CN109436374A - Canopy installation method in a kind of test of aircraft fatigue - Google Patents
Canopy installation method in a kind of test of aircraft fatigue Download PDFInfo
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- CN109436374A CN109436374A CN201811450207.3A CN201811450207A CN109436374A CN 109436374 A CN109436374 A CN 109436374A CN 201811450207 A CN201811450207 A CN 201811450207A CN 109436374 A CN109436374 A CN 109436374A
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- predetermined time
- test
- load
- canopy
- installation method
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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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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Testing Resistance To Weather, Investigating Materials By Mechanical Methods (AREA)
- Adhesives Or Adhesive Processes (AREA)
Abstract
This application provides canopy installation methods in a kind of test of aircraft fatigue.Canopy installation method includes the following steps: step 1 in the aircraft fatigue test: production complexing agent；Step 2: complexing agent being pasted on testing stand outer arc, canopy is installed to formal test state position；Step 3: with first load extrusion cladding the second predetermined time of agent；Step 4: testing stand component is stood into the third predetermined time；Step 5: with second load extrusion cladding the second predetermined time of agent；Step 6: the testing stand component was stood into for the 4th predetermined time；Step 7: using the second predetermined time of third load extrusion cladding agent；Step 8: the testing stand component was stood into for the 5th predetermined time；Step 9: with the 6th predetermined time of the 4th load extrusion cladding agent.Canopy installation method solves the problems, such as installation period length, poor sealing, damage test part in the aircraft fatigue test of the application, and leakproofness is good.
Description
Technical field
The application belongs to aircraft fatigue experimental technique field, in particular to canopy installation side in a kind of aircraft fatigue test
Method.
Background technique
Canopy and windscreen are most important to the safety in utilization of aircraft as Transparent Parts unique on aircraft, especially right
The life support of pilot plays a significant role.Various model aircraft windscreens, canopy must complete fatigue life test, for knot
Structure design and intensive analysis and fatigue life provide test basis.
The fatigue test of canopy and windscreen is carried out on the special fatigue test platform of various models, and testing stand is list
Only non-standard de-sign, windscreen testpieces are fixed on testing stand during the test, and canopy testpieces be can be from examination
It tests on platform and disassembles, to facilitate check at any time.This just increases difficulty to the installation of testpieces, and canopy is mounted on dedicated
After on testing stand, need to canopy inside carry out punching press, this requires four sides of canopy docked with testing stand well, due to
The front and back of canopy are plane, the relatively good processing of leakproofness after docking, and two sides of canopy are hyperboloid,
And canopy needs to carry out the movement of minimum 150mm on testing stand when installation and removal.For the gas for guaranteeing entire testpieces
Close property, the bi-curved abutting joint size on hyperboloid and testpieces on testing stand will be accurate within 1.5mm.Previous
Installation method is to be applied to using epoxide-resin glue (two-in-one) Method for Installation, epoxide-resin glue and curing agent and afterwards testing stand two
In the cambered surface (hyperboloid) of side, when reaching certain degree of hardness after adhesive curing.Pass through push-and-pull canopy check test part and side arc
Gap error, then correction of the flank shape is carried out with milling tools, process needs to wait the solidification of glue, and needs that processing is polished for a plurality of times, and installs
The gap of latter two curved surface is not easy observation and measurement, and installation period is long, generally requires or so three, four week, poor sealing.
And it is easy to cause unnecessary damage to the airtight trough of belt, airtight band and other structural members of testpieces in multiple installation process
Wound.
Thus, it is desirable to have a kind of technical solution overcomes or at least mitigates at least one drawbacks described above of the prior art.
Summary of the invention
There is provided canopy installation method stations in a kind of test of aircraft fatigue for the purpose of the application, to solve existing aircraft
At least one problem existing for canopy installation method in fatigue test.
