CN103983463A - Method for verification test of combined loading of airframe and undercarriage - Google Patents
Method for verification test of combined loading of airframe and undercarriage Download PDFInfo
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- CN103983463A CN103983463A CN201410156235.XA CN201410156235A CN103983463A CN 103983463 A CN103983463 A CN 103983463A CN 201410156235 A CN201410156235 A CN 201410156235A CN 103983463 A CN103983463 A CN 103983463A
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Abstract
The invention belongs to the field of airplane design and relates to a method for a verification test of combined loading of an airframe and an undercarriage. The method is characterized in that firstly, assessment of a load is conducted; secondly, a loading scheme is designed; thirdly, loading is tested; the load of the undercarriage serves as an examination working condition of a full-aircraft static test, combined loading of the airframe and the undercarriage is achieved in the full-aircraft static test, and an airframe structure static strength design envelope under the special working condition of the undercarriage can be fully verified.
Description
Technical field
The invention belongs to airplane design field, relate to the checking test method of a kind of airframe and undercarriage combination loading.
Background technology
In airplane design process, for examining its intensity whether to meet design requirement, carry out slow test.The slow test of aircraft is divided into again full machine slow test and parts slow test by examination position and experimental scale.The bulk strength deposit in the complete various load working condition lower body of machine structure is mainly examined in full machine slow test, and the margin of safety at local load's effect lower body ad hoc structure is mainly examined in parts slow test.Conventionally, the load of parts slow test can not cause static(al) damage to airframe structure or important connecting portion, and therefore full machine test and component test are often carried out respectively.Gear test just belongs to component test, only examines the intensity of undercarriage itself and undercarriage and housing construction connecting portion while carrying out undercarriage slow test separately.
For meeting the Special use requirement of some aircrafts, some components ' loads (especially landing-gear load) will cause compared with macrolesion housing construction key position.For example, for certain stationary platform landing aircraft waterborne, have that fall rate is large, center of gravity overload is high its moment of landing, the range of influence of its undercarriage bearing load has not only been confined to the housing construction being connected with undercarriage, also can cause very large impact to other structures of body simultaneously, and this load condition belongs to undercarriage components ' load, in full machine test, can not be verified.
Summary of the invention
The present invention is a kind of method of aircraft body structure and undercarriage combination loading, can verify the housing construction Static Strength Design envelope curve under undercarriage particular service requirement comprehensively.
Technical scheme of the present invention is: a kind of aircraft body structure and undercarriage combination loading method, it is characterized in that, and comprise the steps:
The first, the assessment of load.Draw respectively aircraft under complete airborne lotus and landing-gear load effect along course and exhibition to shearing, moment curve, contrast two kinds of loaded-up conditions at the whole internal force of housing construction, if the maximum internal force that landing-gear load causes is greater than the maximum internal force that complete airborne lotus causes, a kind of load condition using landing-gear load as full machine slow test;
The second, the design of loading scheme.In full machine slow test, using landing-gear load as a kind of test load situation, by landing-gear load, design separately loading scheme.The trim of load adopts the Calculate Ways of coordinated multi-point, chooses wing primary load bearing member and fuselage main bulkhead as the active load(ing) point of complete airborne lotus, and the complete airborne lotus while applying aircraft landing applies landing-gear load simultaneously on undercarriage.Choose engine bogusware as obligatory point, the support reaction being caused by the error of calculation or loading error in order to balance.
The 3rd, test loads.During imposed load, fuselage adopts rubberized tape to load, and undercarriage adopts urceolus to load.
Advantage of the present invention is:
This method has solved carries out separately full machine test or the gear test problem of proof machine body structure static strength deposit comprehensively, and a kind of load working condition using landing-gear load as full machine test has simultaneously been verified the intensity of undercarriage in full machine test.In a test, verified the intensity of a plurality of members, shortened test progress, improve test efficiency.
Accompanying drawing explanation
The full machine shear diagram of accompanying drawing 1
The full machine moment curve of accompanying drawing 2
Embodiment
Below by specific embodiment, also the present invention is described in further detail by reference to the accompanying drawings.
The first, draw shearing, the moment curve of aircraft under complete airborne lotus and landing-gear load, see accompanying drawing 1, accompanying drawing 2.Cartographic data is full machine result of finite element, and drafting instrument is Excel2007.The internal force that in figure, landing-gear load causes is greater than the internal force that full machine aerodynamic loading causes in part, therefore need to be using landing-gear load a kind of load working condition in full machine slow test.
