CN108163226A - A kind of aircraft nose landing gear outer barrel strut connector launch fatigue test method - Google Patents
A kind of aircraft nose landing gear outer barrel strut connector launch fatigue test method Download PDFInfo
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- CN108163226A CN108163226A CN201711229914.5A CN201711229914A CN108163226A CN 108163226 A CN108163226 A CN 108163226A CN 201711229914 A CN201711229914 A CN 201711229914A CN 108163226 A CN108163226 A CN 108163226A
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- fatigue test
- outer barrel
- fatigue
- strut connector
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Classifications
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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)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The present invention provides a kind of aircraft nose landing gear outer barrel strut connector launch fatigue test method, and step is as follows：Test of static strength is carried out to outer barrel strut connector test exemplar；Fatigue test is carried out, wherein X, Y, Z-direction load coordinate loading, uses stress ratio as 0.06 sine wave CYCLIC LOADING mode, loading frequency 2Hz；Fatigue test is divided into two stages progress：First stage：Load loaded cycle number 7500 times, is once visually inspected for every 500 times, if there is fatigue rupture phenomenon, stops experiment, otherwise recording parameters carry out testpieces entering second stage after flaw detection is qualified；Second stage：Load loaded cycle number 7500~15000 times, is once visually inspected for every 500 times, if there is fatigue rupture phenomenon, stops experiment, otherwise recording parameters continue experiment until terminating, record cycle-index.Fatigue test method provided by the present invention by testing experiment part, verifies fatigue behaviour and the service life of partial structurtes, reduces development cost in advance.
Description
Technical field
The invention belongs to field of airplane structure, more particularly to aircraft structure test field, and in particular to a kind of aircraft
Nose-gear outer barrel strut connector launch fatigue test method.
Background technology
It is preceding to rise and fall to ensure bearing capacity and the life requirements of the aircraft nose landing gear for marine environment launch
The structure type and bearing capacity of frame are significantly strengthened, and nose-gear is subjected to larger hauled load, and vertical load is about common to fly
The 2 times or more of machine, and undercarriage strut connector is subjected to whole hauled loads.As a kind of undercarriage of brand-new design, if directly
Connect and fatigue test carried out using full-scale undercarriage, there are testpieces manufacturing cycle is long, the Test-bed Design manufacturing cycle is long,
The shortcomings of test period is long, development cost is high, experiment obstructed continuous change period later are longer.
Invention content
The purpose of the present invention is to provide a kind of aircraft nose landing gear outer barrel strut connector launch fatigue test method,
Overcome or alleviated by least one drawbacks described above of the prior art.
The purpose of the present invention is achieved through the following technical solutions：A kind of aircraft nose landing gear outer barrel strut connector launch
Fatigue test method includes the following steps,
Step 1：According to nose-gear outer tube structure, the tests exemplar of outer barrel strut connector thereon is made；
Step 2：By outer barrel strut connector test exemplar clamping on fixture, test of static strength is carried out；
Step 3：Fatigue test is carried out, wherein X, Y, Z-direction load coordinate loading, and use sine wave CYCLIC LOADING；
3.1：Fatigue test first stage, cycle carry out load loading, and primary visually inspection is carried out when often reaching pre-determined number
It looks into, if fatigue rupture phenomenon occurs in testpieces, stops experiment, record cycle-index and destruction position, otherwise testpieces is carried out
Nondestructive inspection enters second stage after qualified；
3.2：Fatigue test second stage, cycle carry out load loading, and primary visually inspection is carried out when often reaching pre-determined number
Look into, if fatigue rupture phenomenon occurs in testpieces, stop experiment, record cycle-index and destroy position, otherwise continue experiment until
Terminate, record cycle-index.
Preferably, the sine wave CYCLIC LOADING is 0.06 according to stress ratio, and loading hertz is loaded for 2Hz.
Preferably, load loaded cycle number 7500 times in the fatigue test first stage, every 500 progress are primary
Visual inspection.
