CN105606452A - Portable device for performing load calibration and strength tests of airplane two-force bar piece at external field - Google Patents
Portable device for performing load calibration and strength tests of airplane two-force bar piece at external field Download PDFInfo
- Publication number
- CN105606452A CN105606452A CN201610124309.0A CN201610124309A CN105606452A CN 105606452 A CN105606452 A CN 105606452A CN 201610124309 A CN201610124309 A CN 201610124309A CN 105606452 A CN105606452 A CN 105606452A
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- China
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- test
- load
- workbench
- orientation axes
- power rod
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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
- G01N3/08—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces
- G01N3/10—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces generated by pneumatic or hydraulic pressure
- G01N3/12—Pressure testing
Abstract
The invention belongs to the field of structural load measurement and strength tests of airplanes, and particularly relates to a portable test device capable of performing a load calibration test and a static test of an airplane two-force bar piece at an external field. According to the portable device for performing the load calibration and strength tests of the airplane two-force bar piece at the external field, a load loading device is installed at one end of a working platform (11), and a test piece base (14) fixedly provided with a third two-lug connector (13) is installed at the other end of the working platform (11); the load loading device is connected with an orientation shaft (7); the other end of the orientation shaft (7) is connected with a test pulling pressure sensor (9) with a second two-lug connector (10); the orientation shaft (7) is installed on the working platform (11) through an orientation shaft seat (8) with a groove in the bottom. According to the portable device, precise control over test loads can be achieved, it is guaranteed that calibrated loads or strength test loads of the two-force bar piece are correct and high in precision, and the requirements are met.
Description
Technical field
The invention belongs to aircaft configuration load measurement and strength test field, particularly one outside field energy carry out aircraft two power barsThe portable experimental rig of the test of part load calibration, slow test.
Background technology
Only be subject to the bar of two same axial force effects to be called two power bars, on aircraft, a lot of lever piece members all can be considered two power bars, as behaviourVertical pole, retractable actuating cylinder etc. Two power bar load calibration tests are generally pasted foil gauge on two power bars, then two power bars are appliedTensile or Compressive Loading, load will ensure to be applied on the axis of two power bars. If occur, load axis and two power rod axis are not straight at sameOn line time, will in two power bar axial slices, produce additional moment, cause two power bar loadings not meet reality, two power barsThe foil gauge of upper stickup also just cannot truly reflect the tension and compression strain of two power bars.
Load calibration/the strength test of two power bars in the past is all carried out in Material Testing Machine, because Material Testing Machine is generally more stupidHeavy, volume is large and price is relatively costly, often Material Testing Machine cannot be removed in the load calibration/strength test of outfield two power barsTest to scene.
Summary of the invention
The object of the invention is: a kind of load calibration test/static(al) examination that can directly carry out in outfield two power rod members on aircraft is providedThe mancarried device of testing.
Technical scheme of the present invention is: aircraft two power rod member outfield load calibration/strength test portable units, it comprises: load addsCarry device, orientation axes, tension-compression sensor, testpieces base and bracing frame for test;
Bracing frame comprises: the support member of strip and be arranged on the workbench of support surface; The center of workbench is provided withPositioning key vertically;
Load charger is installed on one end of workbench, is installed with the testpieces floor installation of ears joint C in workThe other end of platform; Load charger is connected with orientation axes; The other end of orientation axes connects with the test of ears joint B to be usedTension-compression sensor; Orientation axes is with reeded directed axle bed to be installed on workbench by bottom;
When test, two power rod members are connected between ears joint B and ears joint C, and load charger applied force,Orientation axes and two power rod members are in same axis.
Beneficial effect: 1, the present invention can realize accurately and controlling test load, ensures demarcation load or the intensity examination of two power rod membersTest that load is correct, precision is high, meet the demands;
What 2, the present invention can ensure to apply draw, the dead in line of compressive load axis and two power bar testpieces;
3,, for large load test situation, hydraulic loaded form of the present invention can realize automatically loading step by step of two power bar tests;
4,, for the less situation of test load, manual loading form of the present invention also can realize the loading step by step to two power rod members.
