CN103149075A - 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
- Publication number
- CN103149075A CN103149075A CN2012105284138A CN201210528413A CN103149075A CN 103149075 A CN103149075 A CN 103149075A CN 2012105284138 A CN2012105284138 A CN 2012105284138A CN 201210528413 A CN201210528413 A CN 201210528413A CN 103149075 A CN103149075 A CN 103149075A
- Authority
- CN
- China
- Prior art keywords
- fuselage wallboard
- keel
- fuselage
- load
- test device
- 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.)
- Granted
Links
Images
Landscapes
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
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 the 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 of carrying 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 generally forms by loading portal frame, loading web member, loading pressurized strut, fuselage wallboard testpieces etc., be fuselage wall plate stretching density of load test unit as Fig. 1, this test unit mainly forms by loading portal frame (being made of two gantry upright post and a gantry beam), web member, loading pressurized strut, fuselage wallboard testpieces etc., and this test unit can be completed the test of fuselage wall plate stretching load working condition.
For example to press, cut allowable value research be exactly that 36 and 50 fuselage wallboards have been carried out respectively axial compression and shear test to aircraft fuselage wallboard, be intended to determine to provide foundation for what the pressure of this airframe typical case wallboard was cut allowable value, the charger of the research can only carry out individual event compression and the test of individual event shear-type load, and during actual the use, limitation is larger.
Summary of the invention
Purpose of the present invention: provide a kind of and can effectively simulate strength test device and the test method that fuselage wallboard combined load boundary condition is convenient to again apply combined load.
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, the angle box is arc component, be arranged on the joint portion between airtight end plate and fuselage wallboard, keel are the arc skeleton, pass through the bonding one-tenth keel of arc rubber slab group between each keel, push rod is arranged on two end webs of keel group, hinge is arranged on fuselage wallboard and keel group, realizes twisting link both.
The upper leaf of hinge of described hinge has the radian identical with the fuselage wallboard, and the lower jaw sheet has the radian identical with the keel web.
Described push rod is the rod member of two sections 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 the load load test, carrying out inner pressuring load by the mode of pressurising joint inflation applies, apply by compression or the airtight end plate that stretches and stretch or compressive load, apply shear-type load by the mode of reversing airtight end plate, and realized the pressure heart following loading of stretching or compressive load.
A kind of fuselage wallboard combined load Strength Testing Methods is when carrying out boundary condition simulation, by the bulging distortion of adjusting yoke length simulation fuselage wallboard under the 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 only are applied on the fuselage wallboard, shortening or the elongation strain of simulation fuselage wallboard under compression or tensile load effect; The mode that single closed chamber that employing is formed by fuselage wallboard and keel group is cut is simulated 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) have effectively been simulated first; Can carry out all operating mode strength tests under 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 can carry out all operating mode strength tests under Action of Combined Loads.
2) realized first the servo-actuated loading of the pressure heart of stretching (or compression) load: when shear-type load applies, the pressure that (or compression) load that stretches is applied to the fuselage wallboard all the time in the heart, and the pressure heart of (or compression) load that stretches is servo-actuated along with applying of shear-type load.
3) realized first in the situation that do not have transition section to apply shear-type load by moment of torsion.When usually applying shear-type load, two bent limits of fuselage wallboard all need 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 chamber structure, need process transition section and just can apply uniform shear-type load.
4) feasible by this test unit of evidence and test method science, satisfy the engineering test requirement.
Description of drawings
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 the ring-shaped rubber pad structural representation;
Fig. 7 is the keel structure schematic diagram;
Fig. 8 is arc rubber slab structural representation;
Fig. 9 is the push rod structure schematic diagram;
Figure 10 is the 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 the inner pressuring load effect;
Figure 18 is that interior pressure working condition tests fuselage wall panel skin is answered F-histogram;
Figure 19 is that compression condition test fuselage wall panel skin is answered F-histogram;
Figure 20 is that compression condition test keel are answered 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
The present invention is described in further detail below by specific embodiment:
See also 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 mainly by 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 with fuselage wallboard 4 is bolted or bonding agent is linked and packed forms.
