CN109710982A - Component-level simulation test piece design and verification method based on FEM Simulation - Google Patents
Component-level simulation test piece design and verification method based on FEM Simulation Download PDFInfo
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- CN109710982A CN109710982A CN201811469878.4A CN201811469878A CN109710982A CN 109710982 A CN109710982 A CN 109710982A CN 201811469878 A CN201811469878 A CN 201811469878A CN 109710982 A CN109710982 A CN 109710982A
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Abstract
The invention discloses the component-level simulation test piece design and verification methods based on FEM Simulation, this method is simplified on the basis of former aircaft configuration, retain the real structure at aircraft examination position, ensure that simulation test piece examination position is consistent with the aircraft original structure examination stress deformation at position, i.e., the structure type, loaded feature, manufacturing process at examination position and sealing technology are consistent with aircaft configuration.Simplify simulation test piece other structures according to aircraft original structure force path and primary structure form simultaneously, it is ensured that simulation test piece can simulate the various operating condition flowering structure internal environment situations of change of aircraft.So carrying out verification test high reliablity using component-level simulation test piece.
Description
Technical field
This method belongs to technical field of aircraft design, in particular to the component-level based on FEM Simulation simulates examination
Part design and verification method is tested, can be used for the design of component-level simulation test piece, demonstration, verification test.
Background technique
In order to meet the needs of state aviation Strategy & Tactics, the improvement remodeling work of different platform aircraft gradually increase with
China's diversification aviation mission demand is adapted to, equipment is largely newly ground and cutting edge technology will be gradually aboard using to improve aircraft
Self performance, aircaft configuration form, material, technology etc. also with airplane equipment and technology upgrading and constantly change
Become.Therefore, it is necessary to carry out verification test to verify the new structure form of emergence, new material, novel technique etc., answer at present
Carrying out verifying work with aircraft actual part structure is common mode, but aircraft actual part structure carries out test and there is examination
Test part manufacturing cost, the problems such as experimentation cost is excessively high, human time's cost is excessively high.So in this context, component-level mould
Quasi- testpieces can take into account the features such as structure type of aircraft examination validation region real structure, material, technique, while also can be right
The non-examination area of aircaft configuration, which simplifies processing, ensures that cost is unlikely to excessively high advantage and emerges from.It is external at present to use finite element fraction
Analysis means simplify the development component-level simulation test piece verifying work of design experiment part and have become ubiquitous, domestic seldom to carry out component
Grade simulation test piece design verification research, while also lacking corresponding component-level simulation test piece design and verification method, usually fly
The improvement Transform Type design verifying work of machine structure is opened using aircraft real structure part or according to airplane design personnel's experience
Often there is the problems such as testpieces simplifies unreasonable design, cost waste in exhibition design.Therefore, carry out component-level simulation test piece
Design and verification method research is significant.
Summary of the invention
Goal of the invention
It is an object of the invention to propose the component-level simulation test piece design and verification method based on FEM Simulation,
Design and manufacture test period can be greatly shortened, Structure Improvement Design workload, while component-level simulation test piece can be effectively reduced
Size is reduced, structure is simplified, the manufacturing cycle is short, the test period it is short can effectively shorten Structure Improvement Design proving period, mention significantly
Height solves the efficiency of problem analysis.
Inventive technique solution
In order to achieve the above-mentioned object of the invention, the present invention uses following technical solutions:
This method is simplified on the basis of former aircaft configuration, retains the real structure at aircraft examination position, it is ensured that mould
Quasi- test
Part examines position and aircraft original structure the examination stress deformation at position consistent, that is, examine position structure type, by
Load feature, manufacturing process and sealing technology are consistent with aircaft configuration.Simultaneously according to aircraft original structure force path and primary structure
Form simplifies simulation test piece other structures, it is ensured that simulation test piece can simulate the various operating condition flowering structure internal environment variations of aircraft
Situation.Using finite element analysis software and calculation optimization simulation test piece model.
Component-level simulation test piece design and verification method based on FEM Simulation, includes the following steps: step 1:
It examines position performance indicator to choose the overall structure that aircraft needs to examine according to aircraft, establishes the overall structure that aircraft needs to examine
Finite element model and carry out finite element method (fem) analysis；Step 2: being that aircraft needs to examine according to the result of finite element method (fem) analysis
Overall structure in key structure evaluation formulate criterion；Step 3: the whole knot that aircraft is needed to examine according to criterion
Structure carries out simplifying design；Step 4: dividing according to simplifying design forming member grade testpieces finite element model and carrying out FEM calculation
Aircraft obtained in component-level testpieces examination position result of finite element and step 1 is examined position FEM calculation by analysis
Analysis result compares and analyzes, and processing experiment part and carries out test if comparative analysis result meets criterion, if being unsatisfactory for sentencing
According to then improving component-level testpieces finite element model.
