CN201540233U - Simple beam-cantilever beam combined impact testing machine - Google Patents
Simple beam-cantilever beam combined impact testing machine Download PDFInfo
- Publication number
- CN201540233U CN201540233U CN2009201103033U CN200920110303U CN201540233U CN 201540233 U CN201540233 U CN 201540233U CN 2009201103033 U CN2009201103033 U CN 2009201103033U CN 200920110303 U CN200920110303 U CN 200920110303U CN 201540233 U CN201540233 U CN 201540233U
- Authority
- CN
- China
- Prior art keywords
- jaw
- pendulum
- free beam
- hammer
- girder
- 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.)
- Expired - Fee Related
Links
Images
Landscapes
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The utility model discloses a simple beam-cantilever beam combined impact testing machine, which belongs to the field of material testing machines. In the prior art, the simple beam impact test and cantilever beam impact test for determining the impact ductility of rigid plastics, fiber reinforced composite materials and other non-metal materials require a simple beam impact testing machine and a cantilever beam impact testing machine respectively. The body of the simple beam-cantilever beam combined impact testing machine comprises a left upright post and a right upright post which are symmetrical, an impact pendulum moves between the two upright posts and is a simple beam pendulum or a cantilever beam pendulum, a simple beam jaw component is arranged on a simple beam lower jaw platform or a simple beam upper jaw platform on the front surfaces of the left and the right upright posts of the machine body, and a cantilever beam jaw component is positioned between the left and the right upright posts of the machine body and is arranged on a base. The simple beam-cantilever beam combined impact testing machine integrates the functions of the simple beam impact testing machine and the cantilever beam impact testing machine, and realizes the requirements for a machine serving several purposes. The combined impact testing machine can be used as the common equipment in material laboratories of scientific institutions, universities and colleges and related factories and mines to determine the impact ductility of rigid plastics, fiber reinforced composite materials, insulating materials and other non-metal materials.
Description
Technical field
The utility model belongs to the Material Testing Machine field, the outstanding combination of particularly a kind of letter impact testing machine.
Background technology
Measure the impact flexibility of nonmetallic materials such as rigid plastic, fibre reinforced composites, nylon, fiberglass, pottery, plastics electrical equipment, insulating material with the charpy impact test machine according to standard GB/T 1043-93 " rigid plastic charpy impact test method ".According to standard GB/T 1843-1996 " plastics izodtest method " above-mentioned nonmetallic materials are carried out the mensuration of cantilever beam impact strength, also will use radial-boom impact tester.And existing material impact test has only charpy impact test machine and radial-boom impact tester two classes, the material laboratory of some scientific research institutions, universities and colleges, relevant factories and miness, especially middle-size and small-size laboratory wishes to require to have to make the combined material impact testing machine that charpy impact test can be done izodtest again.
The utility model content
The purpose of this utility model is can make the combined material impact testing machine that charpy impact test can be done izodtest again for solving described in the background technology, the outstanding combination of a kind of letter impact testing machine is provided, it is characterized in that, fuselage 1 is fixed on the support 2, front at the left and right pillar of fuselage 1, one group of free beam lower jaw platform is arranged at the bottom, there is one group of free beam upper jaw platform at the middle part, free beam jaw assembly is installed in free beam lower jaw platform or free beam upper jaw platform, semi-girder jaw assembly is being installed between the left and right pillar of fuselage 1 on the support 2, ballistic pendulum is free beam pendulum or semi-girder pendulum, free beam pendulum or semi-girder pendulum are fastened on the oscillating weight axle 4 on fuselage 1 top by pendulum upper joint sleeve 11, pendulum releasing mechanism 3 is installed in fuselage 1 top, LCDs 5 is installed in fuselage 1 upper left-hand, and electromagnet and scrambler control enclosure 6 are installed in the back right side.