The technical solution of the application is:
Canopy installation method in a kind of test of aircraft fatigue, canopy installation method includes in the aircraft fatigue test
Following steps:
Step 1: production complexing agent, the complexing agent includes epoxide-resin glue, curing agent and cement；
Step 2: within the first predetermined time, complexing agent being pasted on testing stand outer arc, canopy is installed to formally
Trystate position, to form testing stand component；
Step 3: after reaching for the first predetermined time, with first load extrusion cladding the second predetermined time of agent；
Step 4: after step 3, the testing stand component being stood into the third predetermined time；
Step 5: after the step 4, with second load extrusion cladding the second predetermined time of agent；
Step 6: after the step 5, the testing stand component being stood into for the 4th predetermined time；
Step 7: after the step 6, with third load extrusion cladding the second predetermined time of agent；
Step 8: after step 7, the testing stand component being stood into for the 5th predetermined time；
Step 9: after step 8, with the 6th predetermined time of the 4th load extrusion cladding agent.
Optionally, the epoxide-resin glue, curing agent and cement proportion are 1:10:100.
Optionally, the epoxide-resin glue, curing agent and cement proportion are 1:15:300.
Optionally, first predetermined time is 30 minutes.
Optionally, the load of airtight 10% with crest when first load is test；
Second predetermined time is 2 seconds.
Optionally, the third predetermined time is 60 minutes.
Optionally, the load of airtight 20% with crest when second load is test.
Optionally, the 4th predetermined time is 90 minutes；
The load of the third load airtight 30% with crest when being test.
Optionally, the 5th predetermined time is 180 minutes.
Optionally, the load of airtight 50% with crest when the 4th load is test；Described 6th pre- timing
Between be 5 seconds.
At least there are following advantageous effects in the application:
Canopy installation method solves installation period length, poor sealing, damage in the aircraft fatigue test of the application
The problem of testpieces, leakproofness are good.
Detailed description of the invention
Fig. 1 is the flow diagram of canopy installation method during the aircraft fatigue in one embodiment of the application is tested.
Fig. 2 is the structural schematic diagram of the testing stand component in one embodiment of the application.
Appended drawing reference
The airtight band of 1--.
Specific embodiment
To keep the purposes, technical schemes and advantages of the application implementation clearer, below in conjunction in the embodiment of the present application
Attached drawing, technical solutions in the embodiments of the present application is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label indicate same or similar element or element with the same or similar functions.Described embodiment is the application
A part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
In explanation the application, and it should not be understood as the limitation to the application.Based on the embodiment in the application, ordinary skill people
Member's every other embodiment obtained without creative efforts, shall fall in the protection scope of this application.Under
Face is described in detail embodiments herein in conjunction with attached drawing.
In the description of the present application, it is to be understood that term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown is merely for convenience of description the application and simplifies description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as protecting the application
The limitation of range.
It is described in further details below with reference to aircraft of each attached drawing to the application.
Fig. 1 is the flow diagram of canopy installation method during the aircraft fatigue in one embodiment of the application is tested.Fig. 2 is
The structural schematic diagram of testing stand component in one embodiment of the application.
Canopy installation method includes the following steps: in aircraft fatigue test as shown in Figures 1 and 2
Step 1: production complexing agent, the complexing agent includes epoxide-resin glue, curing agent and cement；
Step 2: within the first predetermined time, complexing agent being pasted on testing stand outer arc, canopy is installed to formally
Trystate position, to form testing stand component；
Step 3: after reaching for the first predetermined time, with first load extrusion cladding the second predetermined time of agent；
Step 4: after step 3, the testing stand component being stood into the third predetermined time；
Step 5: after the step 4, with second load extrusion cladding the second predetermined time of agent；
Step 6: after the step 5, the testing stand component being stood into for the 4th predetermined time；
Step 7: after the step 6, with third load extrusion cladding the second predetermined time of agent；
Step 8: after step 7, the testing stand component being stood into for the 5th predetermined time；
Step 9: after step 8, with the 6th predetermined time of the 4th load extrusion cladding agent.
Canopy installation method solves installation period length, poor sealing, damage in the aircraft fatigue test of the application
The problem of testpieces, leakproofness are good.
In the present embodiment, the epoxide-resin glue, curing agent and cement proportion are 1:10:100.
In another embodiment, the epoxide-resin glue, curing agent and cement proportion are 1:15:300.