Brief description of the drawings
Fig. 1 is an embodiment of the invention;
Fig. 2 is the cutaway view of another embodiment of the invention;
Fig. 3 is the partial enlarged drawing of Fig. 2;
Wherein, 1-hydraulic cylinder base, 2-hydraulic cylinder, 5-feedback tension-compression sensor, 6-ears joint A, 7-orientation axes, 8-are fixedAt the bottom of axle bed, 9-test tension-compression sensor, 10-ears joint B, 11-workbench, 13-ears joint C, 14-testpiecesSeat, 15-support member, 16-strengthening steel slab, 18-feedback line displacement transducer, 19-pulling pressing device base, 20-monaural joint, 21-Directed steel pipe, 22-anchor tip, 23-pin key, 25-charging handle, 26-rectangular thread screw mandrel, 27-round nut, 28-axleCover.
Detailed description of the invention
Below in conjunction with the accompanying drawing embodiment that develops simultaneously, describe the present invention.
Aircraft two power rod member outfield load calibration/strength test portable units, it comprises: load charger, orientation axes 7, surveyTension-compression sensor 9, testpieces base 14 and bracing frame on probation;
Bracing frame comprises: the support member 15 of strip and be arranged on the workbench 11 on support member 15 surfaces; Workbench 11Center be provided with positioning key vertically;
Load charger is installed on one end of workbench 11, and the testpieces base 14 that is installed with ears joint C13 is pacifiedBe contained in the other end of workbench 11; Load charger is connected with orientation axes 7; The other end of orientation axes 7 connects with earsThe tension-compression sensor 9 for test of joint B10; Orientation axes 7 is with reeded directed axle bed 8 to be installed on workbench by bottom11；
When test, two power rod members are connected between ears joint B10 and ears joint C13, and load charger, orientationAxle 7 and two power rod members are in same axis.
Referring to accompanying drawing 1, load charger can be for being provided with the hydraulic cylinder 2 of feedback line displacement transducer 18; Hydraulic cylinder 2 is logicalCross hydraulic cylinder base 1 and be installed on workbench 11, the bottom surface of hydraulic cylinder base 1 be processed with workbench 11 on positioning key phaseThe groove coordinating; The piston rod of hydraulic cylinder 2 connects and feeds back tension-compression sensor 5, feedback tension-compression sensor 5 by ears joint A6 withOrientation axes 7 connects; When test, the piston rod of hydraulic cylinder 2, orientation axes 7 and two power rod members are in same axis.
Wherein, the purposes of feedback tension-compression sensor 5 is: hydraulic cylinder 2 output loads are fed back to peripheral control system, with controlThe output command contrast of system processed, to control output loads within the error allowing;
Feedback by the purposes of displacement transducer 18 is: hydraulic cylinder 2 output displacements are fed back to control system, defeated with control systemGo out order contrast, to control output displacement within the error allowing;
Test by the purposes of tension-compression sensor 9 is: be used for showing the real stressed size of two power bars, get rid of the impact of other factors.
Referring to accompanying drawing 2, load charger can be also manual loading device; Manual loading device comprises: be inlaid with universal drive shaftThe monaural joint 20 holding, the directed steel pipe 21 being fixedly connected with monaural joint 20, the anchor tip being connected with directed steel pipe 2122, be slidably matched with anchor tip 22 and the rectangular thread screw mandrel 26 of locating by pin key 23, connect with rectangular thread screw mandrel 26The round nut 27 that connects, be embedded in axle sleeve 28 in anchor tip 22, be arranged on pushing away between axle sleeve 28 and anchor tip 22Mechanical axis holds 24; Threaded screw rod 26 is through thrust bearing 24, and the internal diameter of thrust bearing 24 coordinates with the crest clearance of axle sleeve 28,The external screw thread of axle sleeve 28 is connected with round nut 27 internal threads; On round nut 27, be provided with charging handle 25; Manual loadingDevice is connected and installed in workbench 11 by monaural joint 20 and pulling pressing device base 19; Rectangular thread screw mandrel 26 is with directedAxle 7 connects; When test, rectangular thread screw mandrel 26, orientation axes 7 and two power rod members are in same axis.