Described free beam pendulum is made of hammer body 7, pendulum lower joint sleeve 8, hammer hook 9, hammer stem 10 and pendulum upper joint sleeve 11, pendulum lower joint sleeve 8 is installed in the breach on hammer body 7 tops, the lower end of hammer stem 10 and pendulum lower joint sleeve 8 are affixed, the upper end is affixed with pendulum upper joint sleeve 11, hammer hook 9 is fixed in hammer stem 10 middle parts, its hook points to the hammer back of the body of hammer body 7, and hammer body 7 lower left quarter breach bottom is a pendulum blade 12.
Described semi-girder pendulum is made of semi-girder tup 13, hammer body upper junction plate 14, hammer body side plate 15, hammer hook 9, hammer stem 10 and pendulum upper joint sleeve 11, semi-girder tup 13 is fixed in hammer stem 10 lower ends, hammer body upper junction plate 14 is installed on the semi-girder tup 13, two blocks of hammer body side plates 15 are installed in 14 times left and right sides of hammer body upper junction plate, hammer stem 10 upper ends and pendulum upper joint sleeve 11 are affixed, hammer hook 9 is fixed in hammer stem 10 middle parts, its hook points to the hammer back of the body of semi-girder tup 13, and the bottom of semi-girder tup 13 is a semi-girder pendulum blade.
Described semi-girder jaw assembly, jaw pedestal 16 is fixed on the jaw base 17, jaw base 17 is installed on the jaw backing plate 18, fixing to clamp piece 19 is fixed on the jaw backing plate 18, bolt on it withstands jaw base 17, jaw orienting lug 20 is installed in the groove of jaw pedestal 16, the adjustable clamp buccal mass 21 of right-angled trapezium is installed on the jaw orienting lug 20, its bottom laterally is connected with compression spring with the right-hand member of jaw orienting lug 20, the compact heap 22 of right-angled trapezium is mounted in the groove of jaw pedestal 16 with interior adjusting leading screw on adjustable clamp buccal mass 21 right sides, both inclined-planes of adjustable clamp buccal mass 21 and compact heap 22 overlap the left surface formation semi-girder jaw 23 of the groove of the plane of the right-angle side of adjustable clamp buccal mass 21 and jaw pedestal 16.
Described free beam jaw assembly is made up of free beam jaw piece 24 and free beam jaw briquetting 25, both longitudinal cross-sections are the identical right-angled trapezium in base angle, the inclined-plane of trapezoidal free beam jaw briquetting 25 upwards, end face points to fuselage 1 and laterally places on the free beam lower jaw platform or free beam upper jaw platform of fuselage 1, use bolt, free beam jaw piece 24 places on the free beam jaw briquetting 25, fuselage 1 is pointed in its bottom surface, both inclined-planes of free beam jaw piece 24 and free beam jaw briquetting 25 overlap, the right-angled trapezium depth of section of free beam jaw piece 24 is less than the right-angled trapezium depth of section of free beam jaw briquetting 25, and two groups of free beam jaw assemblies on fuselage 1 left and right pillar constitute the free beam jaw.
The beneficial effects of the utility model are, because of the left and right pillar of fuselage by symmetry constitutes, pendulum is at two column intermediary movementses, strengthened complete machine and impacted stability, this structure can be installed the free beam jaw, carry out charpy impact test, also the semi-girder jaw can be installed, carry out izodtest, realize the combination function of a tractor serves several purposes.
Description of drawings
Fig. 1 is the outstanding combination of a letter impact testing machine complete machine synoptic diagram;
Fig. 2 A is a free beam pendulum profile front view;
Fig. 2 B is a free beam pendulum profile right view;
Fig. 3 A is a semi-girder pendulum structure left view;
Fig. 3 B is a semi-girder pendulum structural front view;
Fig. 4 is a semi-girder jaw modular construction synoptic diagram.
Among the figure: 1 is fuselage, and 2 is support, and 3 is the pendulum releasing mechanism, 4 is oscillating weight axle, and 5 is LCDs, and 6 is electromagnet and scrambler control enclosure, 7 is hammer body, and 8 is the pendulum lower joint sleeve, and 9 are the hammer hook, 10 is hammer stem, and 11 is the pendulum upper joint sleeve, and 12 is the pendulum blade, 13 is the semi-girder tup, and 14 is the hammer body upper junction plate, and 15 is the hammer body side plate, 16 is the jaw pedestal, 17 is the jaw base, and 18 is the jaw backing plate, and 19 for fixing to clamp piece, 20 is the jaw orienting lug, 21 is the adjustable clamp buccal mass, and 22 is compact heap, and 23 is the semi-girder jaw, 24 is free beam jaw piece, and 25 is free beam jaw briquetting.
Embodiment
Fig. 1 is the complete machine structure synoptic diagram of embodiment of the present utility model.The left and right pillar of fuselage constitutes fuselage 1 and is fixed on the support 2.Front at the left and right pillar of fuselage 1, one group of free beam lower jaw platform is arranged at the bottom, there is one group of free beam upper jaw platform at the middle part, semi-girder jaw assembly is being installed between the left and right pillar of fuselage 1 on the support 2, ballistic pendulum is free beam pendulum or semi-girder pendulum, ballistic pendulum is fastened on the oscillating weight axle 4 on fuselage 1 top by pendulum upper joint sleeve 11, pendulum releasing mechanism 3 is installed in fuselage 1 top, LCDs 5 is installed in fuselage 1 upper left-hand, and electromagnet and scrambler control enclosure 6 are installed in the back right side.
Fig. 2 A and Fig. 2 B are free beam pendulum profile synoptic diagram, pendulum lower joint sleeve 8 is installed in the breach on hammer body 7 tops, the lower end of hammer stem 10 and pendulum lower joint sleeve 8 are affixed, the upper end is affixed with pendulum upper joint sleeve 11, hammer hook 9 is fixed in hammer stem 10 middle parts, its hook points to the hammer back of the body of hammer body 7, and hammer body 7 lower left quarter breach bottom is a pendulum blade 12.
Fig. 3 A and Fig. 3 B are semi-girder pendulum structural representation, semi-girder tup 13 is fixed in hammer stem 10 lower ends, hammer body upper junction plate 14 is installed on the semi-girder tup 13, two blocks of hammer body side plates 15 are installed in 14 times left and right sides of hammer body upper junction plate, hammer stem 10 upper ends and pendulum upper joint sleeve 11 are affixed, hammer hook 9 is fixed in hammer stem 10 middle parts, and its hook points to the hammer back of the body of semi-girder tup 13, and the bottom of semi-girder tup 13 is a semi-girder pendulum blade.
Fig. 4 is a semi-girder jaw modular construction synoptic diagram, jaw pedestal 16 is fixed on the jaw base 17, jaw base 17 is installed on the jaw backing plate 18, fixing to clamp piece 19 is fixed on the jaw backing plate 18, bolt on it withstands jaw base 17, jaw orienting lug 20 is installed in the groove of jaw pedestal 16, the adjustable clamp buccal mass 21 of right-angled trapezium is installed on the jaw orienting lug 20, its bottom laterally is connected with compression spring with the right-hand member of jaw orienting lug 20, the compact heap 22 of right-angled trapezium is mounted in the groove of jaw pedestal 16 with interior adjusting leading screw on adjustable clamp buccal mass 21 right sides, both inclined-planes of adjustable clamp buccal mass 21 and compact heap 22 overlap the left surface formation semi-girder jaw 23 of the groove of the plane of the right-angle side of adjustable clamp buccal mass 21 and jaw pedestal 16.
When doing izodtest, as shown in Figure 1, the ballistic pendulum that hangs on oscillating weight axle 4 is the semi-girder pendulum, sample is clipped in the jaw of semi-girder jaw assembly by the requirement of standard GB/T 1843-1996 " plastics izodtest method ", pendulum is held up, extension with pendulum releasing mechanism 3 is hammered the hammer hook 9 that hook catches on pendulum into shape, and pendulum has promptly been kicked up 160 °, can realize impacting.
When doing charpy impact test, semi-girder jaw assembly shown in Fig. 1 is removed, ballistic pendulum changes the free beam pendulum shown in Fig. 2 A into, when doing several energy impacts test of 0.5J, 1J, 2J, 4J, 5J, free beam jaw assembly is installed in the upper jaw platform, does two kinds of energy lower jaw platforms of 7.5J, 15J.Press size of sample, according to standard GB/T 1043-93 " rigid plastic charpy impact test method ", adjust the width of jaw that a pair of free beam jaw piece 24 and free beam jaw briquetting 25 are formed on the left and right pillar of fuselage 1, sample is placed on jaw, pendulum is held up, extension with pendulum releasing mechanism 3 is hammered the hammer hook 9 that hook catches on pendulum into shape, and pendulum has promptly been kicked up 160 °, can realize impacting.
When realizing impacting, discharge ballistic pendulum by the key command electromagnet of LCDs 5 and the electromagnet interlock pendulum releasing mechanism 3 in the scrambler control enclosure 6, ballistic pendulum rotates and drives oscillating weight axle 4 rotations, angular encoder shaft coupling in oscillating weight axle 4 and the scrambler control enclosure 6, angular encoder is measured the corner of oscillating weight axle 4.According to the corner of ballistic pendulum moment and oscillating weight axle 4, calculate the energy that sample fracture absorbed.
In process of the test, the energy of ballistic pendulum consumption comprises the influence of energy that sample fracture absorbs and friction and air resistance and the energy that loses, for improving the accuracy of data, the energy loss that rubs and air resistance causes is revised, should be calculated as follows the ENERGY E that sample fracture absorbs:
E＝Pd[(cosβ-cosα)-(cosα′-cosα)(α+β/α+α′)]
In the formula: Pd-ballistic pendulum moment; α-ballistic pendulum is raised the angle in advance; Lift angle after α '-the ballistic pendulum sky hits; Ballistic pendulum lift angle after β-sample fracture.
Because the lift angle α ' that ballistic pendulum moment Pd, ballistic pendulum raise angle α, ballistic pendulum sky in advance after hitting is constant,, can calculate the energy that sample fracture absorbs as long as therefore measure ballistic pendulum lift angle β after the sample fracture.
The utility model can be done charpy impact test separately, can do izodtest again, realized a tractor serves several purposes function, the convenient different requirement of using, can be used as the common equipment of the material laboratory of scientific research institution, universities and colleges, relevant factories and miness, be used to measure the impact flexibility of nonmetallic materials such as rigid plastic, fibre reinforced composites, nylon, fiberglass, pottery, plastics electrical equipment, insulating material.
Claims (5)
1. the combination impact testing machine is hanged in a letter, it is characterized in that, fuselage (1) is fixed on the support (2), front at the left and right pillar of fuselage (1), one group of free beam lower jaw platform is arranged at the bottom, there is one group of free beam upper jaw platform at the middle part, free beam jaw assembly is installed in free beam lower jaw platform or free beam upper jaw platform, semi-girder jaw assembly is being installed between the left and right pillar of fuselage (1) on the support (2), ballistic pendulum is free beam pendulum or semi-girder pendulum, free beam pendulum or semi-girder pendulum are fastened on the oscillating weight axle (4) on fuselage (1) top by pendulum upper joint sleeve (11), pendulum releasing mechanism (3) is installed in fuselage (1) top, LCDs (5) is installed in fuselage (1) upper left-hand, and electromagnet and scrambler control enclosure (6) are installed in the back right side.
2. the outstanding combination of letter according to claim 1 impact testing machine, its feature also is, described free beam pendulum is made of hammer body (7), pendulum lower joint sleeve (8), hammer hook (9), hammer stem (10) and pendulum upper joint sleeve (11), pendulum lower joint sleeve (8) is installed in the breach on hammer body (7) top, the lower end of hammer stem (10) and pendulum lower joint sleeve (8) are affixed, the upper end is affixed with pendulum upper joint sleeve (11), hammer hook (9) is fixed in hammer stem (10) middle part, its hook points to the hammer back of the body of hammer body (7), and hammer body (7) lower left quarter breach bottom is pendulum blade (12).
3. the outstanding combination of letter according to claim 1 impact testing machine, its feature also is, described semi-girder pendulum is by semi-girder tup (13), hammer body upper junction plate (14), hammer body side plate (15), hammer hook (9), hammer stem (10) and pendulum upper joint sleeve (11) constitute, semi-girder tup (13) is fixed in hammer stem (10) lower end, hammer body upper junction plate (14) is installed on the semi-girder tup (13), two blocks of hammer body side plates (15) are installed in the left and right sides under the hammer body upper junction plate (14), hammer stem (10) upper end is affixed with pendulum upper joint sleeve (11), hammer hook (9) is fixed in hammer stem (10) middle part, its hook points to the hammer back of the body of semi-girder tup (13), and the bottom of semi-girder tup (13) is a semi-girder pendulum blade.
4. the outstanding combination of letter according to claim 1 impact testing machine, its feature also is, described semi-girder jaw assembly, jaw pedestal (16) is fixed on the jaw base (17), jaw base (17) is installed on the jaw backing plate (18), fixing to clamp piece (19) is fixed on the jaw backing plate (18), bolt on it withstands jaw base (17), jaw orienting lug (20) is installed in the groove of jaw pedestal (16), the adjustable clamp buccal mass (21) of right-angled trapezium is installed on the jaw orienting lug (20), its bottom laterally is connected with compression spring with the right-hand member of jaw orienting lug (20), the compact heap of right-angled trapezium (22) is mounted in the groove of jaw pedestal (16) with interior adjusting leading screw on adjustable clamp buccal mass (21) right side, both inclined-planes of adjustable clamp buccal mass (21) and compact heap (22) overlap, and the left surface of the groove of the plane of the right-angle side of adjustable clamp buccal mass (21) and jaw pedestal (16) constitutes semi-girder jaw (23).
5. the outstanding combination of letter according to claim 1 impact testing machine, its feature also is, described free beam jaw assembly is made up of free beam jaw piece (24) and free beam jaw briquetting (25), both longitudinal cross-sections are the identical right-angled trapezium in base angle, the inclined-plane of trapezoidal free beam jaw briquetting (25) end face that makes progress points to fuselage (1) and laterally places on the free beam lower jaw platform or free beam upper jaw platform of fuselage (1), use bolt, free beam jaw piece (24) places on the free beam jaw briquetting (25), fuselage (1) is pointed in its bottom surface, both inclined-planes of free beam jaw piece (24) and free beam jaw briquetting (25) overlap, the right-angled trapezium depth of section of free beam jaw piece (24) is less than the right-angled trapezium depth of section of free beam jaw briquetting (25), and two groups of free beam jaw assemblies on fuselage (1) left and right pillar constitute the free beam jaw.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009201103033U CN201540233U (en) | 2009-07-23 | 2009-07-23 | Simple beam-cantilever beam combined impact testing machine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009201103033U CN201540233U (en) | 2009-07-23 | 2009-07-23 | Simple beam-cantilever beam combined impact testing machine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201540233U true CN201540233U (en) | 2010-08-04 |
Family
ID=42591690
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009201103033U Expired - Fee Related CN201540233U (en) | 2009-07-23 | 2009-07-23 | Simple beam-cantilever beam combined impact testing machine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201540233U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102830024A (en) * | 2011-06-14 | 2012-12-19 | 黑龙江鑫达企业集团有限公司 | Method for rapid detection of impact performance of automobile modified plastic |
| CN103512814A (en) * | 2012-06-14 | 2014-01-15 | 中国石油天然气集团公司 | Drop weight tear test system and method thereof |
| CN107607416A (en) * | 2017-09-08 | 2018-01-19 | 湖北省计量测试技术研究院 | A kind of Chalpy impact pendulum |
| CN112649281A (en) * | 2020-12-29 | 2021-04-13 | 朗道供应链(苏州)有限公司 | Impact testing machine |
-
2009
- 2009-07-23 CN CN2009201103033U patent/CN201540233U/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102830024A (en) * | 2011-06-14 | 2012-12-19 | 黑龙江鑫达企业集团有限公司 | Method for rapid detection of impact performance of automobile modified plastic |
| CN103512814A (en) * | 2012-06-14 | 2014-01-15 | 中国石油天然气集团公司 | Drop weight tear test system and method thereof |
| CN103512814B (en) * | 2012-06-14 | 2015-07-08 | 中国石油天然气集团公司 | Drop weight tear test system and method thereof |
| CN107607416A (en) * | 2017-09-08 | 2018-01-19 | 湖北省计量测试技术研究院 | A kind of Chalpy impact pendulum |
| CN107607416B (en) * | 2017-09-08 | 2024-02-20 | 湖北省计量测试技术研究院 | Cantilever beam impact pendulum |
| CN112649281A (en) * | 2020-12-29 | 2021-04-13 | 朗道供应链(苏州)有限公司 | Impact testing machine |
| CN112649281B (en) * | 2020-12-29 | 2022-04-05 | 朗道供应链(苏州)有限公司 | Impact testing machine |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN201540233U (en) | Simple beam-cantilever beam combined impact testing machine | |
| CN106940275B (en) | Plate clamp platform for drop hammer impact test and impact speed measuring method | |
| CN105606472B (en) | A kind of anchor pole impact test apparatus and its method | |
| CN104048885A (en) | Pendulum bob type shearing-resistant impact testing machine and testing method thereof | |
| CN112378785B (en) | Plate impact test device | |
| CN211291934U (en) | Collapse rock fall impact force simulation test device | |
| CN204008338U (en) | Pendulum shearing resistance impact testing machine | |
| CN210923350U (en) | Concrete impact resistance test device | |
| CN110672394A (en) | Sample preparation device and method suitable for different cohesive soils | |
| CN202631376U (en) | Automobile nonmetallic section drop hammer test bed | |
| RU2315969C1 (en) | Stand for testing concrete and reinforced concrete members short - time period central and out-of-center dynamic compression | |
| CN103063514B (en) | Radial inclination compressive strength test device for round-section concrete-filled steel tube | |
| CN107607469A (en) | A kind of device for FRP enhancing basal body interface adhesive property tests | |
| CN114136814A (en) | Toughened glass impact-resistant detection equipment for building engineering | |
| CN101387591B (en) | Overturn feed mechanism of drop hammer type impact tester | |
| CN112903491A (en) | Building material detects with shock-resistant test device | |
| CN109469111A (en) | A kind of constructing highway ground loading test equipment | |
| CN210005367U (en) | Impact strength tester for glass bottles | |
| CN204374012U (en) | A kind of drop impact tension test truss conversion equipment realizing elimination inertia force influence | |
| CN102680334A (en) | Magnetic switch control drop hammer type bending impact resistance test table | |
| CN207066657U (en) | A kind of simple lever consolidation apparatus for supporting balancing method expansive force to test | |
| CN206557075U (en) | A kind of building block and binding material adhesive property test device | |
| CN209069703U (en) | A kind of reisilometer locating support | |
| CN209280263U (en) | A kind of guardrail impact test apparatus | |
| CN210293945U (en) | Portable adjustable compaction instrument |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20100804 Termination date: 20120723 |