Preferably, the process of step 2 is as follows: finite element method (fem) analysis aircraft different operating conditions get off the plane needs examine it is whole
The ess-strain and deformation of body structure specify integrally-built loaded feature, force path, stress that aircraft needs to examine
Strain needs key structure evaluation in the overall structure examined to provide foundation, and formulates key structure evaluation criterion for aircraft.
Preferably, the process of step 3 is as follows: for non-key structure, carrying out if meeting criterion requirement to structure
Simplify design, retains technique；For key structure position, original structure form and technique are retained if meeting criterion requirement.
Preferably, the establishment process of component-level testpieces finite element model is as follows in step 4: consider design and manufacture condition because
Element is by the forming member grade simulation test piece CATIA model after simplifying design combination of non-key structure and key structure position, just
It walks the loading method for determining finite element model, magnitude of load, clamped mode and carries out FEM calculation and obtain component after analyzing
Grade testpieces finite element model.
Preferably, component-level testpieces examination position result of finite element and aircraft examine position finite element in step 4
First according to component-level simulation test piece analysis model for finite element feelings when Calculation results comparative analysis result meets criterion
Condition, while considering the design principle of craftsmanship, accessibility, repairability, modification and perfection component-level simulation test piece CATIA design adds
Work model, forming member grade simulation test piece process drawing；Then it is manufactured according to component-level simulation test piece manuscript paper conversion
Component-level simulation test piece；And according to component-level simulation test piece finite element analysis model, the examination of component-level simulation test piece is formulated
Proved recipe case simultaneously carries out test；Then comparative test and component-level simulation test piece result of finite element provide criterion requirement, if
Aircraft examination position stress deformation meets criterion and requires then to obtain examination position conclusion；The detail modifications if being unsatisfactory for criterion and requiring
Component-level simulation test piece model re-starts FEM calculation.
Advantages of the present invention
The present invention has the advantages that
Experimentation cost can be manufactured by reducing design significantly using component-level simulation test piece design and verification method, compared to use
The cost of aircraft original component verifying, can reduce by 60% cost, guarantee to improve verification experimental verification while examining real structure
Reliability is improved in remodeling verifying work in aircaft configuration and shows very high advantage.Component-level simulation test piece design verification
Method is that it is conveniently excellent to have given full play to finite element analysis by the way of both finite element analysis and analysis of experiments combination
The advantage of gesture and test part reliability, it is significant for the verifying work of structure design development.
Component-level simulation test piece design and verification method has very strong directiveness, is constantly improved by test data limited
Element analysis model and parameter improve finite element analysis software and verify ability, gradually accomplish to fly using finite element analysis software test
Machine structure design verification.
Detailed description of the invention
Fig. 1 is component-level simulation test piece design method flow diagram.
Fig. 2 is fuel tanker box section structure reduction procedure schematic diagram.
Fig. 3 is fuel tank simulation test piece finite element model figure.
Fig. 4 is fuel tank simulation test piece structural schematic diagram.
Fig. 5 is the seal durability test load schematic diagram of fuel tank simulating piece.
Specific embodiment
In conjunction with summary of the invention general introduction and attached drawing, the specific embodiment that the present invention will be described in detail.
By the seal durability design verification using wing tank as embodiment, detailed elaboration component-level simulation test piece
Design and verification method, for the leakage of oil problem that aircraft China and foreign countries wing box section wing sliding rail and web connecting portion occur, from limited
Fuel tank seal durability is verified in terms of first simulation analysis and verification test two.
A) selection of fuel tanker structure and FEM calculation and analysis
1) according to fuel tanker oil leak position, theory analysis tentatively is carried out to the structure type of fuel tanker, loaded feature,
The seal durability design verification for specifying wing tank examines position for China and foreign countries' wing box section wing sliding rail and web connecting portion, i.e.,
For oil leak position, chooses and determine the wing tank box section structure comprising aircraft oil leak position；
2) on the basis of aircraft aircraft model, oil leak site units are refined, form oil leak position wing tank
Box section structure finite element analysis model calculates the ess-strain and deformation of analysis of aircraft box section structure under different operating conditions,
Specify the loaded feature of structure in wing-box, force path, ess-strain, for wing box section key structure evaluation provide according to
According to, and formulate key structure evaluation criterion.
