rod, a stepping motor support, a top cover, an outer glass cover, an inner glass cover, a sensor fixing support, a base, a bottom plate, an upper clamp, a lower clamp, a clamp head, a lock catch and a tension sensor.
Sensor fixed bolster and base all pass through the fix with screw on the bottom plate, and force sensor passes through the fixed surface of bolt and sensor fixed bolster, and interior glass cover is placed in the two-thirds circular slot on base up end and top cap lower surface, and outer glass cover is placed in the whole circle circular slot on base up end and top cap lower surface, and can slide in whole circle circular slot. The upper clamp and the upper clamp head are connected through a lock catch, the lower clamp and the lower clamp head are connected through a lock catch, the lower clamp is fixedly connected with the upper surface of the tension sensor through a bolt, the upper clamp penetrates through the top cover and the upper end of the upper clamp to be processed with an external thread and is connected with the internal thread of the head of a push rod of the stepping motor in a matched mode, the push rod of the stepping motor is connected with a support of the stepping motor through a screw, and the support of the stepping motor is connected with the upper surface of the top cover.
Advantageous effects
(1) The invention drives the upper clamp tensile test piece to move along the axial direction of the push rod of the stepping motor through the push rod of the stepping motor, and has better accuracy.
(2) The invention can realize stepless speed change in the pulling-up process by driving the upper clamp to move along the axial line direction of the push rod of the stepping motor through the push rod of the stepping motor.
(3) The cross section of the upper clamp is square and is matched with the top cover, so that the clamp can be effectively prevented from deflecting in the stretching process, and the center of the test piece is ensured to be positioned in a test area of a synchronous light source.
(4) The invention designs the inner glass cover and the outer glass cover, the outer glass cover can rotate 360 degrees, and the test sample is convenient to replace.
Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.
Drawings
The above and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
fig. 1 is a front sectional view of a solid propellant drawing apparatus of the present invention.
Fig. 2 is a top view of the base plate.
FIG. 3 is a front view of the base plate
FIG. 4 is a three-dimensional view of a base
FIG. 5 is a front sectional view of the base
FIG. 6 is a left side cross-sectional view of the base
FIG. 7 is a top view of the base
FIG. 8 is a three-dimensional view of a sensor mounting bracket
FIG. 9 is a front cross-sectional view of a sensor mount bracket
FIG. 10 is a top view of a sensor mount bracket
FIG. 11 is a three-dimensional view of the lower clamp
FIG. 12 is a front sectional view of the lower clamp
FIG. 13 is a right sectional view of the lower clamp
FIG. 14 is a three-dimensional view of a gripper head
FIG. 15 is a three-dimensional view of the upper clamp
FIG. 16 is a front sectional view of the upper clamp
FIG. 17 is a right sectional view of the upper clamp
FIG. 18 is a three-dimensional view of the top cover
FIG. 19 is a front cross-sectional view of the top cover
FIG. 20 is a bottom view of the top cover
FIG. 21 is a three-dimensional view of a stepper motor bracket
FIG. 22 is a front cross-sectional view of a stepper motor bracket
FIG. 23 is a top view of a stepper motor bracket
FIG. 24 is a three-dimensional view of the outer glass cover
FIG. 25 is a three-dimensional view of the inner glass cover
In FIG. 1, 1-a stepping motor push rod, 2-a stepping motor support, 3-a top cover, 4-an upper clamp, 5-a clamp head, 6-a lock catch, 7-a tensile test piece, 8-a lower clamp, 9-a base, 10-a tension sensor, 11-a sensor fixing support, 12-a bottom plate, 13-an outer glass cover and 14-an inner glass cover.
Detailed Description
The following detailed description of embodiments of the invention is intended to be illustrative, and not to be construed as limiting the invention.
The solid propellant stretching device based on synchrotron radiation test provided in this embodiment comprises step motor push rod 1, step motor support 2, top cap 3, go up anchor clamps 4, anchor clamps head 5, hasp 6, lower anchor clamps 8, base 9, tension sensor 10, sensor fixed bolster 11, bottom plate 12, outer glass cover 13, interior glass cover 14.
