CN109436374B - Installation method of cockpit cover in airplane fatigue test - Google Patents
Installation method of cockpit cover in airplane fatigue test Download PDFInfo
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- CN109436374B CN109436374B CN201811450207.3A CN201811450207A CN109436374B CN 109436374 B CN109436374 B CN 109436374B CN 201811450207 A CN201811450207 A CN 201811450207A CN 109436374 B CN109436374 B CN 109436374B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- Testing Resistance To Weather, Investigating Materials By Mechanical Methods (AREA)
Abstract
The application provides a method for installing a cockpit cover in an airplane fatigue test. The installation method of the cockpit cover in the airplane fatigue test comprises the following steps: step 1: preparing a complexing agent; step 2: pasting the complexing agent on the outer arc of the test bed, and installing the canopy on the position of a formal test state; and step 3: extruding the compound with the first load for a second predetermined time; and 4, step 4: standing the test bed component for a third preset time; and 5: extruding the compound with a second load for a second predetermined time; step 6: standing the test bed component for a fourth preset time; and 7: extruding the compound with a third load for a second predetermined time; and 8: standing the test bed component for a fifth preset time; and step 9: the compound is extruded with a fourth load for a sixth predetermined time. The installation method of the cockpit cover in the airplane fatigue test solves the problems that the installation period is long, the sealing performance is poor, and a test piece is damaged, and the sealing performance is good.
Description
Technical Field
The application belongs to the technical field of airplane fatigue tests, and particularly relates to a method for installing a cockpit cover in an airplane fatigue test.
Background
The cockpit cover and the windshield are used as the only transparent parts on the airplane, are very important to the use safety of the airplane, and particularly play an important role in the life guarantee of pilots. The fatigue life test of various types of airplane windshields and canopy is required to be completed, and test basis is provided for structural design, strength analysis and fatigue life.
The fatigue tests of the canopy and the windshield are carried out on special fatigue test stands of various models, the test stands are all independent non-standard designs, the windshield test piece is fixed on the test stand in the test process, and the canopy test piece can be detached from the test stand so as to be convenient to check at any time. The difficulty is increased for the installation of a test piece, the inside of the canopy needs to be punched after the canopy is installed on a special test bed, the four sides of the canopy are required to be well butted with the test bed, the front side and the rear side of the canopy are both flat surfaces, the tightness after butt joint is better treated, the two side surfaces of the canopy are both double curved surfaces, and the canopy needs to move on the test bed by at least 150mm during installation and disassembly. In order to ensure the air tightness of the whole test piece, the butt joint installation size of the hyperboloid on the test bed and the hyperboloid on the test piece is accurate to be within 1.5 mm. The traditional mounting method adopts an epoxy resin adhesive (two-in-one) mounting method, the epoxy resin adhesive and a curing agent are uniformly coated on the cambered surfaces (hyperboloids) at two sides of the test bed, and when the adhesive reaches a certain hardness after being cured. The test piece and the clearance error of side arc are inspected through the push-and-pull canopy, and then the shape is repaired by using a polishing tool, the process needs to wait for the solidification of glue, and the polishing treatment needs to be carried out for many times, the clearance between two curved surfaces after installation is difficult to observe and measure, the installation period is long, the sealing performance is poor due to the fact that the clearance is generally required to be about three or four weeks. And the airtight belt groove, the airtight belt and other structural components of the test piece are easily damaged unnecessarily in multiple installation processes.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
The application aims to provide a method and a station for installing the canopy in the airplane fatigue test, so as to solve at least one problem of the existing method for installing the canopy in the airplane fatigue test.
The technical scheme of the application is as follows:
a method for installing an aircraft canopy in an aircraft fatigue test comprises the following steps:
step 1: preparing a complexing agent, wherein the complexing agent comprises epoxy resin glue, a curing agent and cement;
step 2: within first preset time, pasting the complexing agent on the outer arc of the test bed, and installing the canopy on a formal test state position to form a test bed assembly;
and step 3: after the first preset time is reached, extruding the complexing agent by using the first load for a second preset time;
and 4, step 4: after step 3, standing the test bed assembly for a third predetermined time;
and 5: extruding the compound with a second load for a second predetermined time after said step 4;
step 6: after the step 5, standing the test bed assembly for a fourth preset time;
and 7: extruding the compound with a third load for a second predetermined time after said step 6;
and 8: after step 7, standing the test bed assembly for a fifth predetermined time;
and step 9: after step 8, the compound is extruded with a fourth load for a sixth predetermined time.