The second, the design of loading scheme.In full machine slow test, using landing-gear load as a kind of test load situation, by landing-gear load, design separately loading scheme.The trim of load adopts the Calculate Ways of coordinated multi-point, chooses wing primary load bearing member and fuselage main bulkhead as the active load(ing) point of complete airborne lotus, and the complete airborne lotus while applying aircraft landing applies landing-gear load simultaneously on undercarriage.Choose engine bogusware as obligatory point, the support reaction being caused by the error of calculation or loading error in order to balance.
The 3rd, test loads.During imposed load, fuselage adopts rubberized tape to load, and undercarriage adopts urceolus to load.
Claims (3)
1. a checking test method for airframe and undercarriage combination loading, is characterized in that, comprises the steps:
First, the assessment of load: draw respectively aircraft under complete airborne lotus and landing-gear load effect along course and exhibition to shearing, moment curve, contrast two kinds of loaded-up conditions at the whole internal force of housing construction, if the maximum internal force that landing-gear load causes is greater than the maximum internal force that complete airborne lotus causes, a kind of load condition using landing-gear load as full machine slow test, proceeds to second step;
The second, the design of loading scheme: in full machine slow test, using landing-gear load as a kind of test load situation, design separately loading scheme by landing-gear load; The trim of load adopts the Calculate Ways of coordinated multi-point, chooses wing primary load bearing member and fuselage main bulkhead as the active load(ing) point of complete airborne lotus, and the complete airborne lotus while applying aircraft landing applies landing-gear load simultaneously on undercarriage; Choose engine bogusware as obligatory point, the support reaction being caused by the error of calculation or loading error in order to balance.
The 3rd, test loads: during imposed load, fuselage adopts rubberized tape to load, and undercarriage adopts urceolus to load.
2. the checking test method of airframe according to claim 1 and undercarriage combination loading, is characterized in that, described shearing, moment curve calculate by aircraft model, can reflect the interior force-responsive under the housing construction effect of carrying outside.
3. the checking test method of airframe according to claim 1 and undercarriage combination loading, it is characterized in that, the Calculate Ways of described coordinated multi-point is chosen the member that housing construction load-bearing capacity is strong, arrange and initiatively load rubberized tape thereon, equilibrium condition according to power under 3 d space coordinate system, by the distributed load equivalence rubberized tape on fuselage, is directly loaded into landing-gear load on undercarriage urceolus, after loading, full machine is in stress balance state.
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| CN201410156235.XA CN103983463B (en) | 2014-04-17 | 2014-04-17 | A kind of airframe and the checking test method of undercarriage combination loading |
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| CN201410156235.XA CN103983463B (en) | 2014-04-17 | 2014-04-17 | A kind of airframe and the checking test method of undercarriage combination loading |
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| CN103983463A true CN103983463A (en) | 2014-08-13 |
| CN103983463B CN103983463B (en) | 2016-08-24 |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104477404A (en) * | 2014-11-19 | 2015-04-01 | 中国航空工业集团公司沈阳飞机设计研究所 | Ground validation method of main load-bearing structural member of fuselage under large load |
| CN105447269A (en) * | 2015-12-15 | 2016-03-30 | 西北工业大学 | Non-structural mass trimming method for airplane in steady overload state |
| CN108459517A (en) * | 2018-04-18 | 2018-08-28 | 北京强度环境研究所 | Apply the method for a variety of load |
| CN109305384A (en) * | 2018-11-23 | 2019-02-05 | 中国航空工业集团公司沈阳飞机设计研究所 | The fining aerodynamic loading of aircraft surfaces lid determines method |
| CN109711008A (en) * | 2018-12-12 | 2019-05-03 | 南京航空航天大学 | A kind of center of gravity of airplane envelope curve calculation method |
| CN110002003A (en) * | 2019-03-29 | 2019-07-12 | 中国飞机强度研究所 | A kind of undercarriage Plumb load and restraint device |
