CN107016181A - A kind of cabin door structure static strength computational methods - Google Patents
A kind of cabin door structure static strength computational methods Download PDFInfo
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- CN107016181A CN107016181A CN201710200405.3A CN201710200405A CN107016181A CN 107016181 A CN107016181 A CN 107016181A CN 201710200405 A CN201710200405 A CN 201710200405A CN 107016181 A CN107016181 A CN 107016181A
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
- G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
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- G—PHYSICS
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- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2111/00—Details relating to CAD techniques
- G06F2111/04—Constraint-based CAD
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- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2113/00—Details relating to the application field
- G06F2113/28—Fuselage, exterior or interior
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Abstract
The present invention relates to a kind of cabin door structure static strength computational methods, belong to aircraft structure strength design field.The present invention carries out static strength calculating based on linear contact analysis method, initially sets up the FEM model of cabin door structure；And according to cabin door structure and the matching relationship of airframe structure, determine boundary condition；Afterwards, the load working condition that the constraints of cabin door structure is applicable is determined according to the boundary condition, finally carries out the constraint of linear contact analysis model, set up constraint control file, it is final to calculate the result for obtaining hatch door linear contact constraint reaction.The result of calculation and the result of calculation of nonlinear analysis analyzed using linear contact are compared, linear contact analysis of the present invention can be more convenient, fast and accurately calculate cabin door structure static strength.
Description
Technical field
The invention belongs to aircraft structure strength design field, more particularly to a kind of cabin door structure static strength computational methods.
Background technology
Cabin door structure is moving component special on aircraft, for airtight hatch door, is primarily subjected to positive and negative pressure load, pneumatic
Load and inertial load etc..Because hatch door and fuselage have more contact relation, this requires the Strength co-mputation in cabin door structure
During, it is necessary to determine the edge-restraint condition of hatch door according to load condition.Under boost conditions, airtight load is primarily subjected to,
It is delivered to by fixed detent joint on airframe structure；In the case of non pressurized, inertial load is primarily subjected to, by door-locking claw, is led
It is delivered to groove etc. on airframe structure.
For cabin door structure, on the one hand because different load conditions has different load transfer paths, if using
Linear Static Calculation is, it is necessary to define single constraints to every kind of load condition, and workload is big, and it is real to be difficult to simulation
Contact situation；On the other hand because hatch door belongs to the redundant structure of Multi-contact, if being difficult to draw standard using engineering method
True result.
Although can solve contact problems using gap element in engineering, gap element needs to use non-linear
Sequence is solved, while needing to estimate the rigidity of gap element used, causes the consuming time longer, especially for various working
Calculate, waste time and energy, this method and inadvisable at the beginning of conceptual design.Therefore need to set up a kind of new computational methods, side
Just hatch door static strength calculating, is quickly and accurately carried out.
The content of the invention
The invention provides a kind of cabin door structure static strength computational methods, static strength is carried out based on linear contact analysis method
Calculate, in order to improve the computational efficiency of the Multi-contact problem comprising various working.
Cabin door structure static strength computational methods of the present invention, are mainly included the following steps that:
S1, the FEM model for setting up cabin door structure；
S2, the matching relationship according to cabin door structure and airframe structure, determine boundary condition；
S3, the load working condition that the constraints of cabin door structure is applicable, the load work are determined according to the boundary condition
Condition includes airtight load working condition and inertial load operating mode；
S4, the constraint for carrying out linear contact analysis model, set up constraint control file, calculate the constraint of hatch door linear contact anti-
The result of power.
Preferably, when setting up the FEM model, the hatch door load component of selection comprise at least covering, longeron,
Crossbeam, detent joint, directive wheel and lock bolt.
In such scheme preferably, when setting up the FEM model, when simulating the coupling stiffness of detent joint, extremely
Include latch rigidity and the rigidity of detent joint auricle less.
In such scheme preferably, the boundary condition includes contiguity constraint, the covering of detent joint and airframe structure
With the contiguity constraint of airframe structure, the contiguity constraint of directive wheel and fuselage doorframe and the airtight load with inertial load about
Beam.
In such scheme preferably, the step S4 further comprises setting up constraint control file, and is transported by NASTRAN
Calculate and debug, solve sequence 101.
The present invention sets up nonlinear analysis models simultaneously, using gap element GAP simulating contact relations, submits NASTRAN
Nonlinear analysis is carried out, sequence 106 is solved, is 2 times of linear contact calculating by the statistics calculating time used.Two kinds of calculating moulds
Under formula, the positive lower detent joint constraint reaction distribution of compressive load effect is basically identical.Therefore can be more using linear contact analysis method
Easily and accurately calculate cabin door structure static strength.