As shown in Figure 3, the fuselage wallboard refers to one section airframe structure that comprises 5 ~ 9 long purlins and 5 frames and a covering choosing from the fuselage cylinder.
Apply combined load and refer to apply a kind of, two or three load 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.
The load that the fuselage wallboard need to apply has inner pressuring load, stretching (or compression) load and shear-type load.Inner pressuring load is applied to the inside surface of fuselage wallboard, and load applying is on two bent limits of fuselage wallboard in stretching (or compression), and shear-type load also is applied on two bent limits of fuselage wallboard; Inner pressuring load is applied to the inside surface of fuselage wallboard, produce the constraint tensile load on the straight flange of fuselage wallboard, shear-type load is applied on two bent limits of fuselage wallboard, produces paired shear-type load on the straight flange of fuselage wallboard, and the fuselage wallboard is as shown in Figure 4 stressed.
As shown in Figure 5, the angle box is circular arc steel member, 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, totally two, angle box is arranged on respectively the outside of termination, two bent limits of fuselage wallboard, and effect is that fuselage wallboard bent limit is arranged on airtight end plate.
As shown in Figure 6, ring-shaped rubber pad is the nitrile rubber plate of thickness 5mm, be processed into ellipse, totally two, be arranged on respectively the inboard of two airtight end plates, 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, being used for keel is connected with keel, be processed with on the web at keel two ends for the circular hole that push rod is installed, keel quantity is more, concrete quantity is determined by the length of fuselage wallboard, between keel and keel, bonding arc rubber slab forms the keel group, the keel group has two effects, and the one, form closed structure, conveniently apply inner pressuring load, the 2nd, and the single closed chamber structure of fuselage wallboard composition, shear-type load can be transmitted.
As shown in Figure 8, the arc rubber slab is the nitrile rubber plate of thickness 20mm, be processed into the circular arc identical with the keel listrium, few one than keel of quantity, the arc rubber slab first is bonded between two keel, then with bolt, the arc rubber slab is connected with the keel listrium of being connected, the arc rubber slab has two effects, the one, seal two adjacent keel, the 2nd, reduce test unit fuselage wallboard and grow purlin directional stiffness, arc rubber slab structure.
As shown in Figure 9, push rod is the steel member, presses the principle design of swivel nut, and its length can be regulated.Push rod is arranged on the keel two ends, because the keel at keel group two ends do not need to install push rod, so few two than keel of push rod quantity, push rod can increase the rigidity of keel, a plurality of push rods are arranged on test unit and form the push rod group, the displacement that the push rod group can adjusting test device fuselage wallboard straight flange.
As shown in figure 10, hinge is the steel member, formed by upper leaf of hinge, lower jaw sheet and hinge axis, identical with the ready-made hinge structure, just upper leaf of hinge is with the radian identical with the fuselage wallboard, the lower jaw sheet is with the radian identical with keel, and hinge quantity is the twice of keel, and the effect of hinge is that fuselage wallboard two straight flanges are connected with the keel two ends.
As shown in figure 11, airtight end plate is the thick rectangle steel member of 40mm, totally two, every airtight end plate top is processed with to be connected with the angle box uses bolt hole, the bottom is processed with the bolt hole that is connected with keel, the middle part is processed with square manhole, and in addition, every airtight end plate also is processed with pressurising jiont treatment hole, cover plate for manhole mounting hole, strain measurement cable and portals etc.
The pressurising joint is the circular steel member, totally two, be arranged on airtight end plate, and be used for the fuselage wallboard and apply inner pressuring load.
Cover plate for manhole is the square bar member, totally two, be arranged on respectively on airtight end plate, and be used for the test unit Manhole Sealing Joints.