Optionally, the ratio of the epoxy resin glue, the curing agent and the cement is 1: 10: 100.
optionally, the ratio of the epoxy resin glue, the curing agent and the cement is 1: 15: 300.
optionally, the first predetermined time is 30 minutes.
Optionally, the first load is a load that is 10% of the highest load of the airtight band at the time of the test;
the second predetermined time is 2 seconds.
Optionally, the third predetermined time is 60 minutes.
Optionally, the second load is a load that is 20% of the highest load of the airtight band at the time of the test.
Optionally, the fourth predetermined time is 90 minutes;
the third load was 30% of the highest load in the airtight zone at the time of the test.
Optionally, the fifth predetermined time is 180 minutes.
Optionally, the fourth load is a load that is 50% of the highest load of the airtight band at the time of the test; the sixth predetermined time is 5 seconds.
The application has at least the following beneficial technical effects:
the installation method of the cockpit cover in the airplane fatigue test solves the problems that the installation period is long, the sealing performance is poor, and a test piece is damaged, and the sealing performance is good.
Drawings
Fig. 1 is a schematic flow chart of a method for installing a canopy in an aircraft fatigue test according to an embodiment of the present application.
FIG. 2 is a schematic structural diagram of a test stand assembly according to an embodiment of the present application.
Reference numerals
1- -airtight belt.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The aircraft of the present application is described in further detail below with reference to the various figures.
Fig. 1 is a schematic flow chart of a method for installing a canopy in an aircraft fatigue test according to an embodiment of the present application. FIG. 2 is a schematic structural diagram of a test stand assembly according to an embodiment of the present application.
The installation method of the cockpit cover in the airplane fatigue test shown in fig. 1 and 2 comprises the following steps:
step 1: preparing a complexing agent, wherein the complexing agent comprises epoxy resin glue, a curing agent and cement;
step 2: within first preset time, pasting the complexing agent on the outer arc of the test bed, and installing the canopy on a formal test state position to form a test bed assembly;
and step 3: after the first preset time is reached, extruding the complexing agent by using the first load for a second preset time;
and 4, step 4: after step 3, standing the test bed assembly for a third predetermined time;
and 5: extruding the compound with a second load for a second predetermined time after said step 4;
step 6: after the step 5, standing the test bed assembly for a fourth preset time;
and 7: extruding the compound with a third load for a second predetermined time after said step 6;
and 8: after step 7, standing the test bed assembly for a fifth predetermined time;
and step 9: after step 8, the compound is extruded with a fourth load for a sixth predetermined time.
The installation method of the cockpit cover in the airplane fatigue test solves the problems that the installation period is long, the sealing performance is poor, and a test piece is damaged, and the sealing performance is good.
In this embodiment, the ratio of the epoxy resin adhesive, the curing agent and the cement is 1: 10: 100.
in another embodiment, the epoxy glue, curing agent and cement are in a ratio of 1: 15: 300.
in the present embodiment, the first predetermined time is 30 minutes. It will be appreciated that the first predetermined time may also be between 25 and 40 minutes.
In this example, the first load was a load of 10% of the highest load of the airtight band at the time of the test; the second predetermined time is 2 seconds.
In this embodiment, the third predetermined time is 60 minutes.
In this example, the second load was a load of 20% of the highest load of the airtight band at the time of the test.
In the present embodiment, the fourth predetermined time is 90 minutes; the third load was 30% of the highest load in the airtight band at the time of the test.
In the present embodiment, the fifth predetermined time is 180 minutes.
