CN104139869A - Bidirectional-transmitting load loading device - Google Patents
Bidirectional-transmitting load loading device Download PDFInfo
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- CN104139869A CN104139869A CN201310170197.9A CN201310170197A CN104139869A CN 104139869 A CN104139869 A CN 104139869A CN 201310170197 A CN201310170197 A CN 201310170197A CN 104139869 A CN104139869 A CN 104139869A
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- loading
- aluminium sheet
- load
- bidirectional
- rubber block
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Abstract
The invention belongs to the load loading and transmitting technology and relates to a bidirectional-transmitting load loading device which is used for applying load in static tests and fatigue tests of an aircraft structure. The bidirectional-transmitting load loading device is spliced by a rubber plate and an aluminum plate, wherein the surface of the rubber plate is identical to that of a to-be-spliced aircraft, and at least one screw hole used for loading is formed in the aluminum plate. The bottoms of the screw holes do not penetrate through the aluminum plate. When loading nodes are distributed regularly, four loading screw holes in symmetrical distribution are formed in the aluminum plate for loading. When the loading nodes are distributed irregularly, one loading screw hole is formed in the center of the aluminum plate for lading. The bidirectional-transmitting load loading device solves the problem that an existing transmitting device cannot transmit load in double directions and has the advantages that when the bidirectional-transmitting load loading device is connected with one set of loading equipment, bidirectional transmitting of the load can be realized, utilization amount and reloading amount of the loading equipment are reduced, a test preparation period is shortened, and the bidirectional-transmitting load loading device can be utilized widely.
Description
Technical field
The invention belongs to load and load Transfer Technology, relate to a kind of bi-directional load charger applying for aircaft configuration static(al), fatigue test load.
Background technology
In aircaft configuration static(al), fatigue test, be subject to the impact of the reasons such as space, time, need to use a set of loading system to apply tension compression bidirectional load.Yet in aircaft configuration strength test in the past, all adopt the device of unidirectional delivery load, can not transmit tension compression bidirectional load, need larger loading space and more loading facilities.And also extended the preparatory period of test when these equipment are installed, promoted experimentation cost.
In order to reduce test required loading space and loading facilities, shorten the test preparatory period, need a kind of device that can transmit bidirectional load.
Summary of the invention
The object of the invention is: provide a kind of can accurate transfer bidirectional load, and effectively reduce test and load space and loading facilities, shorten the bi-directional load charger of test preparatory period.
Technical scheme of the present invention is:
Bi-directional load charger, it is by rubber block and aluminium sheet is bonding forms, wherein, rubber block surface with treat that bonding aircraft surfaces is consistent, on aluminium sheet, offer at least one tapped bore for loading.
Aluminium sheet is not run through in tapped bore bottom.
When loading node rule distribution, on aluminium sheet, offer four symmetrical loading tapped bore and load.
When loading the irregular distribution of node, aluminium sheet central authorities offer single loading tapped bore and load.
Rubber block edge carries out processing for reducing the rounding of concentrated stress, raising bind strength.
Before rubber block and aluminium sheet are bonding, rubber block two sides all needs skew intersection grinding process.
When rubber block and aluminium sheet are bonding, baking time is at 24 to 72 hours, and between 25 degrees Celsius to 50 degrees Celsius of temperature, humidity is not more than 70%.
The described glue for adhesive rubber piece and aluminium sheet is the Instant cement that anti-profit soaks.
Technique effect of the present invention is:
The invention solves the problem that transfer device in the past cannot transmit bidirectional load, after its good effect is that a set of loading facilities is attached thereto, can bi-directional load, reduced use amount and the amount of changing the outfit of loading facilities, shortened the test preparatory period, and can be widely used.
Accompanying drawing explanation
Fig. 1 is the structural representation of bi-directional load charger of the present invention;
Fig. 2 is the structural representation of rubber block;
Fig. 3 is the structural representation of aluminium block-1;
Fig. 4 is the structural representation of aluminium block-2,
Wherein: 1-aluminium sheet, 2-lining cement, 3-rubber block, 4-tapped bore.
The specific embodiment
Bi-directional load charger rubber block and aluminium sheet two parts, the bonding formation tension and compression of rubber and aluminium sheet pad, concrete structure is shown in accompanying drawing 1.By the control to rubber block shape, make tension and compression pad meet bonding to difformity aircraft surfaces.By the adjustment to connecting bore on aluminium sheet, make bi-directional load charger can meet the demand loading under different loads node distribution shape.By the selection of lining cement between aluminium sheet and rubber block, make bi-directional load charger can transmit larger Tensile or Compressive Loading, and can resist the immersion corrosion of water, oil, meet test requirements document.
Rubber block adopts mould directly to vulcanize production, as shown in Figure 2, by edge rounding, designs, and falls stress concentration, improves bind strength.Meanwhile, control mold bottom shape, make rubber block be satisfied with the bonding requirement of same shape aircraft surfaces.
Aluminium sheet adopts machine up to form, and according to loading node distribution, requires the multi-form loading tapped bore of design, and concrete structure as shown in Figure 3, Figure 4, has provided respectively the situation of different loading tapped bore designs.Aluminium sheet is converted into uniform load by the concentrated load loading on tapped bore, and is delivered on rubber block.