B) design of fuel tank simulation test piece, simplified and analysis
1) key structure evaluation is carried out to wing box section, feature, front and back is connect with web by box section wing sliding rail
The type of attachment of beam and each rib, edge strip tentatively simplify to wing box section, primarily determines that wing box section simplifies knot
Configuration formula and original structure form form wing box section and tentatively simplify design scheme；
2) on the basis of wing-box FEM calculation and analysis result, from the force path of wing box section, stress
Strain and deformation distributed areas etc., modify to preliminary reduction procedure and perfect, form final reduction procedure；
3) consider to manufacture and design condition element (technique manufacturing, repairability, accessibility etc.), form oil according to reduction procedure
Case simulation test piece CATIA manufactures and designs model, manufactures and designs model foundation finite element analysis model according to CATIA, preliminary true
Determine the loading method of finite element model, magnitude of load, clamped mode etc. carries out FEM calculation and analysis；
4) comparative analysis fuel tank simulation test piece examination position and wing-box examine position result of finite element (see
Table 1), by adjusting fuel tank simulation test piece model, loading method, magnitude of load, clamped mode ensures two examination positions
Ess-strain and deflection difference eventually form fuel tank simulation test piece analysis model for finite element, really in criteria
Experimental enviroment is composed under fixed each operating condition；
Deformation comparison under 1 loading spectrum maximum load of table
5) according to fuel tank simulation test piece analysis model for finite element situation, while considering craftsmanship, accessibility, can repair
Property design principle, modification and perfection fuel tank simulation test piece CATIA design processing model, formed fuel tank simulation test piece manuscript
Paper.
C) verifying and analysis
1) processing drawing is designed according to fuel tank simulation test piece, fabricates fuel tank simulation test piece；
2) according to fuel tank simulation test piece finite element analysis model, the seal durability design verification examination of wing tank is determined
Proved recipe case；Testpieces is adding in the Y-direction load for loading No. 4 No. 1 position, No. 2 positions of load, No. 3 positions of load, load positions, testpieces
No. 5 positions (at flap-track support sliding rail) X-direction, Y-direction load are carried, testpieces fixing end is connected by screw bolts mode and is fixed on
Load column, it is as shown in Table 2 below according to aircraft military service operating condition establishment test load spectrum.
2 test load of table spectrum
Before starting test and during test, water-filling pressurising need to be carried out to testpieces.Method are as follows: installed on testpieces
Pressure gauge and safety valve；95% tap water is filled to testpieces inside according to test requirements document, and adds red staining agent in water,
Testpieces examines area surfaces spraying imaging agent (white)；Pressurising observing and controlling testing stand is connected, 12kPa pressure value is set.Start
Pressurising, after pressure stabilisation to start to test, after the test, pressure release simultaneously closes pressurising equipment.
Test procedure can be divided into four steps, be respectively as follows: the preceding preparation of test, debugging test, test trial operation, is formal tired
Labor test.Wherein test trial operation includes static(al) prerun test and tired prerun test.
1) prepare before test: before on-test, carrying out some preparations, inspection debugging and correction comprising equipment,
Testpieces installation, the installation of testpieces measuring system, testpieces are surveyed pressure, testpieces water filling and leak test and are prepared.
2) single-point debugging debugging test: is carried out respectively to 6 load pressurized struts of test.
3) it tests trial operation: carrying out 30% static(al) prerun test, 100% slow test, 50% fatigue respectively to testpieces
Prerun test and 100% tired prerun test.
4) formal fatigue test: formal fatigue test is carried out according to charter specified load spectrum.
D) test result
Carry out fuel tank simulating piece seal durability verification test, is adopted in fuel tank examination position key structure position layout data
Collect foil gauge, statisticallys analyze verification test result；Comparative analysis finite element modelling result and slow test under different loads spectrum
As a result, modification and perfection finite element model parameter, it is ensured that two resultant errors are no more than 5%, form final finite element model.
E) conclusion
Component-level simulation test piece design and verification method based on FEM Simulation, has carried out fuel tank simulation test piece
Finite Element Simulation Analysis and fuel tank simulation test piece seal durability verification test, from structure type, intensity and toughness, material category
Property, sealing technology etc. demonstrate fuel tank seal durability.Finite Element Simulation Analysis is consistent with test structure, verifies the fuel tank flap
Wing slip rail and the improved validity of web connecting portion structure.
Claims (6)
1. the component-level simulation test piece design and verification method based on FEM Simulation, which is characterized in that this method be
Simplified on the basis of former aircaft configuration, retain aircraft examination position real structure, it is ensured that simulation test piece examine position with
Aircraft original structure examines structure type, loaded feature, manufacturing process and the sealing technology at position consistent with aircaft configuration；It presses simultaneously
Simplify simulation test piece other structures according to aircraft original structure force path and primary structure form, it is ensured that simulation test piece can simulate
The various operating condition flowering structure internal environment situations of change of aircraft；Using finite element analysis software and calculation optimization simulation test piece mould
Type.
