CN103407579A - Major-diameter airframe test loading clamp - Google Patents
Major-diameter airframe test loading clamp Download PDFInfo
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- CN103407579A CN103407579A CN2012105287009A CN201210528700A CN103407579A CN 103407579 A CN103407579 A CN 103407579A CN 2012105287009 A CN2012105287009 A CN 2012105287009A CN 201210528700 A CN201210528700 A CN 201210528700A CN 103407579 A CN103407579 A CN 103407579A
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- airframe
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Abstract
The invention belongs to the test loading technology, and relates to a major-diameter airframe test loading clamp. The major-diameter airframe test loading clamp comprises a butt joint end plate, a force averaging ring and skin. The butt joint end plate is of a circular ring structure matched with an airframe transition section, an inner ring and an outer ring of the butt joint end plate are surrounded by the force averaging ring, one side of the force averaging ring is connected with the butt joint end plate, the other side of the force averaging ring is connected with a loading device through the skin, and the loading device is used for exerting concentrated loads. The major-diameter airframe test loading clamp is applied to a certain type airplane wing body combined body force transmission characteristic test, accurate exertion of various loads on a butt joint end frame section is achieved, rationality of stress distribution of a butt joint end frame is guaranteed, good limitation to a tested piece is provided, and convenience is brought to tare of the loading device. In theory, the loading device and the testing technology of the loading device can achieve exertion of any load on any airframe frame section.
Description
Technical field
The invention belongs to the test loading technique, relate to a kind of major diameter airframe test and load fixture.
Background technology
For airframe frame section subassembly test, usually the method adopted is to increase docking transitional frame section at airframe examination frame section end face, by the Special test fixture, the transitional frame section is fixed on the load wall, realize solid constraint of test article, by the passive suffered various load of fuselage examination frame end that applies of load wall.This method is only applicable to the situation that test article only has a section face.Due to the constraint of load wall as test article, bear the unbalance load of test article and other initiatively put loading error, the passive load applied often is difficult to meet the requirement of test loading accuracy in theory, has increased the test difficulty.According to Saint Venant's principle, on the impact of test article examination section, be down to minimum by admittedly propping up the border condition, need sufficiently long docking transition phase.For the major diameter fuselage, the docking transition section length more will increase, and this not only requires a great deal of time, and has also increased experimentation cost.
For the fuselage frame section that has two end faces, method in the past can not meet test requirements document.Test of the present invention loads fixture, as the support of test, has reduced the impact of the support of test article on the examination position; As test, load bogusware, reduced the installation workload of supporting, the access port that provides test initiatively to load.
Summary of the invention
The objective of the invention is: provide a kind of and can solve the constraint of fuselage frame section both ends of the surface and loading problem, reduce to retrain the impact on the examination position, make to examine carrying major diameter airframe test more accurately in position to load fixture.
Technical scheme of the present invention is: a kind of major diameter airframe test loads fixture, it comprises opposed end panel, equal power ring and covering, described opposed end panel is the circular ring structure be complementary with the fuselage transition phase, all the power ring is surrounded on the opposed end panel Internal and external cycle, all power ring one side connects opposed end panel, and opposite side connects the loading facilities that applies concentrated load through covering.
Opposed end panel surrounding outward flange is provided with for some through holes.
Opposed end panel is spliced or is made of one piece by the dull and stereotyped interlock of some uniform thickness.
The approximate annulus of described equal power ring for being welded by some channel-section steels, all the axial dimension of power ring is between 200mm to 400mm.
Described covering is welded by some metal sheets of middle perforate.
Comprise that base is arranged on equal power ring, both sides are for posting in addition, and the triangular beam be welded by channel-section steel.
Comprise and being arranged on equal power ring, be used to distributing the loading beam of concentrated load to inside and outside equal power ring.
All the power ring stiffness is greater than opposed end panel rigidity.
Technique effect of the present invention is: the present invention is applied in the test of aircraft wing body fabricate block force-transfer characteristic, realized accurately applying of the butt end various load of frame section, guaranteed the reasonableness of butt end frame distribution of force, the good constraint of test article is provided, and has facilitated the button weight of loading facilities.In theory, this loading facilities and testing technique thereof, can realize applying of any fuselage frame section Arbitrary Loads, thereby solved that the major diameter fuselage load applies, structural constraint and the heavy problem of equipment button, realized that major diameter fuselage frame section load applying, structural constraint and equipment buckles weight, for later similar static test is offered reference.
The accompanying drawing explanation
Fig. 1 is the structural representation that major diameter airframe test of the present invention loads fixture;
Fig. 2 is the lateral plan of Fig. 1,
Wherein, 1, opposed end panel 2, all power ring 3, covering 4, triangular beam 5, loading beam.
The specific embodiment
The present invention is described further below in conjunction with accompanying drawing:
Refer to Fig. 1, major diameter airframe test of the present invention loads fixture and comprises opposed end panel, equal power ring, covering, triangular beam, loading beam.Described opposed end panel is the circular ring structure be complementary with the fuselage transition phase, and all the power ring is surrounded on the opposed end panel Internal and external cycle, and all power ring one side connects opposed end panel, and opposite side connects the loading facilities that applies concentrated load through covering.
Wherein, each block construction design feature and function are as follows:
Opposed end panel-design according to the size of test article butt end frame, the opposed end panel center ring is butt joint ring connecting bolt docked with test article, butt joint ring is suitable to the distance of inside and outside both sides expansion, suitable with both sides power transmission distance inside and outside guaranteeing opposed end panel, thus reach approximately equalised power transmission effect.The rigidity of the thickness effect end plate of opposed end panel, and remote effect end plate effect of load balancing mechanism, need determine according to strength Calculation Result.Because the opposed end panel size is larger, the directly more difficult enforcement of whole processing, can adopt polylith to sting than tablet and the form of splicing completes, and splicing mouthful adopts the bolt that gathers to connect, to guarantee the continuity of splicing mouthful.
Equal power ring-be welded by the larger section bar of radial rigidity, consider the comfort feature loaded, and generally adopts double-deck channel-section steel or I-beam section, and around both sides inside and outside opposed end panel, all the power ring is connected by the bolt that gathers with opposed end panel, with the homogeneity of assurance posting.
Stiffened skin-be welded than sheet steel by polylith, gathering is bolted in equal power ring opposite side, and be used to strengthening the rigidity of equal power ring, that improves equal power ring all carries performance.
The steel framed structure of triangular beam-be welded by channel-section steel, be installed on two load(ing) points of equal power ring inboard, as shown in Figure 2, when applying shearing, also apply larger moment of flexure, also solved simultaneously that load(ing) point on equal power ring is more and the space interference problem that causes can arrange in force as required.
Above-mentioned each assembly is assembled into integral body, with the butt end frame, docks with bolt, on load(ing) point, applies the load of various combination, can complete load simulatedly, and its Path of Force Transfer is:
By outside controlled hydraulic equipment, apply the load perpendicular to abutting plate, the load(ing) point of load on equal power ring, because all the power ring stiffness is large than opposed end panel, therefore most of load will be first along all power ring diffusions, then pass to opposed end panel, after the equal power ring of opposed end panel and interior outside joint stand under load again to intermediate transfer to fuselage on connecting bolt.
In above-mentioned power transmission process, there are two links to realize the uniform of concentrated load, at first be that the concentrated load that acts on equal power ring is diffused as the distributed load comparatively disperseed by equal power ring, then the distributed load comparatively disperseed will again uniform along opposed end panel when connecting bolt is transmitted, like this, when load was delivered to connecting bolt, the load distribution situation had met design requirement, thereby reached the exploitativeness of test.
Claims (8)
1. a major diameter airframe test loads fixture, it is characterized in that, comprise opposed end panel, equal power ring and covering, described opposed end panel is the circular ring structure be complementary with the fuselage transition phase, all the power ring is surrounded on the opposed end panel Internal and external cycle, all power ring one side connects opposed end panel, and opposite side connects the loading facilities that applies concentrated load through covering.
2. major diameter airframe test according to claim 1 loads fixture, it is characterized in that, opposed end panel surrounding outward flange is provided with for some through holes.
3. major diameter airframe test according to claim 2 loads fixture, it is characterized in that, opposed end panel is spliced or is made of one piece by the dull and stereotyped interlock of some uniform thickness.
4. major diameter airframe test according to claim 3 loads fixture, it is characterized in that, and the approximate annulus of described equal power ring for being welded by some channel-section steels, all the axial dimension of power ring is between 200mm to 400mm.
5. major diameter airframe test according to claim 4 loads fixture, it is characterized in that, described covering is welded by some metal sheets of middle perforate.
6. major diameter airframe according to claim 5 test loads fixture, it is characterized in that, comprises that base is arranged on equal power ring, and both sides are for posting in addition, and the triangular beam be welded by channel-section steel.
7. major diameter airframe test according to claim 6 loads fixture, it is characterized in that, comprises and being arranged on equal power ring, be used to distributing the loading beam of concentrated load to inside and outside equal power ring.
8. major diameter airframe test according to claim 7 loads fixture, it is characterized in that, all the power ring stiffness is greater than opposed end panel rigidity.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210528700.9A CN103407579B (en) | 2012-12-10 | 2012-12-10 | A kind of major diameter airframe test loads fixture |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210528700.9A CN103407579B (en) | 2012-12-10 | 2012-12-10 | A kind of major diameter airframe test loads fixture |
Publications (2)
| Publication Number | Publication Date |
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| CN103407579A true CN103407579A (en) | 2013-11-27 |
| CN103407579B CN103407579B (en) | 2016-03-30 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201210528700.9A Active CN103407579B (en) | 2012-12-10 | 2012-12-10 | A kind of major diameter airframe test loads fixture |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104648689A (en) * | 2013-12-31 | 2015-05-27 | 中国航空工业集团公司沈阳飞机设计研究所 | Static force/fatigue testing method applicable to reinforcing frame structure |
| CN106563932A (en) * | 2015-10-08 | 2017-04-19 | 陕西飞机工业（集团）有限公司 | Novel butt joint jig |
| CN106596003A (en) * | 2016-11-29 | 2017-04-26 | 中国航空工业集团公司沈阳飞机设计研究所 | Composite aircraft fuselage section pressurizing test method |
| CN109625318A (en) * | 2018-12-07 | 2019-04-16 | 中国飞机强度研究所 | A kind of test local restriction device |
| CN110203420A (en) * | 2019-05-29 | 2019-09-06 | 陕西飞机工业（集团）有限公司 | A kind of aircraft slow test support loading simulation part before by oil pipe part |
| CN110228603A (en) * | 2019-05-29 | 2019-09-13 | 陕西飞机工业（集团）有限公司 | It is a kind of for simulating the slow test end frame of Aircraft Air state |
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| DE19921998C2 (en) * | 1999-05-12 | 2002-06-27 | Stephan Dueren | Device for inserting wings |
| US20070227434A1 (en) * | 2006-03-29 | 2007-10-04 | Matthias Gotze | Testing Device for Hull Shells |
| CN102101531A (en) * | 2009-12-22 | 2011-06-22 | 尤洛考普特德国有限公司 | Lift device for replacing dynamic or static components of helicopter-type aircraft |
| CN102730199A (en) * | 2012-07-05 | 2012-10-17 | 浙江大学 | Large-opening shape-preserving device used for large-scale airplane assembly |
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19921998C2 (en) * | 1999-05-12 | 2002-06-27 | Stephan Dueren | Device for inserting wings |
| US20070227434A1 (en) * | 2006-03-29 | 2007-10-04 | Matthias Gotze | Testing Device for Hull Shells |
| CN102101531A (en) * | 2009-12-22 | 2011-06-22 | 尤洛考普特德国有限公司 | Lift device for replacing dynamic or static components of helicopter-type aircraft |
| CN102730199A (en) * | 2012-07-05 | 2012-10-17 | 浙江大学 | Large-opening shape-preserving device used for large-scale airplane assembly |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104648689A (en) * | 2013-12-31 | 2015-05-27 | 中国航空工业集团公司沈阳飞机设计研究所 | Static force/fatigue testing method applicable to reinforcing frame structure |
| CN104648689B (en) * | 2013-12-31 | 2016-09-14 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of static(al)/fatigue test method being applicable to reinforced frame structure |
| CN106563932A (en) * | 2015-10-08 | 2017-04-19 | 陕西飞机工业（集团）有限公司 | Novel butt joint jig |
| CN106596003A (en) * | 2016-11-29 | 2017-04-26 | 中国航空工业集团公司沈阳飞机设计研究所 | Composite aircraft fuselage section pressurizing test method |
| CN106596003B (en) * | 2016-11-29 | 2019-04-23 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of composite airplane frame sections pressurising test method |
| CN109625318A (en) * | 2018-12-07 | 2019-04-16 | 中国飞机强度研究所 | A kind of test local restriction device |
| CN110203420A (en) * | 2019-05-29 | 2019-09-06 | 陕西飞机工业（集团）有限公司 | A kind of aircraft slow test support loading simulation part before by oil pipe part |
| CN110228603A (en) * | 2019-05-29 | 2019-09-13 | 陕西飞机工业（集团）有限公司 | It is a kind of for simulating the slow test end frame of Aircraft Air state |
| CN110203420B (en) * | 2019-05-29 | 2022-09-20 | 陕西飞机工业（集团）有限公司 | Aircraft static test receives oil pipe spare front support loading simulation piece |
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| Publication number | Publication date |
|---|---|
| CN103407579B (en) | 2016-03-30 |
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