| CN112109919A (en) * | 2020-04-30 | 2020-12-22 | 中国飞机强度研究所 | Strength test loading point layout method |
| CN112591135A (en) * | 2020-11-03 | 2021-04-02 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft static test load loading method |
| CN113704878A (en) * | 2021-08-05 | 2021-11-26 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for applying landing gear load to aircraft structure full-aircraft finite element model |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106442284A (en) * | 2016-09-07 | 2017-02-22 | 中国航空工业集团公司沈阳飞机设计研究所 | Airplane landing gear structure corrosion protection system acceleration corrosion test method |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2007154983A (en) * | 2005-12-05 | 2007-06-21 | Sumitomo Precision Prod Co Ltd | Hydraulic device, loading device and alighting gear |
| CN101788397A (en) * | 2010-02-26 | 2010-07-28 | 中国航空工业集团公司西安飞机设计研究所 | Method for supporting static test for light-aircraft fore fuselages |
| EP2190744B1 (en) * | 2007-09-19 | 2012-04-18 | Messier-Dowty Limited | Load indicator and method for detecting a hard landing or an overload force during towing of an aircraft |
| WO2012055699A1 (en) * | 2010-10-28 | 2012-05-03 | Eads Deutschland Gmbh | Maintenance information apparatus, state sensor for use therein, and method which can be performed thereby for making a decision for or against maintenance |
| CN202267609U (en) * | 2011-08-31 | 2012-06-06 | 中国商用飞机有限责任公司 | Aircraft landing gear loading system |
-
2014
- 2014-04-17 CN CN201410156235.XA patent/CN103983463B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2007154983A (en) * | 2005-12-05 | 2007-06-21 | Sumitomo Precision Prod Co Ltd | Hydraulic device, loading device and alighting gear |
| EP2190744B1 (en) * | 2007-09-19 | 2012-04-18 | Messier-Dowty Limited | Load indicator and method for detecting a hard landing or an overload force during towing of an aircraft |
| CN101788397A (en) * | 2010-02-26 | 2010-07-28 | 中国航空工业集团公司西安飞机设计研究所 | Method for supporting static test for light-aircraft fore fuselages |
| WO2012055699A1 (en) * | 2010-10-28 | 2012-05-03 | Eads Deutschland Gmbh | Maintenance information apparatus, state sensor for use therein, and method which can be performed thereby for making a decision for or against maintenance |
| CN202267609U (en) * | 2011-08-31 | 2012-06-06 | 中国商用飞机有限责任公司 | Aircraft landing gear loading system |
Non-Patent Citations (1)
| Title |
|---|
| 李兵等: "直升机起落架机轮轴载荷分析与强度校核", 《装备制造技术》 * |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104477404B (en) * | 2014-11-19 | 2018-03-02 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of ground validation method of fuselage main force support structure part under big load |
| CN104477404A (en) * | 2014-11-19 | 2015-04-01 | 中国航空工业集团公司沈阳飞机设计研究所 | Ground validation method of main load-bearing structural member of fuselage under large load |
| CN105447269A (en) * | 2015-12-15 | 2016-03-30 | 西北工业大学 | Non-structural mass trimming method for airplane in steady overload state |
| CN105447269B (en) * | 2015-12-15 | 2019-01-11 | 西北工业大学 | A kind of non-structural mass Calculate Ways of aircraft under permanent overload |
| CN108459517B (en) * | 2018-04-18 | 2021-06-11 | 北京强度环境研究所 | Method for applying multiple loads |
| CN108459517A (en) * | 2018-04-18 | 2018-08-28 | 北京强度环境研究所 | Apply the method for a variety of load |
| CN109305384A (en) * | 2018-11-23 | 2019-02-05 | 中国航空工业集团公司沈阳飞机设计研究所 | The fining aerodynamic loading of aircraft surfaces lid determines method |
| CN109711008A (en) * | 2018-12-12 | 2019-05-03 | 南京航空航天大学 | A kind of center of gravity of airplane envelope curve calculation method |
| CN110002003A (en) * | 2019-03-29 | 2019-07-12 | 中国飞机强度研究所 | A kind of undercarriage Plumb load and restraint device |
| CN112109919A (en) * | 2020-04-30 | 2020-12-22 | 中国飞机强度研究所 | Strength test loading point layout method |
| CN112109919B (en) * | 2020-04-30 | 2024-04-19 | 中国飞机强度研究所 | Loading point layout method for strength test |
| CN112591135A (en) * | 2020-11-03 | 2021-04-02 | 中国航空工业集团公司沈阳飞机设计研究所 | Aircraft static test load loading method |
| CN113704878A (en) * | 2021-08-05 | 2021-11-26 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for applying landing gear load to aircraft structure full-aircraft finite element model |
| CN113704878B (en) * | 2021-08-05 | 2023-10-10 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for applying load of landing gear by using aircraft structure full-aircraft finite element model |
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