CN103149075B - Strength testing device and testing method for fuselage wall plate under action of combined loads - Google Patents
Strength testing device and testing method for fuselage wall plate under action of combined loads Download PDFInfo
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- CN103149075B CN103149075B CN201210528413.8A CN201210528413A CN103149075B CN 103149075 B CN103149075 B CN 103149075B CN 201210528413 A CN201210528413 A CN 201210528413A CN 103149075 B CN103149075 B CN 103149075B
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Abstract
The invention belongs to a strength testing device and a testing method for a fuselage wall plate under the action of combined loads. The strength testing device for the fuselage wall plate under the action of the combined loads comprises corner boxes, airtight end plates, the fuselage wall plate, a hinge, mandrils, keels and arc-shaped rubber plates, wherein the airtight end plates are arranged at two ends of the fuselage wall plate, the corner boxes are arc-shaped components and installed at a combined part between the airtight end plates and the fuselage wall plate, the keels are arc-shaped frames, the keels are connected in a pasting mode through the arch-shaped rubber plates to form a keel group, the mandrils are installed on web plates at two ends of the keel group, and the hinge is arranged on the fuselage wall plate and the keel group and achieves hinged connection of the fuselage wall plate and the keel group. According to the strength testing device and the testing method for the fuselage wall plate under the action of the combined loads, boundary conditions of the fuselage wall plate can be effectively imitated, the combined loads are conveniently used for achieving a strength test, and due to the fact that drawing loads and compressing loads are not used at the same time, the applied combined loads are one kind of or two kinds of or three kinds of internal pressure loads, drawing loads (or compressing loads) and shear loads.
Description
Technical field
The invention belongs to strength of aircraft experimental technique, relate to a kind of fuselage wallboard combined load strength test device and test method.
Background technology
The strength test of fuselage wallboard is the most important foundation of airframe design, and the domestic fuselage wallboard strength test carried out at present has: the test of fuselage wall plate stretching, fuselage wallboard compression test, fuselage wallboard shear test, the internal pressure test of fuselage wallboard, fuselage wall plate stretching+inner pressuring load test etc.; Form a series of strength test device.
The strength test of fuselage wallboard comprises 11 kinds of load working conditions altogether: interior pressure operating mode, stretching operating mode, compression condition, shearing operating mode, interior pressure+stretching operating mode, interior pressure+compression condition, interior pressure+shearing operating mode, stretching+shearing operating mode, compression+shearing operating mode, interior pressure+stretching+shearing operating mode, interior pressure+compression+shearing operating mode.Existing fuselage wallboard test unit only can carry out a part of load working condition test in these 11 kinds of load working conditions.Existing wallboard test unit is generally made up of loading portal frame, loading web member, loading pressurized strut, fuselage wallboard testpieces etc., if Fig. 1 is fuselage wall plate stretching density of load test unit, this test unit forms primarily of loading portal frame (being made up of two gantry upright post and a gantry beam), web member, loading pressurized strut, fuselage wallboard testpieces etc., and this test unit can complete the test of fuselage wall plate stretching load working condition.
Such as aircraft fuselage wallboard pressure, cut allowable value research exactly respectively axial compression and shear test have been carried out to 36 and 50 fuselage wallboards, the determination being intended to cut for the pressure of this airframe typical case wallboard allowable value provides foundation, the charger of the research can only carry out individual event compression and the test of individual event shear-type load, and during actual use, limitation is larger.
Summary of the invention
Object of the present invention: provide a kind of fuselage wallboard combined load boundary condition of effectively simulating and be convenient to again apply the strength test device of combined load and test method.
Technical scheme of the present invention is: a kind of fuselage wallboard combined load strength test device, it comprises angle box, airtight end plate, fuselage wallboard, hinge, push rod, keel, arc rubber slab, wherein, airtight end plate is arranged on the two ends of fuselage wallboard, angle box is arc component, be arranged on the joint portion between airtight end plate and fuselage wallboard, keel are arc skeleton, by arc rubber slab bonding one-tenth keel group between each keel, push rod is arranged on two end webs of keel group, hinge is arranged in fuselage wallboard and keel group, the twisting link of both realizations.
The upper leaf of hinge of described hinge has the radian identical with fuselage wallboard, and lower jaw sheet has the radian identical with keel web.
Described push rod is the rod member of two sections of screw thread sockets.
Described keel are that H steel hot bending processes.
Described keel group axial rigidity is not more than the per mille of fuselage wallboard axial rigidity.
Described arc rubber slab shape and size are identical with keel, and thickness is at least 20mm.
Described angle box and airtight end plate interface are provided with ring-shaped rubber pad.