Advantages of the present invention and effect include：
1) contact performance for the method energy accurate simulation cabin door structure that the present invention is provided, meets the calculating of cabin door structure static strength
It is required that.
2) compared with NONLINEAR CALCULATION, calculated gap element stiffness data are not spent, and can respectively be solved with multi-state,
Significantly shorten calculating cycle, reduce design cost.
3) contact that the method that the present invention is provided can be completed under linear analysis is calculated, simple to operate, realizes calculating side
The standardization of method and flow, it is to avoid the result error that different research staff occur when calculating.
Brief description of the drawings
Fig. 1 is the flow chart of a preferred embodiment of cabin door structure static strength computational methods of the present invention.
Embodiment
To make the purpose, technical scheme and advantage of the invention implemented clearer, below in conjunction with the embodiment of the present invention
Accompanying drawing, the technical scheme 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
A part of embodiment, rather than whole embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to uses
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment that member is obtained under the premise of creative work is not made, belongs to the scope of protection of the invention.Under
Embodiments of the invention are described in detail with reference to accompanying drawing for face.
In the description of the invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outer " is based on accompanying drawing institutes
The orientation or position relationship shown, is for only for ease of the description present invention and simplifies description, rather than indicate or imply signified dress
Put or element there must be specific orientation, with specific azimuth configuration and operation, therefore it is not intended that to present invention protection
The limitation of scope.
The present invention is described in further details below by embodiment.
The invention provides a kind of cabin door structure static strength computational methods, carried out based on linear contact analysis method quiet strong
Degree is calculated, in order to improve the computational efficiency of the Multi-contact problem comprising various working.
Cabin door structure static strength computational methods of the present invention, are mainly included the following steps that:
S1, the FEM model for setting up cabin door structure；
S2, the matching relationship according to cabin door structure and airframe structure, determine boundary condition；
S3, the load working condition that the constraints of cabin door structure is applicable, the load work are determined according to the boundary condition
Condition includes airtight load working condition and inertial load operating mode；
S4, the constraint for carrying out linear contact analysis model, set up constraint control file, calculate the constraint of hatch door linear contact anti-
The result of power.
The present embodiment is by taking civil aircraft hatch door as an example, and the contact for carrying out cabin door structure static strength is calculated, and implementation process is as follows：
First, the main load component of hatch door is chosen, should be included：Covering, longeron, crossbeam, detent joint, directive wheel and lock
Door bolt, sets up cabin door structure FEM model, for the contact situation at each position of accurate simulation cabin door structure, adjacent longeron and horizontal stroke
Covering piecemeal between beam is no less than 4 × 4.
When FEM model simplifies, detent joint is reduced to rigid unit RBE2, the CBUSH units of the connection with fuselage
To simulate.For accurate simulation coupling stiffness, it is necessary to while considering the rigidity of latch and the rigidity of detent joint auricle.
Under load F effects, latch and detent joint total deformation are：δ=δ1+δ2。
δ1Deformed for latch, latch axial direction stand under load：It is deformed intoWherein, F is Tensile or Compressive Loading, L1For stop
Sell length, E1For latch modulus of elasticity, A1For latch cross-sectional area；
Similarly, δ2For stop joint distortion, detent joint is considered the cantilever beam stand under load of termination imposed load, is deformed intoWherein, F is Tensile or Compressive Loading, L2For cantilever beam length, E2For cantilever beam modulus of elasticity, I2For auricle root section
The moment of inertia, it is expressed asWherein, b is auricle root width, and h is auricle thickness.
By recklessly can law F=kx (x be above-mentioned deformation, i.e. δ1Or δ2), obtain latch rigidity：
Similarly, detent joint auricle rigidity is obtained：
Therefore, the global stiffness of latch and detent joint：
Second, according to cabin door structure and the matching relationship of airframe structure, covering, detent joint and the lock bolt and fuselage of hatch door
Structure is respectively provided with matching relationship, determines that the boundary condition of hatch door is as follows：
1) detent joint and airframe structure are contact relation, and contiguity constraint direction is along stop surfaces normal direction, inwardly for just；
2) covering on hatch door periphery and airframe structure are contact relation, and contiguity constraint direction is along covering normal direction, outwards for just；
3) directive wheel and fore-body doorframe are contact relation, and contiguity constraint is vertical and course, vertically with upwards for just,
Course is with backward for just；
4) directive wheel and fuselage afterbody doorframe are contact relation, and contiguity constraint is vertical and course, vertically with upwards for just,
Course is with forward for just；
5) under airtight load working condition, uniform airtight load is applied to covering；Under inertial load operating mode, to hatch door finite element mould
Type applies inertia overload factor；
3rd, by above-mentioned boundary condition, determine the load working condition that hatch door constraints is applicable.