Lining cement is selected the Instant cement of water resistant, oil immersion bubble, bonding aluminium sheet and rubber block, and transmitted load.
Can adjust rubber block and aluminium sheet size according to loading demand and planform, meet different surfaces, different loads size, the demand that different loads distributes.
The core content of the invention is by selecting suitable material, carries out forming tensile strength test under varying environment, has formed a kind of suitable apparatus structure form, and supporting operating instruction with it, guarantees its structural strength.In theory, this device can transmit wing, the load of canard, fuselage all sites.
Claims (8)
1. bi-directional load charger, is characterized in that: by rubber block with aluminium sheet is bonding forms, wherein, rubber block surface with treat that bonding aircraft surfaces is consistent, on aluminium sheet, offer at least one tapped bore for loading.
2. according to the bi-directional load charger utilizing described in claim 1, it is characterized in that: aluminium sheet is not run through in tapped bore bottom.
3. according to the bi-directional load charger utilizing described in claim 2, it is characterized in that: when loading node rule and distribute, on aluminium sheet, offer four symmetrical loading tapped bore and load.
4. according to the bi-directional load charger utilizing described in claim 3, it is characterized in that: when loading the irregular distribution of node, aluminium sheet central authorities offer single loading tapped bore and load.
5. according to the bi-directional load charger utilizing described in claim 4, it is characterized in that: rubber block edge carries out processing for reducing concentrated stress, the rounding that improves bind strength.
6. according to the bi-directional load charger utilizing described in claim 1 to 5 any one, it is characterized in that: before rubber block and aluminium sheet are bonding, rubber block two sides all needs skew intersection grinding process.
7. according to the bi-directional load charger utilizing described in claim 6, it is characterized in that: when rubber block and aluminium sheet are bonding, baking time is at 24 to 72 hours, between 25 degrees Celsius to 50 degrees Celsius of temperature, humidity is not more than 70%.
8. according to the bi-directional load charger utilizing described in claim 7, it is characterized in that: the described glue for adhesive rubber piece and aluminium sheet is the Instant cement that anti-profit soaks.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310170197.9A CN104139869A (en) | 2013-05-10 | 2013-05-10 | Bidirectional-transmitting load loading device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310170197.9A CN104139869A (en) | 2013-05-10 | 2013-05-10 | Bidirectional-transmitting load loading device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104139869A true CN104139869A (en) | 2014-11-12 |
Family
ID=51849233
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310170197.9A Pending CN104139869A (en) | 2013-05-10 | 2013-05-10 | Bidirectional-transmitting load loading device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104139869A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112798426A (en) * | 2020-12-24 | 2021-05-14 | 中国飞行试验研究院 | Airplane wing surface tension and compression bidirectional loading device and using method thereof |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2719985Y (en) * | 2004-06-10 | 2005-08-24 | 方大集团股份有限公司 | Mirror-face aluminium-plastic composite board |
| CN101139860A (en) * | 2007-09-25 | 2008-03-12 | 朱金龙 | Metal composite plate with hollow mesh core layer and manufacturing method thereof |
| CN201633676U (en) * | 2009-12-31 | 2010-11-17 | 厦门理工学院 | Formula car collision energy absorbing device |
| CN102469685A (en) * | 2010-11-19 | 2012-05-23 | 昆山雅森电子材料科技有限公司 | Heat-conducting double-faced soft and hard combined base plate and manufacturing method thereof |
| CN202593849U (en) * | 2012-02-06 | 2012-12-12 | 丁慧 | Composite damping sticky plate adhered to inner wall of cabin of military aircraft |
| CN102873884A (en) * | 2012-09-13 | 2013-01-16 | 沈阳飞机工业（集团）有限公司 | Composite material combined core mold compensation pad process |
-
2013
- 2013-05-10 CN CN201310170197.9A patent/CN104139869A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2719985Y (en) * | 2004-06-10 | 2005-08-24 | 方大集团股份有限公司 | Mirror-face aluminium-plastic composite board |
| CN101139860A (en) * | 2007-09-25 | 2008-03-12 | 朱金龙 | Metal composite plate with hollow mesh core layer and manufacturing method thereof |
| CN201633676U (en) * | 2009-12-31 | 2010-11-17 | 厦门理工学院 | Formula car collision energy absorbing device |
| CN102469685A (en) * | 2010-11-19 | 2012-05-23 | 昆山雅森电子材料科技有限公司 | Heat-conducting double-faced soft and hard combined base plate and manufacturing method thereof |
| CN202593849U (en) * | 2012-02-06 | 2012-12-12 | 丁慧 | Composite damping sticky plate adhered to inner wall of cabin of military aircraft |
| CN102873884A (en) * | 2012-09-13 | 2013-01-16 | 沈阳飞机工业（集团）有限公司 | Composite material combined core mold compensation pad process |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112798426A (en) * | 2020-12-24 | 2021-05-14 | 中国飞行试验研究院 | Airplane wing surface tension and compression bidirectional loading device and using method thereof |
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| C10 | Entry into substantive examination | ||
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| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20141112 |
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| RJ01 | Rejection of invention patent application after publication |