Described airtight end plate is provided with pressurising joint and cover plate for manhole.
A kind of fuselage wallboard combined load Strength Testing Methods, when carrying out load load test, the mode of being inflated by pressurising joint carries out inner pressuring load applying, by compressing or stretch airtight end plate applying stretching or compressive load, apply shear-type load by the mode reversing airtight end plate, and achieve the pressure heart following loading of stretching or compressive load.
A kind of fuselage wallboard combined load Strength Testing Methods, when carrying out boundary condition simulation, by the oxygen blast cyanidation of adjusting yoke length simulation fuselage wallboard under inner pressuring load effect; Keel group axial rigidity is not more than the per mille of fuselage wallboard axial rigidity, guarantees that compression or tensile load are only applied on fuselage wallboard, the shortening of simulation fuselage wallboard under compression or tensile load effect or elongation strain; The mode adopting the single closed chamber formed by fuselage wallboard and keel group to be cut simulates fuselage wallboard shear-type load boundary condition.
The invention has the beneficial effects as follows:
1) interior pressure, stretching (or compression), shear-type load boundary condition (as described in technical scheme) is effectively simulated first; All operating mode strength tests under carrying out fuselage wallboard Action of Combined Loads.Test unit in the past only can carry out one or more the operating mode strength tests in 11 kinds of operating modes, and this test unit is all operating mode strength tests under carrying out Action of Combined Loads.
2) loading that the pressure heart of stretching (or compression) load is servo-actuated is achieved first: when shear-type load applies, (or compression) load that stretches is applied to the pressure of fuselage wallboard in the heart all the time, and the pressure heart of (or compression) load that stretches is servo-actuated along with the applying of shear-type load.
3) achieve first and do not apply shear-type load when there is no transition section by moment of torsion.During usual applying shear-type load, fuselage wallboard two bent limits all need to process the transition section suitable with fuselage wallboard length, to reduce boundary effect, adopt this test unit, because shearing flow is applied in a single closed cell structure, do not need processing transition section just can apply uniform shear-type load.
4) by test prove this test unit and test method science feasible, meet engineering test requirement.
Accompanying drawing explanation
Fig. 1 is a kind of prior art fuselage wallboard combined load strength test device structural drawing;
Fig. 2 is the structural representation of fuselage wallboard combined load strength test device of the present invention;
Fig. 3 is fuselage wall plate structure schematic diagram;
Fig. 4 is fuselage wallboard force diagram;
Fig. 5 is angle box structural representation;
Fig. 6 is ring-shaped rubber pad structural representation;
Fig. 7 is keel structure schematic diagram;
Fig. 8 is arc rubber slab structural representation;
Fig. 9 is push rod structure schematic diagram;
Figure 10 is hinge structure schematic diagram;
Figure 11 is airtight end plate plan view;
Figure 12 is subassembly one schematic diagram;
Figure 13 is subassembly two schematic diagram;
Figure 14 is subassembly three schematic diagram;
Figure 15 is subassembly four schematic diagram;
Figure 16 is that fuselage wallboard combined load strength test device combined load of the present invention applies schematic diagram;
Figure 17 is fuselage wallboard deformation result schematic diagram under inner pressuring load effect;
Figure 18 is that interior pressure working condition tests fuselage wall panel skin answers F-histogram;
Figure 19 is that compression condition test fuselage wall panel skin answers F-histogram;
Figure 20 is that compression condition test keel answer F-histogram;
Figure 21 shears working condition tests fuselage wall panel skin shear stress histogram;
Wherein, 1-ring-shaped rubber pad, 2-angle box, the airtight end plate of 3-, 4-fuselage wallboard, 5-hinge, 6-push rod, 7-keel, 8-arc rubber slab, 9-pressurising joint, 10-cover plate for manhole.
Embodiment
Below by specific embodiment, the present invention is described in further detail:
Refer to Fig. 2, it is the structural representation of fuselage wallboard combined load strength test device of the present invention.Described fuselage wallboard combined load strength test device is primarily of 9 kinds of parts such as ring-shaped rubber pad 1, angle box 2, airtight end plate 3, hinge 5, push rod 6, keel 7, arc rubber slab 8, pressurising joint 9, covers plate for manhole and fuselage wallboard 4 is bolted or bonding agent is linked and packed forms.
As shown in Figure 3, fuselage wallboard refers to that a section of choosing from fuselage barrels comprises the airframe structure of 5 ~ 9 long purlins and 5 frames and one piece of covering.