Preferably, load loaded cycle number 7500~15000 times, every 500 times in the fatigue test first stage
Once visually inspected.
A kind of aircraft nose landing gear outer barrel strut connector launch fatigue test method provided by the present invention it is beneficial
Effect is, selects wherein structural weak link according to undercarriage carrying situation or carries larger key position, and design is a kind of
Nose-gear typical structure part to substitute full-scale undercarriage, content of the test is concentrated on, static strength is carried out on typical structure part
Experiment examination can not only verify the reliability of nose-gear structure type design, optimize for full-scale undercarriage design of part
Design provides technical support, and can reduce full-scale undercarriage developing risk and development cost, shortens the lead time, is it
His project, which is developed, provides effective test method and means.
Description of the drawings
Fig. 1 is the structure diagram of nose-gear outer barrel；
Fig. 2 is the structure diagram of outer barrel strut connector test exemplar of the present invention；
Fig. 3 is stress diagram when outer barrel strut connector test exemplar load of the present invention loads；
Fig. 4 is outer barrel strut connector test exemplar clamping schematic diagram of the present invention；
Fig. 5 is sine wave CYCLIC LOADING curve graph in outer barrel strut connector test exemplar fatigue test of the present invention.
Reference numeral：
1- outer barrel struts connector, 2- outer barrel strut connector test exemplars.
Specific embodiment
To make the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction in the embodiment of the present invention
Attached drawing, the technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label represent same or similar element or the element with same or like function.Described embodiment is the present invention
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
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
Member's all other embodiments obtained without creative efforts, shall fall within the protection scope of the present invention.
The aircraft nose landing gear outer barrel strut connector launch fatigue test method of the present invention is done below in conjunction with the accompanying drawings
It is further described.
As shown in Figures 1 to 5, a kind of aircraft nose landing gear outer barrel strut connector launch fatigue test method, passes through
Following steps are implemented：
First according to nose-gear outer tube structure, the tests exemplar of outer barrel strut connector 1 thereon, undercarriage outer barrel are made
Structure is shown in Fig. 1, and outer barrel strut connector test exemplar is shown in Fig. 2.
Secondly 2 clamping of outer barrel strut connector test exemplar is first subjected to test of static strength on the fixture of Fig. 4, loaded
Form is as shown in Figure 3.
Then carry out fatigue test, wherein X, Y, Z-direction load coordinate loading, and select to use stress ratio for 0.06 just
String wave CYCLIC LOADING mode, loading curve as shown in Figure 5, loading frequency 2Hz.
The fatigue test is divided into two stages progress.
The fatigue test first stage：Cycle carries out load loading, and cycle-index selects 7500 times, when often reaching pre-determined number
It is once visually inspected, which selects 500 times.If there is fatigue rupture phenomenon during this step-by-step test, stop
It only tests, otherwise record cycle-index and destruction position carry out testpieces nondestructive inspection, entering second stage after qualified tries
It tests.
Fatigue test second stage：Cycle carries out load loading, and cycle-index selection (7500~15000) is secondary, often reaches
It is once visually inspected during pre-determined number, which selects 500 times.If it is broken to occur fatigue during this step-by-step test
Bad phenomenon stops experiment, record cycle-index and destruction position, otherwise continues experiment until terminating, record cycle-index.
The above description is merely a specific embodiment, but protection scope of the present invention is not limited thereto, any
Those familiar with the art in the technical scope disclosed by the present invention, all should by the change or replacement that can be readily occurred in
It is included within the scope of the present invention.Therefore, protection scope of the present invention should using the scope of the claims as
It is accurate.