2. the component-level simulation test piece design and verification method based on FEM Simulation as described in claim 1, special
Sign is, includes the following steps:
Step 1: examining position performance indicator to choose the overall structure that aircraft needs to examine according to aircraft, establish aircraft and need to examine
Integrally-built finite element model and carry out finite element method (fem) analysis；
Step 2: key structure evaluation is formulated in the overall structure for needing to examine for aircraft according to the result of finite element method (fem) analysis
Criterion；
Step 3: needing the overall structure examined to carry out simplifying design in aircraft according to criterion；
Step 4: according to simplifying design forming member grade testpieces finite element model and carrying out finite element method (fem) analysis, by component-level
Testpieces examines the examination position finite element method (fem) analysis result of aircraft obtained in position result of finite element and step 1 to carry out
Comparative analysis processing experiment part and carries out test if comparative analysis result meets criterion, if being unsatisfactory for criterion improves component
Grade testpieces finite element model.
3. the component-level simulation test piece design and verification method based on FEM Simulation as claimed in claim 2, special
Sign is that the process of step 2 is as follows: finite element method (fem) analysis aircraft different operating conditions get off the plane needs examine it is integrally-built
Ess-strain and deformation specify integrally-built loaded feature, force path, ess-strain that aircraft needs to examine, are
Key structure evaluation provides foundation in the overall structure that aircraft needs to examine, and formulates key structure evaluation criterion.
4. the component-level simulation test piece design and verification method based on FEM Simulation as claimed in claim 2, special
Sign is that the process of step 3 is as follows: for non-key structure, structure carried out if meeting criterion requirement to simplify design,
Retain technique；For key structure position, original structure form and technique are retained if meeting criterion requirement.
5. the component-level simulation test piece design and verification method based on FEM Simulation as claimed in claim 4, special
Sign is that the establishment process of component-level testpieces finite element model is as follows in step 4: considering to manufacture and design condition element for non-pass
The forming member grade simulation test piece CATIA model after simplifying design combination of bond structure and key structure position, has primarily determined
It limits the loading method of meta-model, magnitude of load, clamped mode and obtains component-level testpieces after carrying out FEM calculation and analysis
Finite element model.
6. the component-level simulation test piece design and verification method based on FEM Simulation as claimed in claim 4, special
Sign is that component-level testpieces examination position result of finite element and aircraft examine position finite element method (fem) analysis in step 4
First according to component-level simulation test piece analysis model for finite element situation when Comparative result analysis result meets criterion, examine simultaneously
Consider craftsmanship, accessibility, the design principle of repairability, modification and perfection component-level simulation test piece CATIA designs processing model, shape
Drawing is processed at component-level simulation test piece；Then according to component-level simulation test piece manuscript paper conversion manufacture component-level simulation
Testpieces；And according to component-level simulation test piece finite element analysis model, formulates component-level simulation test piece testing program and open
Exhibition test；Then comparative test and component-level simulation test piece result of finite element provide criterion requirement, if aircraft examination portion
Position stress deformation meets criterion and requires then to obtain examination position conclusion；Detail modifications component-level is simulated if being unsatisfactory for criterion and requiring
Testpieces model re-starts FEM calculation.
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| CN110239742A (en) * | 2019-05-29 | 2019-09-17 | 陕西飞机工业（集团）有限公司 | A method of for two model aircraft combination slow tests |
| CN110795871A (en) * | 2019-09-29 | 2020-02-14 | 中航通飞研究院有限公司 | Method for calculating and testing strength of bottom frame of amphibious aircraft ship |
| CN111122346A (en) * | 2019-12-24 | 2020-05-08 | 中国航空工业集团公司西安飞机设计研究所 | Test load processing method for main structure of airfoil |
| CN112733267A (en) * | 2020-12-30 | 2021-04-30 | 中国特种飞行器研究所 | Design method and device for advanced reinforced structural component-level test piece |
| CN113297709A (en) * | 2021-06-29 | 2021-08-24 | 北京微纳星空科技有限公司 | Modeling method, device and equipment of test piece, storage medium and test piece |
| CN113673023A (en) * | 2020-05-15 | 2021-11-19 | 中航西飞民用飞机有限责任公司 | Method for determining fatigue load spectrum of complex block structure of airplane |
| CN115270335A (en) * | 2022-07-29 | 2022-11-01 | 中国航发沈阳发动机研究所 | Method for designing load of strength test of upper guide rail beam of thrust reverser |
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| CN110795871A (en) * | 2019-09-29 | 2020-02-14 | 中航通飞研究院有限公司 | Method for calculating and testing strength of bottom frame of amphibious aircraft ship |
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| CN113297709A (en) * | 2021-06-29 | 2021-08-24 | 北京微纳星空科技有限公司 | Modeling method, device and equipment of test piece, storage medium and test piece |
| CN115270335A (en) * | 2022-07-29 | 2022-11-01 | 中国航发沈阳发动机研究所 | Method for designing load of strength test of upper guide rail beam of thrust reverser |
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