In the present embodiment, the first predetermined time was 30 minutes.It is understood that the first predetermined time can also be 25
To between 40 minutes.
In the present embodiment, the load of airtight 10% with crest when the first load is test；Second predetermined time
It is 2 seconds.
In the present embodiment, the third predetermined time is 60 minutes.
In the present embodiment, the load of airtight 20% with crest when the second load is test.
In the present embodiment, the 4th predetermined time was 90 minutes；Third load is airtight with crest when being test
30% load.
In the present embodiment, the 5th predetermined time was 180 minutes.
In the present embodiment, the load of airtight 50% with crest when the 4th load is test；6th predetermined time
It is 5 seconds.
The above, the only specific embodiment of the application, but the protection scope of the application is not limited thereto, it is any
Within the technical scope of the present application, any changes or substitutions that can be easily thought of by those familiar with the art, all answers
Cover within the scope of protection of this application.Therefore, the protection scope of the application should be with the scope of protection of the claims
It is quasi-.
Claims (10)
1. canopy installation method in a kind of aircraft fatigue test, which is characterized in that canopy peace in the aircraft fatigue test
Dress method includes the following steps:
Step 1: production complexing agent, the complexing agent includes epoxide-resin glue, curing agent and cement；
Step 2: within the first predetermined time, complexing agent being pasted on testing stand outer arc, canopy is installed to formal test
State position, to form testing stand component；
Step 3: after reaching for the first predetermined time, with first load extrusion cladding the second predetermined time of agent；
Step 4: after step 3, the testing stand component being stood into the third predetermined time；
Step 5: after the step 4, with second load extrusion cladding the second predetermined time of agent；
Step 6: after the step 5, the testing stand component being stood into for the 4th predetermined time；
Step 7: after the step 6, with third load extrusion cladding the second predetermined time of agent；
Step 8: after step 7, the testing stand component being stood into for the 5th predetermined time；
Step 9: after step 8, with the 6th predetermined time of the 4th load extrusion cladding agent.
2. canopy installation method in aircraft fatigue test according to claim 1, which is characterized in that the epoxy resin
Glue, curing agent and cement proportion are 1:10:100.
3. canopy installation method in aircraft fatigue test according to claim 1, which is characterized in that the epoxy resin
Glue, curing agent and cement proportion are 1:15:300.
4. canopy installation method in aircraft fatigue test as described in claim 1, which is characterized in that the described first pre- timing
Between be 30 minutes.
5. canopy installation method in aircraft fatigue as described in claim 1 test, which is characterized in that first load is
The load of airtight 10% with crest when test；
Second predetermined time is 2 seconds.
6. canopy installation method in aircraft fatigue test as described in claim 1, which is characterized in that the pre- timing of third
Between be 60 minutes.
7. canopy installation method in aircraft fatigue as described in claim 1 test, which is characterized in that second load is
The load of airtight 20% with crest when test.
8. canopy installation method in aircraft fatigue test as described in claim 1, which is characterized in that the described 4th pre- timing
Between be 90 minutes；
The load of the third load airtight 30% with crest when being test.
9. canopy installation method in aircraft fatigue test as claimed in claim 8, which is characterized in that the described 5th pre- timing
Between be 180 minutes.
10. canopy installation method in aircraft fatigue test as described in claim 1, which is characterized in that the 4th load
The load of airtight 50% with crest when to test；
6th predetermined time is 5 seconds.
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 |
Applications Claiming Priority (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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109436374A true CN109436374A (en) | 2019-03-08 |
| CN109436374B CN109436374B (en) | 2022-04-01 |
Family
ID=65555420
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| 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 (7)
| 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 |
| US20070227434A1 (en) * | 2006-03-29 | 2007-10-04 | Matthias Gotze | Testing Device for Hull Shells |
| 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 |
-
2018
- 2018-11-30 CN CN201811450207.3A patent/CN109436374B/en active Active
Patent Citations (7)
| 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 |
| US20070227434A1 (en) * | 2006-03-29 | 2007-10-04 | Matthias Gotze | Testing Device for Hull Shells |
| 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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| Publication number | Publication date |
|---|---|
| CN109436374B (en) | 2022-04-01 |
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