The bottom plate 12 is a square structure, and 8M 4X 1 threaded through holes and 4 circular through holes with the diameter of 5mm are formed in the bottom plate 12.
The outer contour of the sensor fixing support 11 is a cylindrical structure, 4 circular through holes uniformly distributed along the circumference are formed in the upper surface of the sensor fixing support and are used for being connected with the tension sensor 10 through bolts, and the lower end of the sensor fixing support 11 is of a flange structure and is connected with the bottom plate 12 through 4M 4 multiplied by 1 screws.
The profile of base 9 is the pipe form, and the lower extreme is the flange structure, is connected with bottom plate 12 through 4M 4X 1's screw, the upper surface of base 9 has 2 different ring channels of diameter, and wherein the great ring channel of diameter is complete annular, and the less inboard ring channel of diameter is two-thirds annular.
The lower clamp 8 is composed of a cylindrical base, a connecting rod and a lower clamp semi-cylinder from bottom to top. The cylindrical base is fixedly connected with the upper surface of the tension sensor through 4M 4 multiplied by 1 screws; the connecting rod is a thin cylindrical rod and is coaxially fixed on the top surface of the cylindrical base; the lower clamp semi-cylinder is fixed at the top end of the connecting rod in a welding mode and the like, and the rotation axis of the lower clamp semi-cylinder deviates from the axis of the connecting rod; and a round hole vertical to the rectangular surface is formed on the semi-cylindrical rectangular surface of the lower clamp.
The clamp head 5 consists of a fixed semi-cylinder and a cylinder vertical to the rectangular surface of the fixed semi-cylinder, the radius of the fixed semi-cylinder is equal to that of a lower clamp semi-cylinder in the lower clamp 8, and the axial length is equal to that of the lower clamp semi-cylinder; the position and the size of a cylinder vertical to the fixed semi-cylindrical rectangular surface are matched with the round hole of the semi-cylindrical rectangular surface of the lower clamp in the lower clamp 8.
The lock catch 6 consists of an elastic round pipe with a notch and a fixing piece at the notch position; the inner diameter of the elastic circular tube is equal to the radius of the fixed semi-cylinder, and the axial length of the elastic circular tube is equal to that of the fixed semi-cylinder. The lock catch 6 can be sleeved outside the combination of the clamp head 5 and the lower clamp semi-cylinder of the lower clamp 8, and the clamp head 5 and the lower clamp semi-cylinder of the lower clamp 8 are fastened through installing a bolt in a fastening hole in the fixing sheet.
Through the cooperation of the lower clamp semi-cylinder of the clamp head 5 and the lower clamp 8, the lower end of the sheet solid propellant tensile test piece 7 can be clamped between the rectangular surfaces of the two, and the clamp head 5 and the lower clamp semi-cylinder of the lower clamp 8 are fastened through the lock catch.
The upper clamp 4 is provided with an upper clamp semi-cylinder and a square rod from bottom to top; the upper clamp semi-cylinder is eccentrically fixed at the lower end of the square rod in a welding mode and the like, the radius of the upper clamp semi-cylinder is equal to that of the fixed semi-cylinder of the clamp head 5, and the axial length is equal to that of the fixed semi-cylinder; and a round hole perpendicular to the rectangular surface is formed in the semi-cylindrical rectangular surface of the upper clamp, and the position and the size of the round hole are matched with those of a cylinder for fixing the semi-cylindrical rectangular surface. The lock catch 6 can be sleeved outside the combination of the clamp head 5 and the upper clamp semi-cylinder of the upper clamp 4, and the clamp head 5 and the upper clamp semi-cylinder of the upper clamp 4 are fastened by installing a bolt in a fastening hole on the fixing sheet. Through the cooperation of the clamp head 5 and the upper clamp semi-cylinder of the upper clamp 4, the upper end of the sheet solid propellant tensile test piece 7 can be clamped between the rectangular surfaces of the clamp head and the upper clamp semi-cylinder of the upper clamp 4, and the clamp head 5 and the upper clamp semi-cylinder of the upper clamp 4 are fastened through the lock catch. The top of the square rod of the upper clamp 4 is provided with a thread section which is used for being connected with the step motor push rod 1.
