CN103983463B - A kind of airframe and the checking test method of undercarriage combination loading - Google Patents
A kind of airframe and the checking test method of undercarriage combination loading Download PDFInfo
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- CN103983463B CN103983463B CN201410156235.XA CN201410156235A CN103983463B CN 103983463 B CN103983463 B CN 103983463B CN 201410156235 A CN201410156235 A CN 201410156235A CN 103983463 B CN103983463 B CN 103983463B
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Abstract
The invention belongs to field of airplane design, relate to the checking test method of a kind of airframe and undercarriage combination loading, it is characterised in that first, the assessment of load；Second, the design of loading scheme；3rd, test loads；Landing-gear load is examined operating mode as one full machine slow test, full machine slow test achieves the combination loading of body and undercarriage, it is possible to the housing construction Static Strength Design envelope curve under comprehensive verification undercarriage particular service requirement.
Description
Technical field
The invention belongs to field of airplane design, relate to a kind of airframe and undercarriage combination loading
Checking test method.
Background technology
During airplane design, for examining whether its intensity meets design requirement, carry out quiet
Power is tested.The slow test of aircraft is divided into again full machine slow test by examination position and experimental scale
With parts slow test.Full machine slow test is mainly examined at full machine various load working condition lower body
The bulk strength deposit of structure, parts slow test is mainly examined and is acted on lower body in local load
The margin of safety of ad hoc structure.Generally, airframe will not be tied by the load of parts slow test
Structure or important connecting portion cause static(al) to damage, and therefore full machine test and component test are often distinguished
Carry out.Gear test just belongs to component test, individually carries out only examining during undercarriage slow test
Core undercarriage itself and undercarriage and the intensity of housing construction connecting portion.
For meeting the Special use requirement of some aircrafts, some components ' loads (especially undercarriage
Load) housing construction key position will be caused relatively macrolesion.Such as, waterborne solid for certain
Fixed platform landing aircraft, has that fall rate is big, center of gravity overload height its moment of landing, and it rises and falls
Frame bears the housing construction that the influence area of load has been not limited solely to be connected with undercarriage,
Also other structures of body can be caused the biggest impact simultaneously, and this load condition belongs to and rises and falls
Frame components ' load, can not be verified in full machine is tested.
Summary of the invention
The present invention is a kind of aircraft body structure and the method for undercarriage combination loading, can test comprehensively
Housing construction Static Strength Design envelope curve under card undercarriage particular service requirement.
The technical scheme is that a kind of aircraft body structure and undercarriage combination loading method,
It is characterized in that, comprise the steps:
First, the assessment of load.Draw aircraft edge under complete airborne lotus and landing-gear load effect respectively
Course and exhibition to shearing, bending moment diagram, contrast two kinds of loaded-up conditions housing construction entirety in
Power, if the maximum internal force that the maximum internal force that landing-gear load causes causes more than complete airborne lotus,
Then using landing-gear load as a kind of load condition of full machine slow test；
Second, the design of loading scheme.In full machine slow test, using landing-gear load as one
Test load situation, by the individually designed loading scheme of landing-gear load.The trim of load uses many
The Calculate Ways that point is coordinated, i.e. chooses wing primary load bearing component and fuselage main bulkhead as full machine
The active load(ing) point of load, applies complete airborne lotus during aircraft landing, executes on undercarriage simultaneously
Add landing-gear load.Choose electromotor bogusware as obligatory point, in order to balance by calculate error or
The support reaction that loading error causes.
3rd, test loads.During imposed load, fuselage uses rubberized tape to load, outside undercarriage uses
Cylinder loads.
The invention have the advantage that
Present method solves and individually carry out full machine test or gear test can not comprehensive verification machine
The problem of body structural static strength deposit, a kind of load simultaneously landing-gear load tested as full machine
Lotus operating mode, demonstrates the intensity of undercarriage in full machine is tested.I.e. demonstrate in a test
The intensity of multiple components, shortens test progress, improves test efficiency.
Accompanying drawing explanation
The full machine shear diagram of accompanying drawing 1
The full machine bending moment diagram of accompanying drawing 2
Detailed description of the invention
Below by specific embodiment and combine accompanying drawing the present invention is made further details of retouching
State.
The first, draw aircraft shearing under complete airborne lotus and landing-gear load, bending moment diagram, 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 the internal force that in figure, landing-gear load causes causes more than full machine aerodynamic loading in local, because of
This needs landing-gear load as 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 one
Test load situation, by the individually designed loading scheme of landing-gear load.The trim of load uses many
The Calculate Ways that point is coordinated, i.e. chooses wing primary load bearing component and fuselage main bulkhead as full machine
The active load(ing) point of load, applies complete airborne lotus during aircraft landing, executes on undercarriage simultaneously
Add landing-gear load.Choose electromotor bogusware as obligatory point, in order to balance by calculate error or
The support reaction that loading error causes.
3rd, test loads.During imposed load, fuselage uses rubberized tape to load, outside undercarriage uses
Cylinder loads.
Claims (3)
1. an airframe and the checking test method of undercarriage combination loading, it is characterised in that
Comprise the steps:
First, the assessment of load: draw aircraft edge under complete airborne lotus and landing-gear load effect respectively
Course and exhibition to shearing, bending moment diagram, contrast two kinds of loaded-up conditions housing construction entirety in
Power, if the maximum internal force that the maximum internal force that landing-gear load causes causes more than complete airborne lotus,
Then using landing-gear load as a kind of load condition of full machine slow test, proceed to second step；
Second, the design of loading scheme: in full machine slow test, using landing-gear load as one
Test load situation, by the individually designed loading scheme of landing-gear load；The trim of load uses many
The Calculate Ways that point is coordinated, i.e. chooses wing primary load bearing component and fuselage main bulkhead as full machine
The active load(ing) point of load, applies complete airborne lotus during aircraft landing, executes on undercarriage simultaneously
Add landing-gear load；Choose electromotor bogusware as obligatory point, in order to balance by calculate error or
The support reaction that loading error causes；
3rd, test loads: during imposed load, and fuselage uses rubberized tape to load, outside undercarriage uses
Cylinder loads.
Airframe the most according to claim 1 and the checking test side of undercarriage combination loading
Method, it is characterised in that described shearing, bending moment diagram are calculated by aircraft model,
The interior force-responsive under housing construction load effect outside can be reflected.
Airframe the most according to claim 1 and the checking test side of undercarriage combination loading
Method, it is characterised in that it is strong that the Calculate Ways of described coordinated multi-point chooses housing construction bearing capacity
Component, thereon arrange actively load rubberized tape, according to power under 3 d space coordinate system
Equilibrium condition, by the distributed load equivalence rubberized tape on fuselage, directly adds landing-gear load
Being downloaded on undercarriage urceolus, after loading, full machine is in stress balance state.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410156235.XA CN103983463B (en) | 2014-04-17 | 2014-04-17 | A kind of airframe and the checking test method of undercarriage combination loading |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410156235.XA CN103983463B (en) | 2014-04-17 | 2014-04-17 | A kind of airframe and the checking test method of undercarriage combination loading |
Publications (2)
| Publication Number | Publication Date |
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| CN103983463A CN103983463A (en) | 2014-08-13 |
| CN103983463B true CN103983463B (en) | 2016-08-24 |
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| CN201410156235.XA Active 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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Cited By (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 |
Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
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| 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 |
| 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 |
| CN109305384B (en) * | 2018-11-23 | 2022-02-22 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for determining fine aerodynamic load of airplane surface covering cap |
| 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 |
| 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 |
| 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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| CN103983463A (en) | 2014-08-13 |
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