Apply combined load and refer to one, two or three load that can apply in inner pressuring load, stretching (or compression) load and shear-type load.Because tensile load and compressive load can not apply simultaneously, so combined load comprises following 11 kinds of operating modes altogether: interior pressure operating mode, stretching operating mode, compression condition, shearing operating mode, interior pressure+stretching operating mode, interior pressure+compression condition, interior pressure+shearing operating mode, stretching+shearing operating mode, compression+shearing operating mode, interior pressure+stretching+shearing operating mode, interior pressure+compression+shearing operating mode.
Fuselage wallboard needs the load applied to have inner pressuring load, stretching (or compression) load and shear-type load.Inner pressuring load is applied to the inside surface of fuselage wallboard, and stretching, (or compression) load applying is on two bent limits of fuselage wallboard, and shear-type load is also applied on two bent limits of fuselage wallboard; Inner pressuring load is applied to the inside surface of fuselage wallboard, the straight flange of fuselage wallboard produces constraint tensile load, shear-type load is applied on two bent limits of fuselage wallboard, and the straight flange of fuselage wallboard produces paired shear-type load, and fuselage wallboard is as shown in Figure 4 stressed.
As shown in Figure 5, angle box is circular arc steel beam column, and the cross sectional shape of cross sectional shape and angle steel is similar, plane and curved surface are processed with two row's bolts hole uniformly, angle box is two pieces altogether, is arranged on the outside of termination, fuselage wallboard two bent limits respectively, and effect is arranged on airtight end plate on bent for fuselage wallboard limit.
As shown in Figure 6, ring-shaped rubber pad is the nitrile rubber plate of thickness 5mm, be processed into ellipse, two pieces altogether, be arranged on the inner side of two pieces of airtight end plates respectively, ring-shaped rubber pad the first half is arranged between airtight end plate and angle box, and effect is the space between the airtight end plate of sealing and angle box, ring-shaped rubber pad the latter half is arranged between airtight end plate and keel group, and effect is the space between the airtight end plate of sealing and keel group.
As shown in Figure 7, keel are processed by 100 type H steel hot bendings, article two, listrium is processed with bolt hole uniformly, be connected with keel for keel, the web at keel two ends is processed with the circular hole for installing push rod, keel quantity is more, concrete quantity is determined by the length of fuselage wallboard, bonding arc rubber slab composition keel group between keel with keel, keel group has two effects, and one is composition closed structure, conveniently applies inner pressuring load, two is form single closed cell structure with fuselage wallboard, can transmit shear-type load.
As shown in Figure 8, arc rubber slab is the nitrile rubber plate of thickness 20mm, be processed into the circular arc identical with keel listrium, quantity is few one of keel comparatively, and arc rubber slab is first bonded between two keel, then is connected with coupled keel listrium by arc rubber slab with bolt, arc rubber slab has two effects, one is seal two adjacent keel, and two is reduce test unit fuselage wallboard long purlin directional stiffness, arc rubber slab structure.
As shown in Figure 9, push rod is steel beam column, and by the principle design of swivel nut, its length can regulate.Push rod is arranged on keel two ends, because the keel at keel group two ends do not need to install push rod, so push rod quantity comparatively few two of keel, push rod can increase the rigidity of keel, multiple push rod is arranged on test unit and forms push rod group, and push rod group can regulate the displacement of test unit fuselage wallboard straight flange.
As shown in Figure 10, hinge is steel beam column, be made up of upper leaf of hinge, lower jaw sheet and hinge axis, identical with ready-made hinge structure, just upper leaf of hinge is with the radian identical with fuselage wallboard, lower jaw sheet is with the radian identical with keel, and hinge quantity is the twice of keel, and the effect of hinge is connected with keel two ends by fuselage wallboard two straight flange.
As shown in figure 11, airtight end plate is the thick rectangle steel component of 40mm, two pieces altogether, the airtight end plate top of every block is processed with and is connected with bolt hole with angle box, bottom is processed with the bolt hole be connected with keel, middle part is processed with square manhole, and in addition, the airtight end plate of every block is also processed with pressurising jiont treatment hole, cover plate for manhole mounting hole, strain measurement cable portal.
Pressurising joint is circular steel component, and two pieces, is arranged on airtight end plate altogether, applies inner pressuring load for fuselage wallboard.
Cover plate for manhole is square bar component, and two pieces, is arranged on airtight end plate, for test unit Manhole Sealing Joints respectively altogether.