The top cap 3 is the cake form, and the center has square through hole and the cooperation of the 4 square poles of last anchor clamps, and the lower surface of top cap 3 has the ring channel that corresponds with the upper surface ring channel of base 9, and the great ring channel of diameter is complete annular promptly, and the less ring channel of inboard diameter is two thirds annular, the size of two ring channels of top cap 3 with the ring channel size of base 9 corresponds the same, and complete ring channel width and groove diameter are the same with outer glass cover 13 thickness and diameter, and third ring channel width and groove diameter are the same with interior glass cover 14 thickness and diameter.
The outer glass cover 13 is in a semicircular tubular shape and made of organic glass, and the outer glass cover 13 is assembled and connected with the complete annular grooves of the base 9 and the top cover 3 and can rotate in the complete annular grooves; the inner glass cover 14 is in a shape of two-thirds circular tube and made of organic glass, and the inner glass cover 14 is fixedly connected with two-thirds annular grooves of the base 9 and the top cover 3 in an assembling way.
The solid propellant formulation parameters of this example:
the mass percentages of the components are respectively as follows: 17% of aluminum powder, 13% of a binder system and 70% of ammonium perchlorate.
Based on the solid propellant stretching device, the test method for testing the stress-strain curve of the propellant used in the embodiment is carried out according to the following steps:
(1) preparing medicine cutting: the solid propellant was cut into a dumbbell shape having a thickness of 1mm, a width of 2mm, and a middle test length of 8 mm.
(2) Step motor push rod preparation: the stepper motor push rod is set to a specified movement speed.
(3) Preparing powder charge: the cut medicine is fixed between the upper clamp and the lower clamp through the lock catch.
(4) And (4) checking whether the medicine strip is well fixed, whether torque exists, and whether the assembly and acquisition system among other parts work normally.
(5) The collection device is started.
(6) The stepper motor push rod is started.
(7) And (5) disassembling the medicine strip, and cleaning the clamp to finish the experiment.
Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made in the above embodiments by those of ordinary skill in the art without departing from the principle and spirit of the present invention.
Claims (5)
1. The utility model provides a solid propellant stretching device based on synchrotron radiation test which characterized in that: the device comprises a stepping motor push rod, a stepping motor support, a top cover, an upper clamp, a clamp head, a lock catch, a lower clamp, a base, a tension sensor, a sensor fixing support, a bottom plate, an outer glass cover and an inner glass cover;
the sensor fixing support and the base are fixed on the bottom plate, the tension sensor is fixedly arranged on the upper surface of the sensor fixing support, the inner glass cover is placed in two-thirds circular grooves on the upper end surface of the base and the lower surface of the top cover, and the outer glass cover is placed in a whole circle of circular grooves on the upper end surface of the base and the lower surface of the top cover; the upper clamp and the upper clamp head are connected through a lock catch, the upper clamp and the upper clamp head combination can clamp one end of the sheet-shaped solid propellant test piece, the lower clamp and the lower clamp head are connected through a lock catch, and the lower clamp head combination can clamp the other end of the sheet-shaped solid propellant test piece; the upper end that lower anchor clamps and force sensor go up anchor clamps and pass top cap and go up anchor clamps is processed there is the external screw thread, is connected with the interior screw-thread fit of step motor push rod head, step motor push rod and step motor support fixed connection, and step motor support fixed mounting is on the top cap.
