CN107977488A - Static strength check method and device - Google Patents
Static strength check method and device Download PDFInfo
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- CN107977488A CN107977488A CN201711086272.8A CN201711086272A CN107977488A CN 107977488 A CN107977488 A CN 107977488A CN 201711086272 A CN201711086272 A CN 201711086272A CN 107977488 A CN107977488 A CN 107977488A
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Abstract
The invention discloses a kind of static strength check method and device.Wherein, this method includes：Component units corresponding with the structure are built according to the structure of aircraft to be checked, wherein, the component units include same category of one or more elements；Obtain the corresponding property parameters of each element and check parameter, wherein, it is described check parameter be used to characterizing need described in the pre-set level that reaches of aircraft to be checked；Property parameters and the corresponding strength margin checked parameter and determine each element, the strength margin according to each element is determined are used to characterize whether the element meets the pre-set level.The present invention solves the static strength manually carried out in the prior art to aircraft under keypoint part or serious operating mode and checks, and causes to check incomplete technical problem.
Description
Technical field
The present invention relates to aircraft static strength to check field, in particular to a kind of static strength check method and device.
Background technology
It is the necessary working link examined to aircraft bearing capacity and safety of structure that aircraft static strength, which is checked, aircraft
Static strength, which checks work, can be related to different failure criterias, different operating mode and structure, if complete to checking task
Portion considers these three dimensions, then it is the relation that three quantity are multiplied that number is checked in analysis, and the quantity of the operating mode of aircraft is few then several
Hundredth, at most thousands of, structure (unit) is even more ten hundreds of, and so more checking tasks, is not tired on simple number
Product and repetition, but each analysis task has its specific structure geometrical property/material property/section characteristic/connection performance, load
Lotus.But in the prior art still without it is a kind of can by advanced method and means, still can only apply traditional selection emphasis
Position carries out the mode of check analysis in the case of extreme operating condition, but this selection just proposes high work to checking engineer
The requirement of journey experience and technical merit, often produces the situation of leakage choosing or wrong choosing, and work efficiency is relatively low.
Checked for manually the static strength under keypoint part or serious operating mode is carried out to aircraft in the prior art, cause to check
Incomplete problem, not yet proposes effective solution at present.
The content of the invention
It is manually right in the prior art at least to solve an embodiment of the present invention provides a kind of static strength check method and device
The static strength that aircraft is carried out under keypoint part or serious operating mode is checked, and causes to check incomplete technical problem.
One side according to embodiments of the present invention, there is provided a kind of static strength check method, including：Fly according to waiting to check
The structure of machine builds component units corresponding with structure, wherein, component units include same category of one or more compositions will
Element；Obtain the corresponding property parameters of each element and check parameter, wherein, check parameter needs to wait to check to fly for characterization
The pre-set level that machine reaches；Property parameters and corresponding check parameter according to each element is determined determine that each composition will
The strength margin of element, strength margin are used to characterize whether element meets pre-set level.
Further, the generalized model of aircraft to be checked is obtained；Equivalent in generalized model is split, obtains treating school
The element of core aircraft；The element of same type is merged, obtains the component units of aircraft.
Further, the pre-set level of each element is obtained；The school of each element is determined according to pre-set level
Nuclear parameter.
Further, if the property parameters of element are more than corresponding check parameter, it is determined that element meets
Pre-set level；If the property parameters of element are less than corresponding check parameter, it is determined that element is unsatisfactory for default finger
Mark.
Further, if the difference of the property parameters of element and check parameter is more than preset value, group is redefined
Into key element.
Further, the component units of aircraft to be checked include：Bar unit, beam element, flat unit, bent plate unit, group
Close unit and typical structure unit.
Another aspect according to embodiments of the present invention, additionally provides a kind of static strength capacity checking device, including：Build module,
Component units corresponding with structure are built for the structure according to aircraft to be checked, wherein, component units include same category of
One or more elements；Acquisition module, for obtaining the corresponding property parameters of each element and checking parameter, its
In, check parameter needs the pre-set level that aircraft to be checked reaches for characterizing；Determining module, for according to definite each composition
The property parameters of key element and the corresponding strength margin checked parameter and determine each element, strength margin, which is used to characterize, to be formed
Whether key element meets pre-set level.