Fuselage wallboard combined load strength test device connection and installation of the present invention are as follows:
At first keel and arc rubber slab are replaced and bondingly be connected moulding with bolt and form subassembly one afterwards, subassembly one two ends should be keel, as shown in figure 12.Secondly push rod is arranged on keel two ends and forms subassembly two, as shown in figure 13, two keel of subassembly two two ends are not installed push rod, all are equipped with for the rubber sheet gasket of sealing at push rod two ends and reduce a thrust bearing of friction force when regulating push rod.The 3rd use hinge is arranged on two straight flanges of fuselage wallboard on the keel of 2 two straight flanges of subassembly, forms subassembly three, as shown in figure 14.At last 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, form subassembly four, as shown in figure 15.
Test unit is characterised in that the combined load that can apply the fuselage wallboard:
When carrying out the strength test of fuselage wallboard combined load, the airtight end plate of test unit one end is arranged on and forms fixing the support on the carrying column, the airtight end plate of the other end is arranged on loading frame, and loading frame is arranged on turning axle, turning axle is fixed on the carrying column, loading frame can move front and back on turning axle, can rotate around turning axle again.Apply stretching (or compression) and shear-type load by loading frame: (or compression) load that stretches applies by three pressurized struts, the pressure heart of three pressurized strut imposed loads in the pressure of fuselage wall plate stretching (or compression) in the heart, three pressurized struts are shunk and are applied compressive load, three overhanging tensile loads that apply of pressurized strut; Apply shear-type load by reversing loading frame, shear-type load applies by two pressurized struts, and a pressurized strut is shunk and loaded, the overhanging loading of another pressurized strut, two pressurized struts apply that size is identical, the load of opposite direction, and two load form moments and apply shear-type load.Apply inner pressuring load by the pressurising joint on the airtight end plate of stiff end, the 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 is simulated the bulging distortion of fuselage wallboard under the inner pressuring load effect by the length of regulating push rod, push rod near airtight end plate is protruding shorter, push rod in the middle of airtight end plate is protruding longer, has effectively simulated load boundary condition and the displacement boundary conditions of fuselage wallboard inner pressuring load.Because in the situation that do not have push rod to apply inner pressuring load, fuselage wall slab integral outward bulge bulging deformation, cause fuselage wallboard straight flange with inside drawdown deformation, the deformation result of fuselage wallboard under the inner pressuring load effect as shown in figure 17, at this moment the boundary effect on fuselage wallboard straight flange is nearly 40% of whole fuselage wallboard.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 is answered F-histogram (unit is: Mpa), covering stress is even especially as can be seen from Figure 18, proves the boundary effect of having eliminated on fuselage wallboard straight flange.
the boundary condition imitation of fuselage wall plate stretching (or compression) load: unclamp the test unit keel during test, coupling bolt between arc rubber slab and keel, the keel of test unit alternately are connected with the arc rubber slab, the thickness of arc rubber slab is 20 millimeters, and elongation at rupture is all greater than 100%, so axially (long purlin direction) rigidity of keel and arc rubber slab subassembly is much smaller than the fuselage wallboard, moving forward and backward along with the airtight end plate of on-fixed end like this, (or compression) load that stretches all is applied on the fuselage wallboard, and can not be applied on keel and arc rubber slab subassembly, effectively simulated 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 are answered 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, negative value is also arranged, illustrate and do not apply compressive load on keel, compressive load all is applied on the 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 that adopts single closed chamber to be cut is simulated fuselage wallboard shear-type load boundary condition, fuselage wallboard and keel arc rubber slab subassembly form a single closed chamber structure, the two ends of single closed chamber structure are equipped with airtight end plate, apply the shear-type load of fuselage wallboard by reversing airtight end plate, effectively simulate the boundary condition of fuselage wallboard shear-type load, shear working condition tests fuselage wall panel skin shear stress histogram (Mpa) as Figure 21, the stress of four stress profiles is similar especially as can be seen from Figure 20.
Claims (10)
1. 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 [4], angle box [2] is arc component, be arranged on the joint portion between airtight end plate [3] and fuselage wallboard [5], keel [7] are the arc skeleton, pass through the bonding one-tenth keel of arc rubber slab [8] group between each keel, push rod [6] is arranged on two end webs of keel group, hinge [5] is arranged on fuselage wallboard [5] and keel group, realize twisting link both.