Fuselage wallboard combined load strength test device connection and installation of the present invention are as follows:
First connect shaping composition subassembly one with bolt afterwards by alternately bonding to keel and arc rubber slab, subassembly one two ends should be keel, as shown in figure 12.Secondly push rod is arranged on keel two ends composition subassembly two, as shown in figure 13, two keel of subassembly two two ends do not install push rod, reduce a thrust bearing of friction force when being all provided with the rubber sheet gasket for sealing at push rod two ends and regulating push rod.Fuselage wallboard two articles of straight flanges are arranged on the keel of subassembly 2 two articles of straight flanges with hinge by the 3rd, composition subassembly three, as shown in figure 14.Finally airtight end plate is arranged on the two ends of subassembly three, then on airtight end plate, pressurising joint and cover plate for manhole is installed, composition subassembly four, as shown in figure 15.
Test unit is characterised in that the combined load that can apply fuselage wallboard:
When carrying out the combined load strength test of fuselage wallboard, the airtight end plate of test unit one end is arranged on carrying column and forms fixing support, the airtight end plate of the other end is arranged on loading frame, and loading frame is installed on the rotary shaft, turning axle is fixed on carrying column, loading frame can move forward and backward on the rotary shaft, can rotate again around turning axle.Stretch (or compression) and shear-type load is applied: (or compression) load that stretches is applied by three pressurized struts by loading frame, the pressure heart of three pressurized strut imposed loads fuselage wall plate stretching (or compression) pressure in the heart, three pressurized struts are shunk and are applied compressive load, three overhanging applying tensile loads of pressurized strut; Shear-type load is applied by reversing loading frame, shear-type load is applied by two pressurized struts, and a pressurized strut is shunk and loaded, the overhanging loading of another pressurized strut, two pressurized struts apply the load that size is identical, direction is contrary, and two load form a moment to apply shear-type load.Apply inner pressuring load by the pressurising joint on the airtight end plate of stiff end, test unit combined load applies as shown in figure 16.
Test unit is characterised in that the simulation of boundary condition:
The boundary condition imitation of fuselage wallboard inner pressuring load: test unit simulates the oxygen blast cyanidation of fuselage wallboard under inner pressuring load effect by regulating the length of push rod, push rod near airtight end plate is protruding shorter, push rod in the middle of airtight end plate is protruding longer, effectively simulates load boundary condition and the displacement boundary conditions of fuselage wallboard inner pressuring load.Because apply inner pressuring load when there is no push rod, fuselage wall slab integral outward bulge bulging deformation, cause fuselage wallboard straight flange by inside drawdown deformation, as shown in figure 17, the boundary effect at this moment on fuselage wallboard straight flange is nearly 40% of whole fuselage wallboard to the deformation result of fuselage wallboard under inner pressuring load effect.This test unit is by regulating the length of push rod, this boundary effect can be eliminated, as shown in figure 18, Figure 18 is that interior pressure working condition tests fuselage wall panel skin answers F-histogram (unit is: Mpa), covering stress is even especially as can be seen from Figure 18, proves to eliminate the boundary effect on fuselage wallboard straight flange.
The boundary condition imitation of fuselage wall plate stretching (or compression) load: unclamp test unit keel during test, coupling bolt between arc rubber slab and keel, the keel of test unit are alternately connected with arc rubber slab, the thickness of arc rubber slab is 20 millimeters, and elongation at rupture is all greater than 100%, so the axis of keel and arc rubber slab subassembly (direction, long purlin) rigidity is much smaller than fuselage wallboard, moving forward and backward like this along with the airtight end plate of on-fixed end, (or compression) load that stretches all is applied on fuselage wallboard, and can not be applied on keel and arc rubber slab subassembly, effectively simulate the boundary condition of fuselage wall plate stretching (or compression) load, as Figure 19, shown in Figure 20, Figure 19 is compression condition test fuselage wall panel skin axial stress histogram, Figure 20 is that compression condition test keel answer F-histogram, as can be seen from Figure 20, maximum stress on keel is 2.55Mpa, minimum stress is-1.96Mpa, keel stress is very little, and stress for have on the occasion of, also negative value is had, illustrate and keel do not apply compressive load, compressive load is all applied on fuselage wallboard, and Figure 19 shows that fuselage wall panel skin axial stress is very even.
The boundary condition imitation of fuselage wallboard shear-type load: the mode adopting single closed chamber to be cut is to simulate fuselage wallboard shear-type load boundary condition, fuselage wallboard and keel arc rubber slab subassembly form a single closed cell structure, the two ends of single closed cell structure are provided with airtight end plate, the shear-type load of fuselage wallboard is applied by reversing airtight end plate, the boundary condition of effective simulation fuselage wallboard shear-type load, as Figure 21 shears working condition tests fuselage wall panel skin shear stress histogram (Mpa), the stress of four stress profiles is similar especially as can be seen from Figure 20.