Table 1 gives the load working condition that hatch door constraints is applicable, and wherein X is along vector backward for just, the Y-direction right side is
Just, it is just in Z-direction.
The load working condition that the hatch door constraints of table 1 is applicable
Wherein, " √ " represents that contact is effective, and "×" represents that contact is invalid, and "-" represents the constraint in non-principal posting direction.
4th, according to table 1, the constraint of linear contact analysis model is carried out, is set up in detent joint position along stop surfaces
The contact of normal direction, constraint direction is inside, by the locking justice of SUPORT；The contact along covering normal direction is set up in periphery covering position, about
Shu Fangxiang is outside, by the locking justice of SUPORT；Contact vertically is set up in directive wheel position, constraint direction is upward, by SUPORT
Locking justice；Vertical, the lateral free degree is constrained in latched position, by the locking justice of SPC.
Finally, constraint control file is set up, NASTRAN computings is submitted and debugs, solve sequence 101.
Table 2 gives the result that hatch door linear contact calculates constraint reaction.
Table 2, hatch door linear contact calculate constraint reaction result
In order that invention effect is more protruded, the present embodiment additionally uses linear analysis method and has carried out structural static strength meter
Calculate, it is as follows.
Nonlinear analysis models are set up, using gap element GAP simulating contact relations, submit NASTRAN to carry out non-linear
Analysis, solves sequence 106, is 2 times of linear contact calculating by the statistics calculating time used.It is non-linear that table 3 gives hatch door
Contact calculates the result of constraint reaction.
Table 3, hatch door NONLINEAR CALCULATION constraint reaction result
Contrast linear contact result of calculation and NONLINEAR CALCULATION result, both constraint reaction values in Main Load direction
Quite；Under two kinds of computation schemas, the positive lower detent joint constraint reaction distribution of compressive load effect is basically identical.Therefore using linear
Contact analysis method can be more convenient, calculate cabin door structure static strength exactly.
Advantages of the present invention and effect include：
1) contact performance for the method energy accurate simulation cabin door structure that the present invention is provided, meets the calculating of cabin door structure static strength
It is required that.
2) compared with NONLINEAR CALCULATION, calculated gap element stiffness data are not spent, and can respectively be solved with multi-state,
Significantly shorten calculating cycle, reduce design cost.
3) contact that the method that the present invention is provided can be completed under linear analysis is calculated, simple to operate, realizes calculating side
The standardization of method and flow, it is to avoid the result error that different research staff occur when calculating.
It is last it is to be noted that：The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent
The present invention is described in detail with reference to the foregoing embodiments for pipe, it will be understood by those within the art that：It is still
Technical scheme described in foregoing embodiments can be modified, or which part technical characteristic is equally replaced
Change；And these modifications or replacement, the essence of appropriate technical solution is departed from the essence of various embodiments of the present invention technical scheme
God and scope.
Claims (5)
1. a kind of cabin door structure static strength computational methods, it is characterised in that including:
S1, the FEM model for setting up cabin door structure；
S2, the matching relationship according to cabin door structure and airframe structure, determine boundary condition；
S3, the load working condition that the constraints of cabin door structure is applicable, the load working condition bag are determined according to the boundary condition
Include airtight load working condition and inertial load operating mode；
S4, the constraint for carrying out linear contact analysis model, set up constraint control file, calculate hatch door linear contact constraint reaction
As a result.
2. cabin door structure static strength computational methods as claimed in claim 1, it is characterised in that：Setting up the FEM model
When, the hatch door load component of selection comprises at least covering, longeron, crossbeam, detent joint, directive wheel and lock bolt.
3. cabin door structure static strength computational methods as claimed in claim 2, it is characterised in that：Setting up the FEM model
When, when simulating the coupling stiffness of detent joint, the rigidity at least including latch rigidity and detent joint auricle.
4. cabin door structure static strength computational methods as claimed in claim 1, it is characterised in that：The boundary condition includes stop
The contiguity constraint of joint and airframe structure, the contiguity constraint of covering and airframe structure, the contiguity constraint of directive wheel and fuselage doorframe
And the airtight load restraint with inertial load.
5. cabin door structure static strength computational methods as claimed in claim 1, it is characterised in that：The step S4 further comprises
Constraint control file is set up, and by NASTRAN computings and debugging, solves sequence 101.
