CN108168855A - A kind of aircraft nose landing gear outer barrel suspension joint launch slow test method - Google Patents
A kind of aircraft nose landing gear outer barrel suspension joint launch slow test method Download PDFInfo
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- CN108168855A CN108168855A CN201711229963.9A CN201711229963A CN108168855A CN 108168855 A CN108168855 A CN 108168855A CN 201711229963 A CN201711229963 A CN 201711229963A CN 108168855 A CN108168855 A CN 108168855A
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- load
- outer barrel
- suspension joint
- test
- barrel suspension
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/08—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces
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- General Health & Medical Sciences (AREA)
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- Pathology (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The present invention provides a kind of aircraft nose landing gear outer barrel suspension joint launch slow test method, and step is as follows：Situation is carried according to outer barrel suspension joint, determines its crucial force part and foil gauge patch location；Foil gauge is detected, ensures more than 95% foil gauge survival rate when loading measures；The exemplar of outer barrel suspension joint is made, and exemplar is mounted on fixture and applies load；Load test is divided into prerun and formal test, prerun is according to 5% limitation load multistage loadings to 60% limitation load, formal test includes one time 100% limitation load test and 150% Ultimate load test, the former is according to 5% limitation load multistage loadings, 100% limitation load limits load multistage loadings according to 50% limitation load after 5% limitation load multistage loadings according to 2% before the latter, above step exemplar does not destroy, then assert that outer barrel suspension joint passes through slow test.Slow 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 suspension joint launch slow 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 suspension joint is subjected to whole hauled loads.As a kind of undercarriage of brand-new design, if directly
Connect and slow 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 suspension joint launch slow 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 suspension joint launch
Slow test method, includes the following steps,
Step 1：Outer barrel suspension joint is calculated by analysis and carries situation, determines outer barrel suspension joint key force part
And foil gauge patch location；
Step 2：Foil gauge is detected, count and is supplemented, ensures that foil gauge is survived when load test measures；
Step 3：Make the tests exemplar of the outer barrel suspension joint；
Step 4：Outer barrel suspension joint tests exemplar is mounted on special fixture, applies load by loading pressurized strut；
4.1：Prerun is carried out, according to gradient A multistage loadings to predetermined limit load, with checkout facility system mode and is tensed
Outer barrel suspension joint tests exemplar eliminates gap；
4.2：Formal test is carried out, is first kept to schedule to 100% limitation load according to gradient B multistage loadings
Load is offloaded to 0 step by step, and test data is analyzed, and checkout facility exemplar state；According still further to gradient B multistage loadings extremely
100% limitation load, if experiment gathered data repeatability is good, according to gradient C multistage loadings to ultimate load, according to pre- timing
Between keep load, test data is analyzed, and checkout facility exemplar；
Step 5：Alignment type experiment evaluated, 100% limitation load test after, outer barrel suspension joint tests exemplar without
It destroys, no yield deformation or is loaded onto in the case of ultimate load, tests exemplar is not destroyed, then assert that the suspension of nose-gear outer barrel connects
Head is examined by slow test.
Preferably, ensure that the foil gauge survival rate is more than 95% when load test measures.
Preferably, in the step 4.1, the gradient A is 5% limitation load, and the predetermined limit load is 60%
Limit load.
Preferably, in the step 4.2, the gradient B is 5% limitation load, and the predetermined time for keeping load is
30s。
Preferably, in the step 4.2, the ultimate load is 150% limitation load, and the gradient C is 2% limitation
Load, the predetermined time for keeping load are 3s.
Preferably, requiring to include for the checkout facility part in the step 4 measures each foil gauge in load test
Strain, strain measurement classification carry out, and the strain of foil gauge, measurement error requirement are little when recording every grade of load according to loading rank
In 2%.
A kind of aircraft nose landing gear outer barrel suspension joint launch slow 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 suspension joint tests exemplar of the present invention；
Fig. 3 is stress diagram when outer barrel suspension joint tests exemplar load of the present invention loads；
Fig. 4 is invention outer barrel suspension joint tests exemplar clamping schematic diagram.
Reference numeral：
1- outer barrels suspension joint, 2- outer barrel suspension joint tests 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 suspension joint launch slow 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 4, a kind of aircraft nose landing gear outer barrel suspension joint launch slow test method, by such as
Lower step is implemented.
Step 1 calculates outer barrel suspension joint by analysis and carries situation, determines outer barrel suspension joint key force part
And foil gauge patch location, as shown in Figure 1.
Step 2 is detected foil gauge, counts and supplements, and ensures that foil gauge is survived when load test measures, survival
Rate ensures more than 95%.
Step 3 makes the tests exemplar of the outer barrel suspension joint 1, as shown in Figure 2.
Outer barrel suspension joint tests exemplar 2 is mounted on special fixture, as shown in Figure 4, by loading start by step 4
Cylinder applies load, and loading form is as shown in Figure 3.
The test procedure of load test is divided into prerun and formal test.
Prerun：According to gradient A multistage loadings to predetermined limit load, gradient A is preferably 5% limitation load, pre- fixed limit
Load processed is preferably 60% limitation load.The purpose of the prerun is the state of checkout facility system and outer barrel suspension joint is tested
Exemplar 2 tenses, and eliminates gap, and wherein inspection item includes：Check whether loading system, measuring system are normal, experiment installation shape
Whether state is intact, analyzes measurement data, judges whether load applies accurate.