2. The solid propellant stretching device based on the synchrotron radiation test of claim 1, wherein: the upper surface of the base is provided with 2 annular grooves with different diameters, wherein the annular groove with the larger diameter is a complete ring, and the inner annular groove with the smaller diameter is two thirds of a ring; the lower surface of the top cover is provided with 2 annular grooves with different diameters corresponding to the annular groove on the upper surface of the base, wherein the annular groove with the larger diameter is a complete annular groove, and the annular groove on the inner side with the smaller diameter is a two-thirds annular groove; the size of the annular groove of the top cover is correspondingly the same as that of the annular groove of the base, the groove width and the groove diameter of the complete annular groove are correspondingly the same as those of the outer glass cover, and the groove width and the groove diameter of the two-thirds of the annular groove are correspondingly the same as those of the inner glass cover.
3. The solid propellant stretching device based on the synchrotron radiation test of claim 2, wherein: the outer glass cover is in a semicircular tubular shape and made of organic glass, is assembled and connected with the complete annular grooves of the base and the top cover, and can rotate in the complete annular grooves; the inner glass cover is in a two-thirds circular tube shape and made of organic glass, and the inner glass cover is fixedly connected with the two-thirds annular grooves of the base and the top cover in an assembling mode.
4. The solid propellant stretching device based on the synchrotron radiation test of claim 1, wherein: the lower clamp consists of a cylindrical base, a connecting rod and a lower clamp semi-cylinder from bottom to top; the cylindrical base is fixedly connected with the upper surface of the tension sensor; the connecting rod is a thin cylindrical rod and is coaxially fixed on the top surface of the cylindrical base;
the lower clamp semi-cylinder is fixed at the top end of the connecting rod, and the rotation axis of the lower clamp semi-cylinder deviates from the axis of the connecting rod;
a round hole vertical to the rectangular surface is formed on the semi-cylindrical rectangular surface of the lower clamp;
the upper clamp is provided with an upper clamp semi-cylinder and a square rod from bottom to top; the upper clamp semi-cylinder is eccentrically fixed at the lower end of the square rod, and a round hole vertical to the rectangular surface is formed in the rectangular surface of the upper clamp semi-cylinder;
the clamp head consists of a fixed semi-cylinder and a cylinder vertical to the rectangular surface of the fixed semi-cylinder, the radius of the fixed semi-cylinder is the same as that of the lower clamp semi-cylinder and the upper clamp semi-cylinder, and the axial length of the fixed semi-cylinder is equal to that of the lower clamp semi-cylinder and the upper clamp semi-cylinder; the position and the size of a cylinder vertical to the fixed semi-cylindrical rectangular surface are matched with the round hole of the lower clamp semi-cylindrical rectangular surface and the round hole of the upper clamp semi-cylindrical rectangular surface.
5. The solid propellant stretching device based on the synchrotron radiation test of claim 1, wherein: the top of the square rod of the upper clamp is provided with a threaded section which is used for being connected with a stepping motor push rod 1; the center of the top cover is provided with a square through hole which is matched with the square rod of the upper clamp 4.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011158435.0A CN112304759A (en) | 2020-10-26 | 2020-10-26 | Solid propellant stretching device based on synchrotron radiation test |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011158435.0A CN112304759A (en) | 2020-10-26 | 2020-10-26 | Solid propellant stretching device based on synchrotron radiation test |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114018713A (en) * | 2022-01-10 | 2022-02-08 | 北京理工大学 | Accelerated aging test device and method for solid propellant |
| CN114942185A (en) * | 2022-04-13 | 2022-08-26 | 北京理工大学 | In-situ mechanical loading testing machine, testing system and testing method |
| KR102630897B1 (en) * | 2023-09-13 | 2024-01-30 | 국방기술품질원 | Solid propellant specimen fixing jig for stress relaxation test and test apparatus using the same |
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| CN114942185A (en) * | 2022-04-13 | 2022-08-26 | 北京理工大学 | In-situ mechanical loading testing machine, testing system and testing method |
| KR102630897B1 (en) * | 2023-09-13 | 2024-01-30 | 국방기술품질원 | Solid propellant specimen fixing jig for stress relaxation test and test apparatus using the same |
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