Claims (4)
1. a kind of aircraft nose landing gear outer barrel strut connector launch fatigue test method, which is characterized in that including walking as follows
Suddenly,
Step 1：According to nose-gear outer tube structure, the tests exemplar of outer barrel strut connector (1) thereon is made；
Step 2：By outer barrel strut connector test exemplar (2) clamping on fixture, test of static strength is carried out；
Step 3：Fatigue test is carried out, wherein X, Y, Z-direction load coordinate loading, and use sine wave CYCLIC LOADING；
3.1：Fatigue test first stage, cycle carry out load loading, are once visually inspected when often reaching pre-determined number, if
There is fatigue rupture phenomenon in testpieces, stops experiment, record cycle-index and destruction position, otherwise carries out lossless spy to testpieces
Wound enters second stage after qualified；
3.2：Fatigue test second stage, cycle carry out load loading, are once visually inspected when often reaching pre-determined number, if
There is fatigue rupture phenomenon in testpieces, stops experiment, record cycle-index and destruction position, otherwise continues experiment until terminating,
Record cycle-index.
2. aircraft nose landing gear outer barrel strut connector launch fatigue test method according to claim 1, feature
It is, the sine wave CYCLIC LOADING is 0.06 according to stress ratio, and loading hertz is loaded for 2Hz.
3. aircraft nose landing gear outer barrel strut connector launch fatigue test method according to claim 2, feature
It is, load loaded cycle number 7500 times in the fatigue test first stage, is once visually inspected for every 500 times.
4. aircraft nose landing gear outer barrel strut connector launch fatigue test method according to claim 3, feature
It is, load loaded cycle number 7500~15000 times in the fatigue test first stage, every 500 progress are primary visual
It checks.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711229914.5A CN108163226A (en) | 2017-11-29 | 2017-11-29 | A kind of aircraft nose landing gear outer barrel strut connector launch fatigue test method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711229914.5A CN108163226A (en) | 2017-11-29 | 2017-11-29 | A kind of aircraft nose landing gear outer barrel strut connector launch fatigue test method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108163226A true CN108163226A (en) | 2018-06-15 |
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|---|---|---|---|
| CN201711229914.5A Pending CN108163226A (en) | 2017-11-29 | 2017-11-29 | A kind of aircraft nose landing gear outer barrel strut connector launch fatigue test method |
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Citations (5)
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|---|---|---|---|---|
| CN102556363A (en) * | 2011-12-20 | 2012-07-11 | 南京航空航天大学 | Servo motor type undercarriage retractile follow-up loading system and loading method of loading system |
| CN202518458U (en) * | 2011-05-04 | 2012-11-07 | 中国航空工业集团公司西安飞机设计研究所 | Stiffened wallboard fatigue test transition section |
| CN104773306A (en) * | 2015-04-07 | 2015-07-15 | 中国直升机设计研究所 | Main landing gear three-way loading test device |
| CN106441839A (en) * | 2016-09-09 | 2017-02-22 | 中国航空工业集团公司沈阳飞机设计研究所 | Strength verification method for super steel laser molding undercarriage |
| CN106525365A (en) * | 2016-10-28 | 2017-03-22 | 中航动力股份有限公司 | Aeroengine wheel disc crack prefabrication test system and test method |
-
2017
- 2017-11-29 CN CN201711229914.5A patent/CN108163226A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202518458U (en) * | 2011-05-04 | 2012-11-07 | 中国航空工业集团公司西安飞机设计研究所 | Stiffened wallboard fatigue test transition section |
| CN102556363A (en) * | 2011-12-20 | 2012-07-11 | 南京航空航天大学 | Servo motor type undercarriage retractile follow-up loading system and loading method of loading system |
| CN104773306A (en) * | 2015-04-07 | 2015-07-15 | 中国直升机设计研究所 | Main landing gear three-way loading test device |
| CN106441839A (en) * | 2016-09-09 | 2017-02-22 | 中国航空工业集团公司沈阳飞机设计研究所 | Strength verification method for super steel laser molding undercarriage |
| CN106525365A (en) * | 2016-10-28 | 2017-03-22 | 中航动力股份有限公司 | Aeroengine wheel disc crack prefabrication test system and test method |
Non-Patent Citations (1)
| Title |
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| 孙侠生主编: "《民用飞机结构强度刚度设计与验证指南 第2册》", 30 September 2012 * |
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Application publication date: 20180615 |
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