Formal test：Including one time 100% limitation load test and 150% Ultimate load test.First carry out 100%
Limit load test：It selects, using 5% limitation load as level-one, after multistage loadings to 100% limitation load, to protect to schedule
Hold load, then which is offloaded to 0 (being also 5% limitation load) step by step, after the completion of experiment, to test data into
Row analysis, checks tests exemplar.Followed by 150% Ultimate load test.Selection is added step by step with 5% limitation load
After being loaded onto 100% limitation load, if experiment gathered data repeatability is good, select to be loaded onto 150% with every grade 2% limitation load
Ultimate load test keeps load to schedule, which analyzes test data after the completion of experiment,
Tests exemplar is checked.
It should be noted that requiring to include for checkout facility part is as follows：1) answering for each foil gauge is measured in load test
Become；2) strain measurement classification carries out, the strain of foil gauge when recording every grade of load according to loading rank；3) measurement error requires not
More than 2%.
Step 5, alignment type experiment are evaluated, for each load condition, after 100% limits load test, outer barrel
Suspension joint tests exemplar 2 no yield deformation or is loaded onto in the case of 150% ultimate load without destruction, and tests exemplar is not destroyed,
Then assert that nose-gear outer barrel suspension joint is examined by slow test.
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 (6)
- A kind of 1. aircraft nose landing gear outer barrel suspension joint launch slow test method, which is characterized in that including walking as follows Suddenly,Step 1：Outer barrel suspension joint is calculated by analysis and carries situation, determine outer barrel suspension joint key force part and Foil gauge patch location；Step 2：Foil gauge is detected, count and is supplemented, ensures that foil gauge is survived when load test measures；Step 3：Make the tests exemplar of the outer barrel suspension joint (1)；Step 4：By outer barrel suspension joint tests exemplar (2) on special fixture, apply load by loading pressurized strut；4.1：Prerun is carried out, according to gradient A multistage loadings to predetermined limit load, with checkout facility system mode and tenses outer barrel Suspension joint tests exemplar (2) eliminates gap；4.2：Formal test is carried out, first according to gradient B multistage loadings to 100% limitation load, keeps load to schedule, It is offloaded to 0 step by step, test data is analyzed, and checkout facility exemplar state；According still further to gradient B multistage loadings to 100% Load is limited, if experiment gathered data repeatability is good, according to gradient C multistage loadings to ultimate load, is protected to schedule Load is held, test data is analyzed, and checkout facility exemplar；Step 5：Alignment type experiment is evaluated, and after 100% limitation load test, outer barrel suspension joint tests exemplar (2) is without broken It is bad, it no yield deformation or is loaded onto in the case of ultimate load, tests exemplar is not destroyed, then assert nose-gear outer barrel suspension joint It is examined by slow test.
- 2. aircraft nose landing gear outer barrel suspension joint launch slow test method according to claim 1, feature It is, ensures that the foil gauge survival rate is more than 95% when load test measures.
- 3. aircraft nose landing gear outer barrel suspension joint launch slow test method according to claim 2, feature It is, in the step 4.1, the gradient A is 5% limitation load, and the predetermined limit load is 60% limitation load.
- 4. aircraft nose landing gear outer barrel suspension joint launch slow test method according to claim 3, feature It is, in the step 4.2, for the gradient B for 5% limitation load, the predetermined time for keeping load is 30s.
- 5. aircraft nose landing gear outer barrel suspension joint launch slow test method according to claim 4, feature It is, in the step 4.2, the ultimate load is 150% limitation load, and the gradient C is 2% limitation load, keeps carrying The predetermined time of lotus is 3s.
- 6. aircraft nose landing gear outer barrel suspension joint launch slow test method according to claim 5, feature It is, the checkout facility part in the step 4 requires to include the strain that each foil gauge is measured in load test, strain survey Amount classification carries out, and the strain of foil gauge, measurement error requirement are no more than 2% when recording every grade of load according to loading rank.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711229963.9A CN108168855A (en) | 2017-11-29 | 2017-11-29 | A kind of aircraft nose landing gear outer barrel suspension joint launch slow test method |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201711229963.9A CN108168855A (en) | 2017-11-29 | 2017-11-29 | A kind of aircraft nose landing gear outer barrel suspension joint launch slow test method |
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| CN108168855A true CN108168855A (en) | 2018-06-15 |
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| CN201711229963.9A Pending CN108168855A (en) | 2017-11-29 | 2017-11-29 | A kind of aircraft nose landing gear outer barrel suspension joint launch slow test method |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109592075A (en) * | 2018-11-05 | 2019-04-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of dynamic monitoring and controlling method of aircraft structure fatigue test measurement data |
| CN112461648A (en) * | 2020-10-06 | 2021-03-09 | 湖北超卓航空科技股份有限公司 | Testing device for fatigue performance detection of sample piece |
| CN113702181A (en) * | 2021-08-16 | 2021-11-26 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Butt joint test device and test method for lower wall plate of wing root of airplane wing with upper dihedral angle |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109592075A (en) * | 2018-11-05 | 2019-04-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of dynamic monitoring and controlling method of aircraft structure fatigue test measurement data |
| CN109592075B (en) * | 2018-11-05 | 2022-04-19 | 中国航空工业集团公司西安飞机设计研究所 | Dynamic monitoring method for measuring data of airplane structure fatigue test |
| CN112461648A (en) * | 2020-10-06 | 2021-03-09 | 湖北超卓航空科技股份有限公司 | Testing device for fatigue performance detection of sample piece |
| CN113702181A (en) * | 2021-08-16 | 2021-11-26 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Butt joint test device and test method for lower wall plate of wing root of airplane wing with upper dihedral angle |
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Application publication date: 20180615 |