Claims (10)
1. a fuselage wallboard combined load strength test device, it is characterized in that: comprise angle box (2), airtight end plate (3), fuselage wallboard (4), hinge (5), push rod (6), keel (7), arc rubber slab (8), wherein, airtight end plate (3) is arranged on the two ends of fuselage wallboard (), angle box (2) is arc component, be arranged on the joint portion between airtight end plate (3) and fuselage wallboard (5), keel (7) are arc skeleton, by arc rubber slab (8) bonding one-tenth keel group between each keel, push rod (6) is arranged on two end webs of keel group, hinge (5) is arranged on fuselage wallboard (5) with in keel group, the twisting link of both realizations.
2. fuselage wallboard combined load strength test device according to claim 1, it is characterized in that, the upper leaf of hinge of hinge has the radian identical with fuselage wallboard, and lower jaw sheet has the radian identical with keel web.
3. fuselage wallboard combined load strength test device according to claim 1, is characterized in that, push rod is the rod member of two sections of screw thread sockets.
4. fuselage wallboard combined load strength test device according to claim 1, is characterized in that, described keel are the skeleton that H steel hot bending processes.
5. fuselage wallboard combined load strength test device according to claim 4, it is characterized in that, described keel group axial rigidity is not more than the per mille of fuselage wallboard axial rigidity.
6. fuselage wallboard combined load strength test device according to claim 1, is characterized in that, described arc rubber slab shape and size are identical with keel, and thickness is at least 20mm.
7. fuselage wallboard combined load strength test device according to claim 1, is characterized in that, described angle box and airtight end plate interface are provided with ring-shaped rubber pad (1).
8. fuselage wallboard combined load strength test device according to claim 7, is characterized in that, described airtight end plate is provided with pressurising joint (9) and cover plate for manhole (10).
9. a fuselage wallboard combined load Strength Testing Methods, it is characterized in that, when utilizing the fuselage wallboard combined load strength test device of any one of claim 1 to 8 to carry out load load test, the mode of being inflated by pressurising joint carries out inner pressuring load applying, by compressing or stretch airtight end plate applying stretching or compressive load, apply shear-type load by the mode reversing airtight end plate, and achieve the pressure heart following loading of stretching or compressive load.
10. a fuselage wallboard combined load Strength Testing Methods, it is characterized in that, when utilizing the fuselage wallboard combined load strength test device of any one of claim 1 to 8 to carry out boundary condition simulation, by the oxygen blast cyanidation of adjusting yoke length simulation fuselage wallboard under inner pressuring load effect; Keel group axial rigidity is not more than the per mille of fuselage wallboard axial rigidity, guarantees that compression or tensile load are only applied on fuselage wallboard, the shortening of simulation fuselage wallboard under compression or tensile load effect or elongation strain; The mode adopting the single closed chamber formed by fuselage wallboard and keel group to be cut simulates fuselage wallboard shear-type load boundary condition.
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| CN201210528413.8A CN103149075B (en) | 2012-12-10 | 2012-12-10 | Strength testing device and testing method for fuselage wall plate under action of combined loads |
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| CN113155606B (en) * | 2021-03-30 | 2024-06-11 | 中国飞机强度研究所 | Fuselage wallboard mechanical property test device |
| CN113340711A (en) * | 2021-06-11 | 2021-09-03 | 中国飞机强度研究所 | Reinforced wallboard static fatigue load application test device |
| CN114397186A (en) * | 2022-01-16 | 2022-04-26 | 李成虎 | Test device for combined action of normal pressure and other loads of composite material laminated plate |
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102288483A (en) * | 2011-07-08 | 2011-12-21 | 中国飞机强度研究所 | Supporting clamp for compression stabilization experiment of reinforced wallboard and supporting coefficient testing method for end socket |
| CN102607940A (en) * | 2012-03-26 | 2012-07-25 | 南京航空航天大学 | Tensile-shear test loading device with flight structure |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7246527B2 (en) * | 2004-11-12 | 2007-07-24 | The Boeing Company | E-fixture |
-
2012
- 2012-12-10 CN CN201210528413.8A patent/CN103149075B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102288483A (en) * | 2011-07-08 | 2011-12-21 | 中国飞机强度研究所 | Supporting clamp for compression stabilization experiment of reinforced wallboard and supporting coefficient testing method for end socket |
| CN102607940A (en) * | 2012-03-26 | 2012-07-25 | 南京航空航天大学 | Tensile-shear test loading device with flight structure |
Non-Patent Citations (1)
| Title |
|---|
| 加筋板结构强度分析软件STRANAS设计和应用;吴存利等;《强度与环境》;20110630;第38卷(第03期);36-44 * |
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