Further, acquisition module includes：Acquisition submodule, for obtaining the generalized model of aircraft to be checked；Split son
Module, for the equivalent in generalized model to be split, obtains the element of aircraft to be checked；Submodule is combined, is used for
The element of same type is merged, obtains the component units of aircraft.
Another aspect according to embodiments of the present invention, additionally provides a kind of storage medium, it is characterised in that storage medium bag
The program of storage is included, wherein, equipment performs the static strength school of above-mentioned any one where controlling storage medium when program is run
Kernel method.
Another aspect according to embodiments of the present invention, additionally provides a kind of processor, it is characterised in that processor is used to transport
Line program, wherein, program performs the static strength check method of above-mentioned any one when running.
Component units corresponding with structure are obtained according to the structure of aircraft to be checked in embodiments of the present invention, are obtained each
The corresponding property parameters of element and check parameter, join according to the property parameters and corresponding check that determine each element
Number determines the strength margin of each element.Such scheme carries out static strength check by the component units of aircraft to aircraft,
The mass that work is checked so as to fulfill aircraft static strength performs, greatly improve check work efficiency while, avoid pair
The leakage choosing of structure position checked is needed, so that accomplished that precision analysis is checked and non-artificial screening by rule of thumb judges,
So as to solve the static strength check in the prior art manually carried out aircraft under keypoint part or serious operating mode, cause to check not
Comprehensive technical problem.
Brief description of the drawings
Attached drawing described herein is used for providing a further understanding of the present invention, forms the part of the application, this hair
Bright schematic description and description is used to explain the present invention, does not form inappropriate limitation of the present invention.In the accompanying drawings：
Fig. 1 is the flow chart of static strength check method according to embodiments of the present invention；
Fig. 2 a are the interfaces of the input property parameters of certain flat unit in a kind of importing fuselage according to the embodiment of the present application
Schematic diagram；
Fig. 2 b are the property parameters according to a kind of the importing fuselage assembled unit and its element of the embodiment of the present application
Interface schematic diagram；
Fig. 2 c are a kind of schematic diagrames to the interface for being analyzed intensity according to embodiments of the present invention；And
Fig. 3 is a kind of schematic diagram of static strength device according to embodiments of the present invention.
Embodiment
In order to make those skilled in the art more fully understand the present invention program, below in conjunction with the embodiment of the present invention
Attached drawing, is clearly and completely described the technical solution in the embodiment of the present invention, it is clear that described embodiment is only
The embodiment of a part of the invention, instead of all the embodiments.Based on the embodiments of the present invention, ordinary skill people
Member's all other embodiments obtained without making creative work, should all belong to the model that the present invention protects
Enclose.
It should be noted that term " first " in description and claims of this specification and above-mentioned attached drawing, "
Two " etc. be for distinguishing similar object, without for describing specific order or precedence.It should be appreciated that so use
Data can exchange in the appropriate case, so as to the embodiment of the present invention described herein can with except illustrating herein or
Order beyond those of description is implemented.In addition, term " comprising " and " having " and their any deformation, it is intended that cover
Cover it is non-exclusive include, be not necessarily limited to for example, containing the process of series of steps or unit, method, system, product or equipment
Those steps or unit clearly listed, but may include not list clearly or for these processes, method, product
Or the intrinsic other steps of equipment or unit.
Embodiment 1
According to embodiments of the present invention, there is provided a kind of embodiment of the method for static strength check method, it is necessary to explanation,
The step of flow of attached drawing illustrates can perform in the computer system of such as a group of computer-executable instructions, also,
, in some cases, can be with different from shown in order execution herein although showing logical order in flow charts
The step of going out or describing.
Fig. 1 is the flow chart of static strength check method according to embodiments of the present invention, as shown in Figure 1, this method is included such as
Lower step：
Step S102, component units corresponding with structure are built according to the structure of aircraft to be checked, wherein, component units bag
Include same category of one or more elements.
The complex equipment that aircraft is made of tens thousand of a parts, such as common fixed wing aircraft are by fuselage, wing, tail
Major complicated component composition such as the wing, dynamic aerofoil, undercarriage, system, and these complicated architectures be by bar, plate, beam,
Each first component such as the opening members such as frame, rib, hatch door, connector, connector, typical parts is formed, point of its bearing capacity and strength margin
Analysis, which calculates, is that item is complicated and huge work, tends to take up more than the 70% of aircraft structure strength design work, and to aircraft
The most basic and most important examination link of ultimate bearing capacity and whole service life security.Above-mentioned steps are in order to aircraft
All parts carry out bulk static strength and check, it is therefore desirable to obtain the component units of aircraft.For different structure class
The aircraft of type, may have different component units, it is therefore desirable to obtain according to the structure of aircraft.
Specifically, each component units include the other one or more elements of same class, above-mentioned element
For characterizing the specific component of aircraft, component units to element by being classified to obtain.Multiple dimensions pair can be passed through
The element of aircraft classify, such as：It is used as using the species of material as the dimension of classification, with element
The dimension of classification, or the dimension using the position residing for element as classification.
Step S104, obtains the corresponding property parameters of each element and checks parameter, wherein, check parameter and be used for table
Sign needs the pre-set level that aircraft to be checked reaches.
Specifically, above-mentioned property parameters are used to characterize the intrinsic parameter of element in itself, namely the work of element
Make stress, i.e., the external applied load suffered by structure produces the characterization or equivalent of effect.When determining the composition structure of aircraft, aircraft
Element working stress i.e. be determined.In a kind of optional embodiment, above-mentioned property parameters can include unit pair
The geometric attribute answered, section attribute, material properties, connection attribute parameter, Standard property parameters etc. and static strength are checked point
The relevant characterisitic parameter of analysis itself.
Above-mentioned check parameter namely allowable stress, the allowable stress are used for the index for characterizing aircaft configuration bearing capacity, with
The correlation such as structure selection, structure characteristic in itself and type of attachment.
The corresponding property parameters of each element and check parameter obtained in above-mentioned steps can be that batch imports
In the application program checked for static strength, which can be according to the corresponding composition member of the mark of component matching
Element.
Step S106, determines that each composition will according to the property parameters and corresponding check parameter that determine each element
The strength margin of element, strength margin are used to characterize whether element meets pre-set level.
From the foregoing, it will be observed that the above embodiments of the present application obtain composition list corresponding with structure according to the structure of aircraft to be checked
Member, obtain the corresponding property parameters of each element and check parameter, according to determine each element property parameters and
The corresponding strength margin checked parameter and determine each element.Such scheme carries out aircraft by the component units of aircraft
Static strength is checked, and the mass that work is checked so as to fulfill aircraft static strength performs, and the same of work efficiency is checked greatly improving
When, avoid and the leakage of structure position that needs are checked selected so that accomplished precision analysis to check and it is non-artificial by rule of thumb
Screening judge, so as to solve the static strength school manually carried out in the prior art to aircraft under keypoint part or serious operating mode
Core, causes to check incomplete technical problem.
Optionally, according to the above embodiments of the present application, composition corresponding with structure is obtained according to the structure of aircraft to be checked
Unit, including：
Step S1021, obtains the generalized model of aircraft to be checked.
Specifically, such scheme is to the generalized model of aircraft by carrying out static strength check, to realize to the quiet strong of aircraft
Degree is checked, the direct equivalent of generalized model, that is, actual airplane, and its essence is the relevant all designs point of these gongwu objects
The tissue set of key element is analysed, and most directly reflect " benchmark model " of these engineering objects, it will be included in engineering object
Each expert data carries out the processing and management of " unified model ", its corresponding backstage is also all kinds of logical under unified model theory
Bottom data structure, base class component/control, general function module and unified database architecture.
Step S1023, the equivalent in generalized model is split, and obtains the element of aircraft to be checked.
Since the generalized model of aircraft is the equivalent of actual airplane, to the difference of generalized model equivalent to aircraft
Each parts split.
Step S1025, the element of same type is merged, and obtains the component units of aircraft.
As a kind of optional embodiment, the component units of aircraft to be checked include：Bar unit, beam element, flat unit,
Bent plate unit, assembled unit and typical structure unit.
Fig. 2 a are the interfaces of the input property parameters of certain flat unit in a kind of importing fuselage according to the embodiment of the present application
Schematic diagram, with reference to shown in Fig. 2 a, what is currently inputted is the element that unit name (identifying) is 7975, which has multiple sections
Point, can import the positional information of each node in the information of the plate (as shown in the nodal information in figure), to determine the plate
Geometry, then determined according to features such as the selections of the plate and import the parameter information of the plate.
Fig. 2 b are the property parameters according to a kind of the importing fuselage assembled unit and its element of the embodiment of the present application
Interface schematic diagram, with reference to shown in Fig. 2 b, assembled unit diagrammatically show form the assembled unit subelement (i.e. composition will
Element) be schematic diagram, and import the subelement information of the assembled unit, the node for also having imported each subelement is entirely being checked
During nodal information.In this example, assembled unit is respectively by left covering, right covering, stringer, its corresponding mark
837th, 840,836, each unit has multiple nodes, and each node has the numbering during whole check, with stringer
Exemplified by, the 1 corresponding node serial number of node of stringer is 286, and 2 corresponding node serial number of node is 463, and described in nodal information
The specific coordinate of the node of each numbering, therefore can pass through the geological information of the node serial number determination subelement of subelement.
Optionally, according to the above embodiments of the present application, check parameter corresponding with each element is obtained, including：
Step S1041, obtains the pre-set level of each element.
Step S1043, the check parameter of each element is determined according to pre-set level.
Specifically, above-mentioned check parameter can include load-up condition and boundary condition, answering for limit member calculating is mainly included
The establishment of coefficient is supported in the importing and processing of power/power/strain result, structure boundary and end.Can use to corresponding units into
The processing of row mass load assignment.
Optionally, according to the above embodiments of the present application, according to the property parameters and corresponding school for determining each element
Nuclear parameter determines the strength margin of each element, including：
Step S1061, if the property parameters of element are more than corresponding check parameter, it is determined that element meets
Pre-set level.
Step S1063, if the property parameters of element are less than corresponding check parameter, it is determined that element is discontented with
Sufficient pre-set level.
In a kind of optional embodiment, the strength margin of each key element can be calculated by equation below：Wherein, MS is used to characterize strength margin, σaFor characterizing allowable stress, that is, check parameter, σwFor work in table
Make stress, i.e. property parameters.When MS is more than 0, i.e., the property parameters of element are more than corresponding check parameter, composition is determined
Key element meets to check the corresponding index of parameter；When MS is less than 0, i.e. the property parameters of element are less than corresponding check parameter
When, determine that element is unsatisfactory for checking the corresponding index of parameter.It is unsatisfactory for checking the corresponding finger of parameter in definite element
In the case of target, structural strengthening processing can be carried out to former element.
Optionally, according to the above embodiments of the present application, if the property parameters of element are more than corresponding check parameter,
The above method further includes：If the property parameters of element and the difference of check parameter are more than preset value, composition is redefined
Key element.
Still in the above-described embodiments, if the property parameters of element are more than corresponding check parameter, but more than check
The degree of parameter is larger, namely the MS in above-mentioned formula larger, then it needs to be determined that the material of element, structure, or original is tied
Structure carries out loss of weight processing.
In the following, the above method is illustrated exemplified by carrying out static strength check to the fuselage of certain aircraft.
In a kind of optional embodiment, by taking certain aircraft middle fuselage as an example, first, the component units of fuselage are built.Table one
For illustrating the component units of the airframe, airframe structure mainly include fuselage skin, stringer, common frame, reinforcing frame, beam,
The structure compositions such as floor, doorway frame, jointing, the present invention require according to the mechanical essence of strength check, unit are criticized
Quantify to sort out and comb, be attributed to：Bar, plate, beam, assembled unit, typical structure, as shown in Table 1：
Table one
Then the property parameters of each element in component units are write, include material properties, section attribute, connector
Attribute, structure combination and mount attribute parameter etc..These parameters can be cured in the form of database, in strength check flow
In directly mass be incorporated into fixed structure objects and unit, that is, complete mass characteristic assignment.Specifically need assignment
Property parameters can be as shown in Table 2.
Then carry out checking the write-in of parameter, checking parameter includes load and boundary condition, mainly includes limit member and calculates
Stress/power/strain result importing and processing, the establishment of coefficient is supported in structure boundary and end.The present invention is using to corresponding
Unit carries out the processing of mass load assignment.
Further, it is bulk to be analyzed according to default algorithm, obtain strength margin：Completing above-mentioned composition
After unit, property parameters, the mass of check parameter are handled, all units that carry out static strength check complete intensity school
The setting of all input parameters of core.Then select the mass automated execution that corresponding failure criteria carries out multiple analyses, i.e., it is complete
Into all units, all operating modes, all analyses calculating.Specifically can as shown in Figure 2 c, Fig. 2 c show a kind of to by intensity
The interface analyzed, with reference to shown in Fig. 2 c, the analysis type in left side includes multiple component units in interface, and each composition is single
The submenu of member includes element, when element in choosing, the various operating modes checked to the element occurs,
The selected operating mode type for needing to check, and the constraints this time checked in middle column input, the rightmost side " operating mode " this column are used
In the check parameter that user's static strength of selection is checked, also correspond to check index, for determining whether element can expire
The requirement for the operating mode that foot is currently chosen.
Table two
Finally, analysis result can also be post-processed, generation mass performs whole analyses completed, whole operating modes, complete
The result form of portion's unit, screens the inadequate position of the strength margin of static strength check, strength check concern in result form
Position and other structures design need carry out intensity, the position to be examined of rigidity and stability, automatically generate accurately (in
Fuselage) static strength check report.
Embodiment 2
According to embodiments of the present invention, there is provided a kind of embodiment of the method for static strength check method, Fig. 3 is according to the present invention
A kind of schematic diagram of static strength device of embodiment, with reference to shown in Fig. 3, which includes：
Module 30 is built, component units corresponding with structure are built for the structure according to aircraft to be checked, wherein, composition
Unit includes same category of one or more elements.
Acquisition module 32, for obtaining the corresponding property parameters of each element and checking parameter, wherein, check parameter
For characterizing the pre-set level for needing aircraft to be checked to reach.
Determining module 34, it is each for being determined according to the property parameters and corresponding check parameter that determine each element
The strength margin of element, strength margin are used to characterize whether element meets pre-set level.
Optionally, included according to the above embodiments of the present application, above-mentioned first acquisition module：
Acquisition submodule, for obtaining the generalized model of aircraft to be checked.
Submodule is split, for the equivalent in generalized model to be split, obtains the element of aircraft to be checked.
Submodule is combined, for the element of same type to be merged, obtains the component units of aircraft.
Embodiment 3
According to embodiments of the present invention, there is provided a kind of storage medium, storage medium include the program of storage, wherein, in journey
Equipment performs the static strength check method of any one in embodiment 1 where controlling storage medium during sort run.
Embodiment 4
According to embodiments of the present invention, there is provided a kind of processor, processor are used for operation program, wherein, when program is run
Perform the static strength check method of any one in embodiment 1.
The embodiments of the present invention are for illustration only, do not represent the quality of embodiment.
In the above embodiment of the present invention, the description to each embodiment all emphasizes particularly on different fields, and does not have in some embodiment
The part of detailed description, may refer to the associated description of other embodiment.
In several embodiments provided herein, it should be understood that disclosed technology contents, can pass through others
Mode is realized.Wherein, device embodiment described above is only schematical, such as the division of the unit, Ke Yiwei
A kind of division of logic function, can there is an other dividing mode when actually realizing, for example, multiple units or component can combine or
Person is desirably integrated into another system, or some features can be ignored, or does not perform.Another, shown or discussed is mutual
Between coupling, direct-coupling or communication connection can be INDIRECT COUPLING or communication link by some interfaces, unit or module
Connect, can be electrical or other forms.
The unit illustrated as separating component may or may not be physically separate, be shown as unit
The component shown may or may not be physical location, you can with positioned at a place, or can also be distributed to multiple
On unit.Some or all of unit therein can be selected to realize the purpose of this embodiment scheme according to the actual needs.
In addition, each functional unit in each embodiment of the present invention can be integrated in a processing unit, can also
That unit is individually physically present, can also two or more units integrate in a unit.Above-mentioned integrated list
Member can both be realized in the form of hardware, can also be realized in the form of SFU software functional unit.
If the integrated unit is realized in the form of SFU software functional unit and is used as independent production marketing or use
When, it can be stored in a computer read/write memory medium.Based on such understanding, technical scheme is substantially
The part to contribute in other words to the prior art or all or part of the technical solution can be in the form of software products
Embody, which is stored in a storage medium, including some instructions are used so that a computer
Equipment (can be personal computer, server or network equipment etc.) perform each embodiment the method for the present invention whole or
Part steps.And foregoing storage medium includes：USB flash disk, read-only storage (ROM, Read-Only Memory), arbitrary access are deposited
Reservoir (RAM, Random Access Memory), mobile hard disk, magnetic disc or CD etc. are various can be with store program codes
Medium.
The above is only the preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
For member, various improvements and modifications may be made without departing from the principle of the present invention, these improvements and modifications also should
It is considered as protection scope of the present invention.
Claims (10)
- A kind of 1. static strength check method, it is characterised in that including：Component units corresponding with the structure are built according to the structure of aircraft to be checked, wherein, the component units include same A kind of other one or more elements；Obtain the corresponding property parameters of each element and check parameter, wherein, the check parameter, which is used to characterize, to be needed The pre-set level for wanting the aircraft to be checked to reach；Property parameters and corresponding check parameter according to each element is determined determine each element Strength margin, the strength margin are used to characterize whether the element meets the pre-set level.
- 2. according to the method described in claim 1, it is characterized in that, obtained and the structure pair according to the structure of aircraft to be checked The component units answered, including：The generalized model of aircraft to be checked described in acquisition；Equivalent in the generalized model is split, obtains the element of the aircraft to be checked；The element of same type is merged, obtains the component units of the aircraft.
- 3. according to the method described in claim 1, join it is characterized in that, obtaining check corresponding with each element Number, including：Obtain the pre-set level of each element；The check parameter of each element is determined according to the pre-set level.
- 4. according to the method described in claim 3, it is characterized in that, according to the property parameters for determining each element and The corresponding strength margin checked parameter and determine each element, including：If the property parameters of the element are more than corresponding check parameter, it is determined that the element meets described pre- If index；If the property parameters of the element are less than corresponding check parameter, it is determined that the element is unsatisfactory for described Pre-set level.
- 5. if according to the method described in claim 4, it is characterized in that, the property parameters of the element are more than corresponding Parameter is checked, the method further includes：If the property parameters of the element and the difference for checking parameter are more than default Value, then redefine the element.
- 6. method as claimed in any of claims 1 to 5, it is characterised in that the composition list of the aircraft to be checked Member includes：Bar unit, beam element, flat unit, bent plate unit, assembled unit and typical structure unit.
- A kind of 7. static strength capacity checking device, it is characterised in that including：Module is built, component units corresponding with the structure are built for the structure according to aircraft to be checked, wherein, described group Include same category of one or more elements into unit；Acquisition module, for obtaining the corresponding property parameters of each element and checking parameter, wherein, it is described to check ginseng The pre-set level that number reaches for aircraft to be checked described in characterization needs；Determining module, for determining each institute according to the property parameters and corresponding check parameter that determine each element The strength margin of element is stated, the strength margin is used to characterize whether the element meets the pre-set level.
- 8. device according to claim 7, it is characterised in that the acquisition module includes：Acquisition submodule, for obtaining the generalized model of the aircraft to be checked；Submodule is split, for the equivalent in the generalized model to be split, the composition for obtaining the aircraft to be checked will Element；Submodule is combined, for the element of same type to be merged, obtains the component units of the aircraft.
- A kind of 9. storage medium, it is characterised in that the storage medium includes the program of storage, wherein, run in described program When control the storage medium where static strength check method in equipment perform claim requirement 1 to 6 described in any one.
- A kind of 10. processor, it is characterised in that the processor is used for operation program, wherein, right of execution when described program is run Profit requires the static strength check method described in any one in 1 to 6.
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| CN201711086272.8A CN107977488B (en) | 2017-11-07 | 2017-11-07 | Static strength checking method and device |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110940507A (en) * | 2019-12-16 | 2020-03-31 | 宁波奥克斯电气股份有限公司 | Motor frame static strength analysis method and system |
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