2. fuselage wallboard combined load strength test device according to claim 1, is characterized in that, the upper leaf of hinge of hinge has the radian identical with the fuselage wallboard, and the lower jaw sheet has the radian identical with the 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 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, is characterized in that, states the per mille that keel group axial rigidity is not more than 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. fuselage wallboard combined load Strength Testing Methods, it is characterized in that, when utilizing the fuselage wallboard combined load strength test device of claim 1 to 8 any one to carry out the load load test, carrying out inner pressuring load by the mode of pressurising joint inflation applies, apply by compression or the airtight end plate that stretches and stretch or compressive load, apply shear-type load by the mode of reversing airtight end plate, and realized the pressure heart following loading of stretching or compressive load.
10. fuselage wallboard combined load Strength Testing Methods, it is characterized in that, when utilizing the fuselage wallboard combined load strength test device of claim 1 to 8 any one to carry out boundary condition simulation, by the bulging distortion of adjusting yoke length simulation fuselage wallboard under the 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 only are applied on the fuselage wallboard, shortening or the elongation strain of simulation fuselage wallboard under compression or tensile load effect; The mode that single closed chamber that employing is formed by fuselage wallboard and keel group is cut is simulated fuselage wallboard shear-type load boundary condition.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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 |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103149075A true CN103149075A (en) | 2013-06-12 |
| CN103149075B CN103149075B (en) | 2015-01-28 |
Family
ID=48547280
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210528413.8A Active CN103149075B (en) | 2012-12-10 | 2012-12-10 | Strength testing device and testing method for fuselage wall plate under action of combined loads |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103149075B (en) |
Cited By (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104007017A (en) * | 2014-05-23 | 2014-08-27 | 北京理工大学 | Metal pipe stretching device |
| CN104697845A (en) * | 2013-12-06 | 2015-06-10 | 中国飞机强度研究所 | Static force/fatigue/damage tolerance test loading system of fuselage panel |
| CN104807694A (en) * | 2015-05-04 | 2015-07-29 | 中国飞机强度研究所 | Fuselage panel combined load test device |
| CN104807703A (en) * | 2015-05-12 | 2015-07-29 | 中国飞机强度研究所 | Airtight and compression loading test device of bent plate |
| CN105043899A (en) * | 2015-05-13 | 2015-11-11 | 中国飞机强度研究所 | Aircraft large-size panel shear loading apparatus |
| CN105067424A (en) * | 2015-08-31 | 2015-11-18 | 中国飞机强度研究所 | Fuselage panel test keel device and production method thereof |
| CN105388002A (en) * | 2015-10-13 | 2016-03-09 | 中国飞机强度研究所 | Airplane body wallboard pressurizing test device |
| CN106168556A (en) * | 2016-06-21 | 2016-11-30 | 中国飞机强度研究所 | A kind of anti-unstability device for docking wall strength test |
| 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 |
| CN104696513B (en) * | 2013-12-06 | 2017-10-31 | 中国飞机强度研究所 | A kind of fuselage wallboard encapsulating method |
| CN109612836A (en) * | 2018-11-12 | 2019-04-12 | 南京航空航天大学 | A kind of vertical compression experimental rig suitable for bending big siding |
| CN110329539A (en) * | 2019-07-05 | 2019-10-15 | 中国飞机强度研究所 | Packaged type bogey in a kind of aircraft target ship compression-shear test platform |