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| CN201710200405.3A CN107016181A (en) | 2017-03-30 | 2017-03-30 | A kind of cabin door structure static strength computational methods |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107525673A (en) * | 2017-10-25 | 2017-12-29 | 南京康尼机电股份有限公司 | The exposure parameter measurement apparatus and method of a kind of rail traffic vehicles door guidance system |
| CN108090260A (en) * | 2017-12-01 | 2018-05-29 | 中国直升机设计研究所 | A kind of analysis method of connector restraint forces |
| CN110378000A (en) * | 2019-07-11 | 2019-10-25 | 上海理工大学 | Structural static strength design method based on intensity field |
| CN110489825A (en) * | 2019-07-30 | 2019-11-22 | 中国航发沈阳发动机研究所 | A kind of Compensation Design method of big orifice class air pipe line |
| CN112417600A (en) * | 2020-11-20 | 2021-02-26 | 中国直升机设计研究所 | Method for rapidly calculating static strength of helicopter oil tank cabin |
| CN113607559A (en) * | 2021-07-14 | 2021-11-05 | 武汉航达航空科技发展有限公司 | Static test platform for cockpit door |
| CN114239152A (en) * | 2021-12-31 | 2022-03-25 | 中国航空工业集团公司西安飞机设计研究所 | Deformation calculation method for rectangular airtight cabin of airplane |
| CN114492145A (en) * | 2022-03-31 | 2022-05-13 | 江铃汽车股份有限公司 | Structural member static strength analysis method and system based on CAE |
| CN114692469A (en) * | 2022-05-27 | 2022-07-01 | 成都飞机工业（集团）有限责任公司 | Optimization method of local finite element model of aircraft door and fuselage contact area |
| CN115186395A (en) * | 2022-09-07 | 2022-10-14 | 中国飞机强度研究所 | Cabin door failure characteristic analysis method for airplane test |
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Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107525673B (en) * | 2017-10-25 | 2023-10-31 | 南京康尼机电股份有限公司 | Contact parameter measuring device and method for rail transit vehicle door guiding system |
| CN107525673A (en) * | 2017-10-25 | 2017-12-29 | 南京康尼机电股份有限公司 | The exposure parameter measurement apparatus and method of a kind of rail traffic vehicles door guidance system |
| CN108090260A (en) * | 2017-12-01 | 2018-05-29 | 中国直升机设计研究所 | A kind of analysis method of connector restraint forces |
| CN108090260B (en) * | 2017-12-01 | 2021-04-30 | 中国直升机设计研究所 | Analysis method for joint constrained load |
| CN110378000A (en) * | 2019-07-11 | 2019-10-25 | 上海理工大学 | Structural static strength design method based on intensity field |
| CN110378000B (en) * | 2019-07-11 | 2020-11-24 | 上海理工大学 | Structural static strength design method based on strength field |
| CN110489825A (en) * | 2019-07-30 | 2019-11-22 | 中国航发沈阳发动机研究所 | A kind of Compensation Design method of big orifice class air pipe line |
| CN112417600A (en) * | 2020-11-20 | 2021-02-26 | 中国直升机设计研究所 | Method for rapidly calculating static strength of helicopter oil tank cabin |
| CN113607559A (en) * | 2021-07-14 | 2021-11-05 | 武汉航达航空科技发展有限公司 | Static test platform for cockpit door |
| CN114239152A (en) * | 2021-12-31 | 2022-03-25 | 中国航空工业集团公司西安飞机设计研究所 | Deformation calculation method for rectangular airtight cabin of airplane |
| CN114239152B (en) * | 2021-12-31 | 2022-09-20 | 中国航空工业集团公司西安飞机设计研究所 | Deformation calculation method for rectangular airtight cabin of airplane |
| CN114492145B (en) * | 2022-03-31 | 2022-08-09 | 江铃汽车股份有限公司 | Structural member static strength analysis method and system based on CAE |
| CN114492145A (en) * | 2022-03-31 | 2022-05-13 | 江铃汽车股份有限公司 | Structural member static strength analysis method and system based on CAE |
| CN114692469A (en) * | 2022-05-27 | 2022-07-01 | 成都飞机工业（集团）有限责任公司 | Optimization method of local finite element model of aircraft door and fuselage contact area |
| CN115186395A (en) * | 2022-09-07 | 2022-10-14 | 中国飞机强度研究所 | Cabin door failure characteristic analysis method for airplane test |
| CN115186395B (en) * | 2022-09-07 | 2022-11-25 | 中国飞机强度研究所 | Cabin door failure characteristic analysis method for airplane test |
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