In this example, the fourth load was a load of 50% of the highest load of the airtight band at the time of the test; the sixth predetermined time is 5 seconds.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (3)
1. A method for installing an aircraft canopy in an aircraft fatigue test is characterized by comprising the following steps:
step 1: preparing a complexing agent, wherein the complexing agent comprises epoxy resin glue, a curing agent and cement;
step 2: adhering the complexing agent to the outer arc of the test bed within first preset time, and installing the canopy to a formal test state position to form a test bed assembly, wherein the first preset time is 30 minutes;
and step 3: after reaching the first preset time, extruding the complexing agent by using a first load for a second preset time, wherein the first load is 10% of the highest load of the airtight belt in the test, and the second preset time is 2 seconds;
and 4, step 4: after step 3, standing the test bed assembly for a third predetermined time, wherein the third predetermined time is 60 minutes;
and 5: after said step 4, compressing the compound with a second load for a second predetermined time, said second load being a load that is 20% of the highest load of the airtight band at the time of the test;
step 6: after the step 5, standing the test bed assembly for a fourth preset time, wherein the fourth preset time is 90 minutes;
and 7: extruding the composition with a third load for a second predetermined time after said step 6, said third load being a load of 30% of the highest load of the airtight band at the time of the test;
and 8: after step 7, standing the test bed assembly for a fifth predetermined time, wherein the fifth predetermined time is 180 minutes;
and step 9: after step 8, the compound is extruded with a fourth load of 50% of the highest load of the airtight belt at the time of the test for a sixth predetermined time of 5 seconds.
2. The method for installing the cockpit cover in the airplane fatigue test according to claim 1, wherein the ratio of the epoxy resin glue, the curing agent and the cement is 1: 10: 100.
3. the method for installing the cockpit cover in the airplane fatigue test according to claim 1, wherein the ratio of the epoxy resin glue, the curing agent and the cement is 1: 15: 300.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811450207.3A CN109436374B (en) | 2018-11-30 | 2018-11-30 | Installation method of cockpit cover in airplane fatigue test |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811450207.3A CN109436374B (en) | 2018-11-30 | 2018-11-30 | Installation method of cockpit cover in airplane fatigue test |
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| Publication Number | Publication Date |
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| CN109436374A CN109436374A (en) | 2019-03-08 |
| CN109436374B true CN109436374B (en) | 2022-04-01 |
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| CN201811450207.3A Active CN109436374B (en) | 2018-11-30 | 2018-11-30 | Installation method of cockpit cover in airplane fatigue test |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH10157016A (en) * | 1996-12-02 | 1998-06-16 | Yokohama Rubber Co Ltd:The | Under water rubber structure |
| CN2764856Y (en) * | 2004-11-11 | 2006-03-15 | 李天伶 | Decorative floor capable of seamless mounting |
| CN101384478A (en) * | 2006-02-17 | 2009-03-11 | 空中客车德国有限公司 | Method for autoclave-free adhesive bonding of components for aircraft |
| WO2015102911A1 (en) * | 2013-12-30 | 2015-07-09 | Dow Global Technologies Llc | Toughening agents for epoxy systems |
| CN105398582A (en) * | 2015-11-13 | 2016-03-16 | 中国人民解放军国防科学技术大学 | Skin, bulkhead integrated unmanned aerial vehicle body and manufacturing method of bulkhead integrated unmanned aerial vehicle body |
| CN106501096A (en) * | 2016-10-21 | 2017-03-15 | 山西省交通科学研究院 | A kind of ground surface material bilayer cuboid test specimen compression staight scissors fatigue experimental device |
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 |
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2018
- 2018-11-30 CN CN201811450207.3A patent/CN109436374B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH10157016A (en) * | 1996-12-02 | 1998-06-16 | Yokohama Rubber Co Ltd:The | Under water rubber structure |
| CN2764856Y (en) * | 2004-11-11 | 2006-03-15 | 李天伶 | Decorative floor capable of seamless mounting |
| CN101384478A (en) * | 2006-02-17 | 2009-03-11 | 空中客车德国有限公司 | Method for autoclave-free adhesive bonding of components for aircraft |
| WO2015102911A1 (en) * | 2013-12-30 | 2015-07-09 | Dow Global Technologies Llc | Toughening agents for epoxy systems |
| CN105398582A (en) * | 2015-11-13 | 2016-03-16 | 中国人民解放军国防科学技术大学 | Skin, bulkhead integrated unmanned aerial vehicle body and manufacturing method of bulkhead integrated unmanned aerial vehicle body |
| CN106501096A (en) * | 2016-10-21 | 2017-03-15 | 山西省交通科学研究院 | A kind of ground surface material bilayer cuboid test specimen compression staight scissors fatigue experimental device |
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| CN109436374A (en) | 2019-03-08 |
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