| CN110823719A (en) * | 2019-11-19 | 2020-02-21 | 中国飞机强度研究所 | Device is applyed to fuselage load |
| CN111409856A (en) * | 2020-04-17 | 2020-07-14 | 中国飞机强度研究所 | Engine body cabin section structural strength test constraint system |
| CN111537333A (en) * | 2020-06-22 | 2020-08-14 | 中国飞机强度研究所 | Bent plate comprehensive test device |
| CN112052520A (en) * | 2020-09-02 | 2020-12-08 | 中国航空工业集团公司沈阳飞机设计研究所 | Composite loading method for curved plate |
| CN112857762A (en) * | 2020-12-29 | 2021-05-28 | 中国航空工业集团公司西安飞机设计研究所 | Transition section for semi-ellipsoid structural strength test |
| CN113155606A (en) * | 2021-03-30 | 2021-07-23 | 中国飞机强度研究所 | Mechanical property test device for body wallboard |
| 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 |
| CN114739619A (en) * | 2022-06-09 | 2022-07-12 | 中国飞机强度研究所 | Combined loading test system and loading test method for airplane pneumatic impact test |
| CN113155606B (en) * | 2021-03-30 | 2024-06-11 | 中国飞机强度研究所 | Fuselage wallboard mechanical property test device |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060101921A1 (en) * | 2004-11-12 | 2006-05-18 | The Boeing Company | E-fixture |
| 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 |
-
2012
- 2012-12-10 CN CN201210528413.8A patent/CN103149075B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060101921A1 (en) * | 2004-11-12 | 2006-05-18 | The Boeing Company | E-fixture |
| 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 |
|---|
| 吴存利等: "加筋板结构强度分析软件STRANAS设计和应用", 《强度与环境》 * |
Cited By (34)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104697845B (en) * | 2013-12-06 | 2017-06-06 | 中国飞机强度研究所 | Fuselage wallboard static(al)/fatigue/damage tolerance test loading system |
| CN104697845A (en) * | 2013-12-06 | 2015-06-10 | 中国飞机强度研究所 | Static force/fatigue/damage tolerance test loading system of fuselage panel |
| CN104696513B (en) * | 2013-12-06 | 2017-10-31 | 中国飞机强度研究所 | A kind of fuselage wallboard encapsulating method |
| CN104007017A (en) * | 2014-05-23 | 2014-08-27 | 北京理工大学 | Metal pipe stretching device |
| CN104007017B (en) * | 2014-05-23 | 2016-02-17 | 北京理工大学 | A kind of metal pipe material stretching device |
| CN104807694A (en) * | 2015-05-04 | 2015-07-29 | 中国飞机强度研究所 | Fuselage panel combined load test device |
| CN104807694B (en) * | 2015-05-04 | 2018-01-30 | 中国飞机强度研究所 | A kind of fuselage wallboard combined load experimental rig |
| CN104807703A (en) * | 2015-05-12 | 2015-07-29 | 中国飞机强度研究所 | Airtight and compression loading test device of bent plate |
| CN105043899A (en) * | 2015-05-13 | 2015-11-11 | 中国飞机强度研究所 | Aircraft large-size panel shear loading apparatus |
| CN105043899B (en) * | 2015-05-13 | 2018-06-12 | 中国飞机强度研究所 | A kind of aircraft large size siding shears loading device |
| CN105067424A (en) * | 2015-08-31 | 2015-11-18 | 中国飞机强度研究所 | Fuselage panel test keel device and production method thereof |
| CN105067424B (en) * | 2015-08-31 | 2019-03-22 | 中国飞机强度研究所 | A kind of fuselage wallboard test keel device and its manufacturing method |
| CN105388002A (en) * | 2015-10-13 | 2016-03-09 | 中国飞机强度研究所 | Airplane body wallboard pressurizing test device |
| CN105388002B (en) * | 2015-10-13 | 2019-03-08 | 中国飞机强度研究所 | A kind of fuselage wallboard pressurising experimental rig |
| CN106168556A (en) * | 2016-06-21 | 2016-11-30 | 中国飞机强度研究所 | A kind of anti-unstability device for docking wall strength test |
| CN106168556B (en) * | 2016-06-21 | 2019-05-24 | 中国飞机强度研究所 | A kind of anti-unstability device tested for docking wall strength |
| 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 |
| CN109612836A (en) * | 2018-11-12 | 2019-04-12 | 南京航空航天大学 | A kind of vertical compression experimental rig suitable for bending big siding |