In such scheme, support member 15 is two affixed forming of back-to-back channel-section steel, is provided with reinforcing at the lower surface of support member 15Steel plate 16; For preventing the long distortion causing of length, positioning key is designed for segmented; Each base is at workbench for convenienceInstallation, at the equally spaced screwed hole that is provided with in the both sides of positioning key.
To sum up, these are only preferred embodiment of the present invention, be not intended to limit protection scope of the present invention. All at thisWithin bright spirit and principle, any amendment of doing, be equal to replacement, improvement etc., all should be included in protection scope of the present inventionWithin.
Claims (5)
1. aircraft two power rod member outfield load calibration/strength test portable units, is characterized in that, it comprises: load charger,Orientation axes (7), test tension-compression sensor (9), testpieces base (14) and bracing frame;
Support frame as described above comprises: the support member (15) of strip and be arranged on the workbench on described support member (15) surface(11); The center of described workbench (11) is provided with positioning key vertically;
Load charger is installed on one end of described workbench (11), be installed with ears joint C (13) described inTestpieces base (14) is arranged on the other end of described workbench (11); Load charger and described orientation axes (7) connectConnect; The other end of described orientation axes (7) connects with ears joint B (10) described tension-compression sensor (9) for test; InstituteStating orientation axes (7) is with reeded directed axle bed (8) to be installed on described workbench (11) by bottom;
When test, two power rod members are connected between described ears joint B (10) and described ears joint C (13), and described inLoad charger applied force, described orientation axes (7) and described two power rod members are in same axis.
2. aircraft two power rod member outfield load calibration/strength test portable units as claimed in claim 1, is characterized in that instituteState load charger for the hydraulic cylinder (2) of feedback line displacement transducer (18) is installed; Described hydraulic cylinder (2) passes through hydraulic pressureCylinder bottom seat (1) is installed on described workbench (11), and the bottom surface of described hydraulic cylinder base (1) is processed with and described workbench(11) groove that upper positioning key matches; The piston rod of described hydraulic cylinder (2) even feeds back tension-compression sensor (5), and described feedback is drawnPressure sensor (5) is connected with described orientation axes (7) by ears joint A (6); When test, described hydraulic cylinder (2)Piston rod, described orientation axes (7) and described two power rod members are in same axis.
3. aircraft two power rod member outfield load calibration/strength test portable units as claimed in claim 1, is characterized in that instituteStating load charger is manual loading device; Described manual loading device comprises: be inlaid with universal bearing monaural joint (20),The directed steel pipe (21) being fixedly connected with described monaural joint (20), the anchor tip (22) being connected with described directed steel pipe (21),Be slidably matched with described anchor tip (22) and pass through the rectangular thread screw mandrel (26) of pin key (23) location, with described rectangle spiral shellRound nut (27) that line screw mandrel (26) connects, be embedded in axle sleeve (28) in described anchor tip (22), be arranged on instituteState the thrust bearing (24) between axle sleeve (28) and described anchor tip (22); Described in passing, described threaded screw rod (26) pushes awayMechanical axis holds (24), and the internal diameter of described thrust bearing (24) coordinates with the crest clearance of described axle sleeve (28), described axle sleeve (28)External screw thread be connected with described round nut (27) internal thread; On described round nut (27), be provided with charging handle (25);
Described manual loading device is connected and installed in described workbench by monaural joint (20) and pulling pressing device base (19)(11); Described rectangular thread screw mandrel (26) is connected with orientation axes (7); When test, described rectangular thread screw mandrel (26), instituteState orientation axes (7) and described two power rod members in same axis.
4. aircraft two power rod member outfield load calibration/strength test portable units as claimed in claim 1, is characterized in that, described inSupport member (15) is the affixed formation of channel-section steel of two, is provided with strengthening steel slab (16) at the lower surface of described support member (15).
5. aircraft two power rod member outfield load calibration/strength test portable units as claimed in claim 1, is characterized in that, described inPositioning key designs for segmented, and at the equally spaced screwed hole that is provided with in the both sides of described positioning key.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610124309.0A CN105606452B (en) | 2016-03-04 | 2016-03-04 | The power rod member outfield load calibration of aircraft two/strength test portable unit |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610124309.0A CN105606452B (en) | 2016-03-04 | 2016-03-04 | The power rod member outfield load calibration of aircraft two/strength test portable unit |
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| Publication Number | Publication Date |
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| CN105606452A true CN105606452A (en) | 2016-05-25 |
| CN105606452B CN105606452B (en) | 2018-02-09 |
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| CN201610124309.0A Active CN105606452B (en) | 2016-03-04 | 2016-03-04 | The power rod member outfield load calibration of aircraft two/strength test portable unit |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106500975A (en) * | 2016-10-20 | 2017-03-15 | 中国汽车工程研究院股份有限公司 | A kind of parts strain and load calibration test device |
| CN108177367A (en) * | 2017-12-27 | 2018-06-19 | 常州朗锐凯迩必减振技术有限公司 | A kind of automatic tension and compression equipment of oil-pressure damper and its control method |
| CN109187201A (en) * | 2018-10-25 | 2019-01-11 | 上海第机床厂有限公司 | In-pile component plays the load test device of hanging piece |
| CN112874809A (en) * | 2020-12-28 | 2021-06-01 | 国机集团北京飞机强度研究所有限公司 | Movable external field tension and compression load calibration test device and method |
| CN113008561A (en) * | 2021-03-01 | 2021-06-22 | 国机集团北京飞机强度研究所有限公司 | Loading device for load calibration test of engine suspension mounting joint |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0357966A1 (en) * | 1988-08-15 | 1990-03-14 | Liberty Technologies, Inc. | Devices and methods for determining axial loads |
| JP2842555B2 (en) * | 1987-04-21 | 1999-01-06 | モバッツ インコーポレイテッド | Mandrel load measurement system |
| EP0730210B1 (en) * | 1995-03-03 | 2002-06-12 | Faro Technologies Inc. | Three dimensional coordinate measuring apparatus |
| CN201532315U (en) * | 2009-05-31 | 2010-07-21 | 广州飞机维修工程有限公司 | Airplane spoiler power control assembly testing system |
| CN202013301U (en) * | 2011-01-21 | 2011-10-19 | 燕山大学 | Loading device for pulling/pressing and creeping test of rod piece |
| CN102866033A (en) * | 2012-10-22 | 2013-01-09 | 清华大学 | Dynamic loading device for two-way tension and pressure |
| CN103630442A (en) * | 2013-12-04 | 2014-03-12 | 中国飞机强度研究所 | Aircraft structural strength test loading level |
| CN104697758A (en) * | 2013-12-04 | 2015-06-10 | 广州汽车集团股份有限公司 | Two force member test bed |
| CN204649439U (en) * | 2015-05-15 | 2015-09-16 | 广州汽车集团股份有限公司 | strength testing device |
| CN104990696A (en) * | 2015-06-23 | 2015-10-21 | 中国航空工业集团公司西安飞机设计研究所 | Loading system |
-
2016
- 2016-03-04 CN CN201610124309.0A patent/CN105606452B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2842555B2 (en) * | 1987-04-21 | 1999-01-06 | モバッツ インコーポレイテッド | Mandrel load measurement system |
| EP0357966A1 (en) * | 1988-08-15 | 1990-03-14 | Liberty Technologies, Inc. | Devices and methods for determining axial loads |
| EP0730210B1 (en) * | 1995-03-03 | 2002-06-12 | Faro Technologies Inc. | Three dimensional coordinate measuring apparatus |
| CN201532315U (en) * | 2009-05-31 | 2010-07-21 | 广州飞机维修工程有限公司 | Airplane spoiler power control assembly testing system |
| CN202013301U (en) * | 2011-01-21 | 2011-10-19 | 燕山大学 | Loading device for pulling/pressing and creeping test of rod piece |
| CN102866033A (en) * | 2012-10-22 | 2013-01-09 | 清华大学 | Dynamic loading device for two-way tension and pressure |
| CN103630442A (en) * | 2013-12-04 | 2014-03-12 | 中国飞机强度研究所 | Aircraft structural strength test loading level |
| CN104697758A (en) * | 2013-12-04 | 2015-06-10 | 广州汽车集团股份有限公司 | Two force member test bed |
| CN204649439U (en) * | 2015-05-15 | 2015-09-16 | 广州汽车集团股份有限公司 | strength testing device |
| CN104990696A (en) * | 2015-06-23 | 2015-10-21 | 中国航空工业集团公司西安飞机设计研究所 | Loading system |
Non-Patent Citations (5)
| Title |
|---|
| BENJAMIN ZILLMANN ET AL.: "In-plane biaxial compression and tension testing of thin sheet materials", 《INTERNATIONAL JOURNAL OF SOLIDS AND STRUCTURES》 * |
| V. SATHEESHKUMAR & R. GANESH NARAYANAN: "In-plane plane strain formability of adhesive-bonded steel sheets:influence of adhesive properties", 《INTERNATIONAL JOURNAL OF ADVANCED MANUFACTURING TECHNOLOGY》 * |
| 景国玺等: "发动机连杆疲劳强度试验及寿命预测方法研究", 《车用发动机》 * |
| 李卫平等: "民用飞机发动机吊挂部段静力试验与静强度分析", 《南京航空航天大学学报》 * |
| 韩晓明等: "节制杆式模拟汽车座椅强度试验装置研究", 《汽车技术》 * |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106500975A (en) * | 2016-10-20 | 2017-03-15 | 中国汽车工程研究院股份有限公司 | A kind of parts strain and load calibration test device |
| CN108177367A (en) * | 2017-12-27 | 2018-06-19 | 常州朗锐凯迩必减振技术有限公司 | A kind of automatic tension and compression equipment of oil-pressure damper and its control method |
| CN108177367B (en) * | 2017-12-27 | 2019-10-25 | 常州朗锐凯迩必减振技术有限公司 | A kind of automatic tension and compression equipment of oil-pressure damper and its control method |
| CN109187201A (en) * | 2018-10-25 | 2019-01-11 | 上海第机床厂有限公司 | In-pile component plays the load test device of hanging piece |
| CN112874809A (en) * | 2020-12-28 | 2021-06-01 | 国机集团北京飞机强度研究所有限公司 | Movable external field tension and compression load calibration test device and method |
| CN113008561A (en) * | 2021-03-01 | 2021-06-22 | 国机集团北京飞机强度研究所有限公司 | Loading device for load calibration test of engine suspension mounting joint |
| CN113008561B (en) * | 2021-03-01 | 2022-07-29 | 国机集团北京飞机强度研究所有限公司 | Loading device for load calibration test of engine hanging installation joint |
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| CN105606452B (en) | 2018-02-09 |
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Address after: 100083 comprehensive research building, No.1 North Beach, Beijing, Chaoyang District Applicant after: China aircraft group Beijing Aircraft Strength Research Institute Co Ltd Address before: 100083 comprehensive research building, No.1 North Beach, Beijing, Chaoyang District Applicant before: SINOMACH GROUP BEIJING FLIGHT INTENSITY RESEARCH INSTITUTE CO., LTD. |
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