CN103407579B - A kind of major diameter airframe test loads fixture - Google Patents
A kind of major diameter airframe test loads fixture Download PDFInfo
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- CN103407579B CN103407579B CN201210528700.9A CN201210528700A CN103407579B CN 103407579 B CN103407579 B CN 103407579B CN 201210528700 A CN201210528700 A CN 201210528700A CN 103407579 B CN103407579 B CN 103407579B
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- end panel
- power ring
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- 238000012360 testing method Methods 0.000 title claims abstract description 41
- 230000007704 transition Effects 0.000 claims abstract description 6
- 229910000831 Steel Inorganic materials 0.000 claims description 8
- 239000010959 steel Substances 0.000 claims description 8
- 239000002184 metal Substances 0.000 claims description 2
- 238000000034 method Methods 0.000 abstract description 9
- 238000012546 transfer Methods 0.000 abstract description 4
- 230000000694 effects Effects 0.000 description 5
- 230000005540 biological transmission Effects 0.000 description 3
- 238000013461 design Methods 0.000 description 3
- 238000003032 molecular docking Methods 0.000 description 3
- 210000001503 joint Anatomy 0.000 description 2
- 238000004364 calculation method Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000010008 shearing Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
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- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention belongs to test loading technique, relate to the test of a kind of major diameter airframe and load fixture.Described major diameter airframe test loads fixture and comprises opposed end panel, all power ring and covering.Described opposed end panel is the circular ring structure matched with fuselage transition phase, and equal power ring is surrounded on opposed end panel Internal and external cycle, and equal power ring side connects opposed end panel, and opposite side connects the loading facilities applying concentrated load through covering.The present invention is applied in the test of aircraft multi-wall interference force-transfer characteristic, achieve the accurate applying of the various load of butt end frame section, ensure that the reasonableness of butt end frame distribution of force, provide the good constraint of test article, and facilitate the button weight of loading facilities.In theory, this loading facilities and testing technique thereof, can realize the applying of any fuselage frame section Arbitrary Loads.
Description
Technical field
The invention belongs to test loading technique, relate to the test of a kind of major diameter airframe and load fixture.
Background technology
For airframe frame section subassembly test, the method of usual employing increases docking transitional frame section at airframe examination frame section end face, by Special test fixture, transitional frame section is fixed on load wall, realize the clamped constraint of test article, examine various load suffered by frame end by load wall passive applying fuselage.This method is only applicable to the situation that test article only has a section face.Because load wall is as the constraint of test article, bear the unbalance load of test article and other initiatively put loading error, the load of passive applying in theory is often difficult to the requirement meeting test loading accuracy, adds test difficulty.According to Saint Venant's principle, the impact of fixed-end boundary condition on test article examination section is down to minimum, needs sufficiently long docking transition phase.For major diameter fuselage, docking transition section length more will increase, and this not only requires a great deal of time, and also add experimentation cost.
For the fuselage frame section of existence 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, reduces the support of test article to the impact at examination position; Load bogusware as test, reduce the installation workload of support, provide the access port that test initiatively loads.
Summary of the invention
The object of the invention is: provide one can solve the constraint of fuselage frame section both ends of the surface and loading problem, reduce the impact of constraint on examination position, make examination position carry major diameter airframe test more accurately and load fixture.
Technical scheme of the present invention is: a kind of major diameter airframe test loads fixture, it comprises opposed end panel, all power ring and covering, described opposed end panel is the circular ring structure matched with fuselage transition phase, equal power ring is surrounded on opposed end panel Internal and external cycle, equal power ring side connects opposed end panel, and opposite side connects the loading facilities applying concentrated load through covering.
Opposed end panel surrounding outward flange is provided with for some through holes.
Opposed end panel is spliced by the occlusion of some uniform thickness flat boards or is made of one piece.
Described equal power ring is the approximate annulus be welded by some channel-section steels, and the axial dimension of equal power ring is between 200mm to 400mm.
Described covering is welded by some metal sheets of central aperture.
Comprising base is arranged on equal power ring, and both sides are used for posting in addition, and the triangular beam be welded by channel-section steel.
Comprise and be arranged on equal power ring, for distributing the loading beam of concentrated load to inside and outside equal power ring.
Equal 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 multi-wall interference force-transfer characteristic, achieve the accurate applying of the various load of butt end frame section, ensure that the reasonableness of butt end frame distribution of force, provide the good constraint of test article, and facilitate the button weight of loading facilities.In theory, this loading facilities and testing technique thereof, the applying of any fuselage frame section Arbitrary Loads can be realized, thus solve the heavy problem of the applying of major diameter fuselage load, structural constraint and equipment button, achieve major diameter fuselage frame section load applying, structural constraint and equipment and buckle weight, for later similar static test is offered reference.
Accompanying drawing explanation
Fig. 1 is the structural representation that major diameter airframe of the present invention test 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.
Detailed description of the invention
Below in conjunction with accompanying drawing, the present invention is described further:
Refer to Fig. 1, major diameter airframe test of the present invention loads fixture and comprises opposed end panel, all power ring, covering, triangular beam, loading beam.Described opposed end panel is the circular ring structure matched with fuselage transition phase, and equal power ring is surrounded on opposed end panel Internal and external cycle, and equal power ring side connects opposed end panel, and opposite side connects the loading facilities applying concentrated load through covering.
Wherein, each block construction design feature and function as follows:
Opposed end panel-design according to the size of test article butt end frame, opposed end panel center ring is the butt joint ring docked connecting bolt with test article, the distance that butt joint ring is expanded to inside and outside both sides is suitable, to ensure that inside and outside opposed end panel, both sides power transmission distance quite, 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 opposed end panel size is comparatively large, the more difficult enforcement of direct overall processing, can adopt polylith to sting compared with tablet and the form of splicing completes, and splicing mouth adopts the bolt that gathers to connect, to ensure the continuity of splicing mouth.
Equal power ring-be welded by the section bar that radial rigidity is larger, considers the comfort feature loaded, the double-deck channel-section steel of general employing or I-beam section, and around both sides inside and outside opposed end panel, equal power ring is connected, to ensure the homogeneity of posting by the bolt that gathers with opposed end panel.
Stiffened skin-by polylith comparatively sheet steel be welded, gather be bolted in equal power ring opposite side, for 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 inside equal power ring, as shown in Figure 2, also larger moment of flexure is applied while applying shearing, also solve the more and space interference problem that causes of load(ing) point on equal power ring simultaneously, can arrange as required in force.
Above-mentioned each assembling components integrally, docks with butt end frame with bolt, and load(ing) point applies the load of various combination, can complete load simulated, and its Path of Force Transfer is:
The load perpendicular to abutting plate is applied by outside controlled hydraulic equipment, load acts on the load(ing) point on equal power ring, because equal power ring stiffness is large compared with opposed end panel, therefore most of load will first along equal power ring diffusion, then pass to opposed end panel, after opposed end panel and interior outside equal power ring joint stand under load again to intermediate transfer to fuselage on connecting bolt.
In above-mentioned power transmission process, two links are had to realize the uniform of concentrated load, first be that the concentrated load acting on equal power ring is diffused as by equal power ring the distributed load comparatively disperseed, then the distributed load comparatively disperseed is along opposed end panel to will be again uniform when transmitting connecting bolt, like this, when dynamic changes process is to during to connecting bolt, load diatibution situation has met design requirement, thus reaches the exploitativeness of test.
Claims (5)
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 matched with fuselage transition phase, equal power ring is surrounded on opposed end panel Internal and external cycle, equal power ring side connects opposed end panel, opposite side connects the loading facilities applying concentrated load through covering, described equal power ring is the approximate annulus be welded by some channel-section steels, the axial dimension of equal power ring is between 200mm to 400mm, and also comprise and be arranged on equal power ring, for distributing the loading beam of concentrated load to inside and outside equal power ring, equal power ring stiffness is greater than opposed end panel rigidity.
2. major diameter airframe test according to claim 1 loads fixture, and 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 by the occlusion of some uniform thickness flat boards or is made of one piece.
4. major diameter airframe test according to claim 3 loads fixture, and it is characterized in that, described covering is welded by some metal sheets of central aperture.
5. major diameter airframe test according to claim 4 loads fixture, and it is characterized in that, comprise base and be arranged on equal power ring, both sides are used for posting in addition, and the triangular beam be welded by channel-section steel.
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 |
|---|---|
| CN103407579A CN103407579A (en) | 2013-11-27 |
| CN103407579B true 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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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
| CN109625318B (en) * | 2018-12-07 | 2022-04-19 | 中国飞机强度研究所 | Test local restraint device |
| CN110228603B (en) * | 2019-05-29 | 2022-11-18 | 陕西飞机工业（集团）有限公司 | Static test end frame for simulating 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 |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19921998C2 (en) * | 1999-05-12 | 2002-06-27 | Stephan Dueren | Device for inserting wings |
| 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 |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102006062794B4 (en) * | 2006-03-29 | 2010-04-22 | Ima Materialforschung Und Anwendungstechnik Gmbh | Testing device for frame reinforced hull shells |
-
2012
- 2012-12-10 CN CN201210528700.9A patent/CN103407579B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE19921998C2 (en) * | 1999-05-12 | 2002-06-27 | Stephan Dueren | Device for inserting wings |
| 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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| CN103407579A (en) | 2013-11-27 |
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