| CN109612836B (en) * | 2018-11-12 | 2021-09-17 | 南京航空航天大学 | Vertical compression test device suitable for big wallboard of buckling |
| CN110329539A (en) * | 2019-07-05 | 2019-10-15 | 中国飞机强度研究所 | Packaged type bogey in a kind of aircraft target ship compression-shear test platform |
| CN110823719A (en) * | 2019-11-19 | 2020-02-21 | 中国飞机强度研究所 | Device is applyed to fuselage load |
| CN110823719B (en) * | 2019-11-19 | 2022-06-07 | 中国飞机强度研究所 | Device is applyed to fuselage load |
| CN111409856A (en) * | 2020-04-17 | 2020-07-14 | 中国飞机强度研究所 | Engine body cabin section structural strength test constraint system |
| CN111537333A (en) * | 2020-06-22 | 2020-08-14 | 中国飞机强度研究所 | Bent plate comprehensive test device |
| CN111537333B (en) * | 2020-06-22 | 2020-10-09 | 中国飞机强度研究所 | Bent plate comprehensive test device |
| CN112052520A (en) * | 2020-09-02 | 2020-12-08 | 中国航空工业集团公司沈阳飞机设计研究所 | Composite loading method for curved plate |
| CN112857762A (en) * | 2020-12-29 | 2021-05-28 | 中国航空工业集团公司西安飞机设计研究所 | Transition section for semi-ellipsoid structural strength test |
| CN113155606A (en) * | 2021-03-30 | 2021-07-23 | 中国飞机强度研究所 | Mechanical property test device for body wallboard |
| 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 |
| CN114739619A (en) * | 2022-06-09 | 2022-07-12 | 中国飞机强度研究所 | Combined loading test system and loading test method for airplane pneumatic impact test |
| CN114739619B (en) * | 2022-06-09 | 2022-08-26 | 中国飞机强度研究所 | Combined loading test system and loading test method for airplane pneumatic impact test |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103149075B (en) | 2015-01-28 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103149075B (en) | Strength testing device and testing method for fuselage wall plate under action of combined loads | |
| CN104697845B (en) | Fuselage wallboard static(al)/fatigue/damage tolerance test loading system | |
| CN108238282B (en) | Central wing box test equipment | |
| CN106885745B (en) | Beam column node beam end loading test device and test method thereof | |
| DE102006015642B4 (en) | Testing device for hull shells | |
| CN104807694A (en) | Fuselage panel combined load test device | |
| CN102607940A (en) | Tensile-shear test loading device with flight structure | |
| CN109520860B (en) | Spar butt joint test piece design method | |
| CN109323941A (en) | Damper comprehensive test system | |
| CN202582980U (en) | Tension-shear test loading device for flight structure | |
| CN105181442B (en) | Shaping air bag and the experimental rig and method for applying evenly load to plate using it | |
| CN204282544U (en) | A kind of joint reinforcing and energy consuming mechanism | |
| RU2653774C1 (en) | Device for testing panels | |
| CN110254748A (en) | A kind of connector-wall panel structure static pressure experimental rig | |
| CN208163977U (en) | Deformed bar automatic Tensioning system | |
| CN102980812B (en) | A kind of reusable by the creep device transferring compression to that stretches | |
| CN105729621A (en) | Concrete member prefabrication component | |
| CN104990754A (en) | Simple-supported cast-in-place girder static load testing device | |
| EP1930506B1 (en) | Load-testing element | |
| CN103624130A (en) | Device with double-direction buffering and resetting functions | |
| CN108914998B (en) | Reinforced soil retaining wall damage mechanism experimental device and working method | |
| RU196657U1 (en) | Aircraft wing panel | |
| CN205581969U (en) | Prefabricated device that can be used to complicated girder construction | |
| CN213516588U (en) | Loading device for airplane stabilizer control load test | |
| CN205572668U (en) | Girder construction prefabricating formwork mounting fixture |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |