CN109543262A - Helicopter Main Reducer bogusware and its design method - Google Patents
Helicopter Main Reducer bogusware and its design method Download PDFInfo
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- CN109543262A CN109543262A CN201811334295.0A CN201811334295A CN109543262A CN 109543262 A CN109543262 A CN 109543262A CN 201811334295 A CN201811334295 A CN 201811334295A CN 109543262 A CN109543262 A CN 109543262A
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- G06—COMPUTING OR CALCULATING; 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 OR CALCULATING; 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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Abstract
This application provides a kind of Helicopter Main Reducer bogusware and its design methods, this method initially sets up true master and subtracts analysis model, determine the true main stiffness characteristics subtracted, resettle the main finite element concept model appearance for subtracting bogusware, then critical design dimensions are determined using the method for experimental design, the response relation of design variable and design object is obtained simultaneously, and then it selects suitable optimization algorithm to subtract the certain component thickness of bogusware to master and optimizes, final design goes out while meeting the bogusware of strength and stiffness characteristic requirements, it is simple with design, the advantages that design result is reliable.
Description
Technical field
This application involves helicopter structure design fields, specifically provide a kind of Helicopter Main Reducer plus-minus and its set
Meter method.
Background technique
When helicopter complete machine or large component make a strength test, for save funds purpose, non-checking construction and plus
Holder can generally be replaced using bogusware, this kind of bogusware be in design design by meeting strength of materials principle, but when bogusware certainly
When body stiffness effect load distribution, rigidity is not designed, the precision entirely tested will receive influence.
Summary of the invention
At least one in order to solve the above-mentioned technical problem, this application provides a kind of Helicopter Main Reducer bogusware and its set
Meter method.
In a first aspect, this application discloses a kind of design methods of Helicopter Main Reducer bogusware, which is characterized in that packet
It includes:
S1: posting and force analysis are carried out to true main reducing gear, obtain the transmitting of the true main reducing gear tie point
The size and Orientation of load；
S2: establishing the finite element model of the true main reducing gear, according to the direction of the transmitting load to described true
Main reducing gear tie point is constrained accordingly, while being obtained the true main reducing gear according to the size of the transmitting load and being connected
The restraint forces value of junction；
S3: according to the distance and occupied space between the true main reducing gear tie point, main reducing gear bogusware shell is determined
Volume range, an assembled closed shell by the way of the steel plate that welds and/or be spirally connected, and it is false to establish the main reducing gear
The finite element model of part, wherein the main reducing gear bogusware is by main shaft, upper cover plate, oblique closed plate, side plate, connection pedestal, lower cover
Plate and reinforcing rib composition；
S4: for the thickness of each component of the finite element model in selecting step S3 as design variable, design constraint is weldering
Connect area's shearing allowable, the shearing allowable of connection bolt and stretching, case material strength degree；
S5: design of experiment analysis is carried out to the main reducing gear bogusware in step S3:
Design variable in step S4 is sampled, it is horizontal point identical that each design variable is divided into quantity
Area randomly combines all horizontal partitionings, to specify N number of point for defining design matrix, guarantees every
Each horizontal partitioning of one variable is only studied primary；
The number of the design variable of the main reducing gear bogusware is D, according to the manufacturing process of the main reducing gear bogusware, often
The thickness of a plate uses discrete variable, and Thickness range is [t1,t2], Δ t is divided between value, then sample level point N=
(t2-t1)/Δ t randomly selects unduplicated sample point in space and is calculated, and utilizes least square method structure to each response
Multinomial is built to fit analysis data, thus can obtain a series of multinomial coefficient, to any two independent variable X1, X2's
Main effect multinomial:
To above-mentioned polynomial derivation
Dy=C1dX1+C2dX2+2C3X1dX1+2C4X2dX2+C5(X2dX1+X1dX2)
Respectively obtain linear main effect
MX1=C1dX1,MX1=C2dX2,
Second order main effect
Interaction
MX1X2=C5(X1dX2+X2dX1),
And then each design variable is obtained to the influence curve of design object, plate thickness is judged by slope of a curve
Degree filters out the main final design variable for subtracting bogusware analysis model to tie point loading effect on this basis；
S6: the main bogusware stiffness analysis model mathematical characteristic that subtracts determines:
Using the experimental design analysis of step S5, it is fitted the response surface of any two design variable and some design object,
If response surface is plane, stiffness characteristics are linear problems；
If response surface is the curved surface of single wave crest, stiffness characteristics are unimodal nonlinear problems；
If response surface, there are multiple wave crests, stiffness characteristics are multimodal nonlinear problems；
S7: the setting of equivalent stiffness evaluation criteria:
Under same loading environment, in the connection point load and step S2 that the main reducing gear bogusware analysis model obtains
True main reducing gear tie point load comparison, the change rate of the two is smaller, then illustrates that bogusware and true part stiffness characteristics are closer；
S8: mathematical optimization models are established:
Design variable is determined that optimization algorithm chooses the analysis for referring to step S6, if rigidity model is linear by step S5
Or unimodal nonlinear problem, select any one global or local optimization algorithm；
If rigidity model is multimodal nonlinear problem, the algorithm for selecting local optimum that global optimization is added to combine；
Design object is determined by step S7, and after the completion of seismic responses calculated, obtained each part dimension is final institute
State the design size of main reducing gear bogusware.
According at least one embodiment of the application, in step S5, it is corresponding greatly that final design variable chooses the slope of curve
Panel thickness.
Second aspect, this application discloses a kind of Helicopter Main Reducer bogusware, Helicopter Main Reducer bogusware passes through upper
The Helicopter Main Reducer bogusware design method stated obtains.
In Helicopter Main Reducer plus-minus provided by the embodiments of the present application and its design method, true main deceleration is initially set up
Device analysis model determines the stiffness characteristics of true main reducing gear, resettles the finite element concept model appearance of main reducing gear bogusware,
Then critical design dimensions are determined using the method for experimental design, while obtain the response relation of design variable and design object,
And then select suitable optimization algorithm to subtract the certain component thickness of bogusware to master and optimize, final design goes out while meeting strong
The bogusware that degree and stiffness characteristics require.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of main reducing gear bogusware provided by the embodiments of the present application.
Wherein:
1, main shaft；2, upper cover plate；3, oblique closed plate；4, side plate；5, pedestal is connected；6, lower cover plate；7, reinforcing rib.
Specific embodiment
The application is described in further detail with reference to the accompanying drawings and examples.It is understood that this place is retouched
The specific embodiment stated is used only for explaining related application, rather than the restriction to this application.It also should be noted that in order to
Convenient for description, part relevant to the application is illustrated only in attached drawing.
It should be noted that in the absence of conflict, the features in the embodiments and the embodiments of the present application can phase
Mutually combination.The application is described in detail below with reference to the accompanying drawings and in conjunction with the embodiments.
The design method of Helicopter Main Reducer bogusware provided by the embodiments of the present application the following steps are included:
S1: posting and force analysis are carried out to true main reducing gear, obtain the transmitting load of true main reducing gear tie point
Size and Orientation.
S2: establishing the finite element model of true main reducing gear, is connected according to the direction of transmitting load to true main reducing gear
Point is constrained accordingly, while obtaining the restraint forces value at true main reducing gear tie point according to the size of transmitting load.
Wherein, restraint forces value can embody the rigidity of true main reducing gear.
S3: according to the distance and occupied space between true main reducing gear tie point, the body of main reducing gear bogusware shell is determined
Product range, an assembled closed shell by the way of the steel plate that welds and/or be spirally connected, and establish the limited of main reducing gear bogusware
Meta-model.
Wherein, by the way of the steel plate that welds and/or be spirally connected, it can guarantee the simplicity for producing mounting process.
As shown in Figure 1, main reducing gear bogusware by main shaft, upper cover plate, oblique closed plate, side plate, connection pedestal, lower cover plate and
The shell of reinforcing rib composition.
S4: for the thickness of each component of the finite element model in selecting step S3 as design variable, design constraint is weldering
Connect area's shearing allowable, the shearing allowable of connection bolt and stretching, case material strength degree.
Wherein, welding section shearing allowable, the shearing allowable of connection bolt can be from setting with stretching, case material strength degree
It is searched in meter handbook.
S5: design of experiment analysis is carried out to the main reducing gear bogusware in step S3:
Design variable in step S4 is sampled, each design variable is divided into the identical horizontal partitioning of quantity,
All horizontal partitionings are randomly combined, to specify N number of point for defining design matrix, guarantee each variable
Each horizontal partitioning be only studied it is primary.
The number of the design variable of main reducing gear bogusware is D, according to the manufacturing process of main reducing gear bogusware, each plate
Thickness uses discrete variable, and Thickness range is [t1,t2], Δ t is divided between value, then sample level point N=(t2-t1)/
Δ t randomly selects unduplicated sample point in space and is calculated, and constructs multinomial using least square method to each response
To fit analysis data, a series of multinomial coefficient thus can be obtained, to any two independent variable X1, X2Main effect it is more
Item formula:
To above-mentioned polynomial derivation
Dy=C1dX1+C2dX2+2C3X1dX1+2C4X2dX2+C5(X2dX1+X1dX2)
Respectively obtain linear main effect
MX1=C1dX1,MX1=C2dX2,
Second order main effect
Interaction
MX1X2=C5(X1dX2+X2dX1),
And then each design variable is obtained to the influence curve of design object, panel thickness pair is judged by slope of a curve
Tie point loading effect filters out the main final design variable for subtracting bogusware analysis model on this basis.
Optionally, final design variable chooses the big corresponding panel thickness of the slope of curve.
S6: the main bogusware stiffness analysis model mathematical characteristic that subtracts determines:
Using the experimental design analysis of step S5, it is fitted the response surface of any two design variable and some design object,
If response surface is plane, stiffness characteristics are linear problems；
If response surface is the curved surface of single wave crest, stiffness characteristics are unimodal nonlinear problems；
If response surface, there are multiple wave crests, stiffness characteristics are multimodal nonlinear problems；
S7: the setting of equivalent stiffness evaluation criteria:
Under same loading environment, connection point load that main reducing gear bogusware analysis model obtains with it is true in step S2
Main reducing gear tie point load comparison, the change rate of the two is smaller, then illustrates that bogusware and true part stiffness characteristics are closer.
S8: mathematical optimization models are established:
Design variable is determined that optimization algorithm chooses the analysis for referring to step S6, if rigidity model is linear by step S5
Or unimodal nonlinear problem, select any one global or local optimization algorithm；
If rigidity model is multimodal nonlinear problem, the algorithm for selecting local optimum that global optimization is added to combine；
Design object is determined by step S7, and after the completion of seismic responses calculated, obtained each part dimension is final master
The design size of retarder bogusware.
On the other hand, present invention also provides a kind of Helicopter Main Reducer bogusware, subtracted by above-mentioned Helicopter Main
Fast device bogusware design method obtains.
So far, it has been combined preferred embodiment shown in the drawings and describes the technical solution of the application, still, this field
Technical staff is it is easily understood that the protection scope of the application is expressly not limited to these specific embodiments.Without departing from this
Under the premise of the principle of application, those skilled in the art can make equivalent change or replacement to the relevant technologies feature, these
Technical solution after change or replacement is fallen within the protection scope of the application.
Claims (3)
1. a kind of design method of Helicopter Main Reducer bogusware characterized by comprising
S1: posting and force analysis are carried out to true main reducing gear, obtain the transmitting load of the true main reducing gear tie point
Size and Orientation；
S2: establishing the finite element model of the true main reducing gear, is subtracted according to the direction of the transmitting load to the true master
Fast device tie point is constrained accordingly, while obtaining the true main reducing gear tie point according to the size of the transmitting load
The restraint forces value at place；
S3: according to the distance and occupied space between the true main reducing gear tie point, the body of main reducing gear bogusware shell is determined
Product range, an assembled closed shell by the way of the steel plate that welds and/or be spirally connected, and establish the main reducing gear bogusware
Finite element model, wherein the main reducing gear bogusware by main shaft, upper cover plate, oblique closed plate, side plate, connection pedestal, lower cover plate with
And reinforcing rib composition；
S4: for the thickness of each component of the finite element model in selecting step S3 as design variable, design constraint is welding section
It is allowable to shear, connect bolt shearing allowable and stretching, case material strength degree；
S5: design of experiment analysis is carried out to the main reducing gear bogusware in step S3:
Design variable in step S4 is sampled, each design variable is divided into the identical horizontal partitioning of quantity,
All horizontal partitionings are randomly combined, to specify N number of point for defining design matrix, guarantee each
Each horizontal partitioning of variable is only studied primary；
The number of the design variable of the main reducing gear bogusware is D, according to the manufacturing process of the main reducing gear bogusware, each plate
The thickness of part uses discrete variable, and Thickness range is [t1,t2], Δ t is divided between value, then sample level point N=(t2-
t1)/Δ t randomly selects unduplicated sample point in space and is calculated, more using least square method building to each response
Thus item formula can obtain a series of multinomial coefficient, to any two independent variable X to fit analysis data1, X2Main effect
Answer multinomial:
To above-mentioned polynomial derivation
Dy=C1dX1+C2dX2+2C3X1dX1+2C4X2dX2+C5(X2dX1+X1dX2)
Respectively obtain linear main effect
MX1=C1dX1,MX1=C2dX2,
Second order main effect
Interaction
MX1X2=C5(X1dX2+X2dX1),
And then each design variable is obtained to the influence curve of design object, panel thickness pair is judged by slope of a curve
Tie point loading effect filters out the main final design variable for subtracting bogusware analysis model on this basis；
S6: the main bogusware stiffness analysis model mathematical characteristic that subtracts determines:
Using the experimental design analysis of step S5, it is fitted the response surface of any two design variable and some design object,
If response surface is plane, stiffness characteristics are linear problems；
If response surface is the curved surface of single wave crest, stiffness characteristics are unimodal nonlinear problems；
If response surface, there are multiple wave crests, stiffness characteristics are multimodal nonlinear problems；
S7: the setting of equivalent stiffness evaluation criteria:
Under same loading environment, connection point load that the main reducing gear bogusware analysis model obtains with it is true in step S2
Main reducing gear tie point load comparison, the change rate of the two is smaller, then illustrates that bogusware and true part stiffness characteristics are closer；
S8: mathematical optimization models are established:
Design variable is determined that optimization algorithm chooses the analysis for referring to step S6, if rigidity model is linear or single by step S5
Peak nonlinear problem selects any one global or local optimization algorithm；
If rigidity model is multimodal nonlinear problem, the algorithm for selecting local optimum that global optimization is added to combine；
Design object is determined by step S7, and after the completion of seismic responses calculated, obtained each part dimension is the final master
The design size of retarder bogusware.
2. the design method of Helicopter Main Reducer bogusware according to claim 1, which is characterized in that in step S5, most
Whole design variable chooses the big corresponding panel thickness of the slope of curve.
3. a kind of Helicopter Main Reducer bogusware, which is characterized in that Helicopter Main Reducer bogusware passes through claims 1 or 2 institute
The Helicopter Main Reducer bogusware design method stated obtains.
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| CN201811334295.0A CN109543262A (en) | 2018-11-09 | 2018-11-09 | Helicopter Main Reducer bogusware and its design method |
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| CN201811334295.0A CN109543262A (en) | 2018-11-09 | 2018-11-09 | Helicopter Main Reducer bogusware and its design method |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110083979A (en) * | 2019-05-15 | 2019-08-02 | 重庆大学 | A kind of heavy helicopter main reducing gear point turns round transmission and carries design method |
| CN118618728A (en) * | 2024-06-18 | 2024-09-10 | 中国航发成都发动机有限公司 | Complete machine dummy for aircraft engine packaging box identification test |
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| CN104002988A (en) * | 2014-04-17 | 2014-08-27 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for implementing aircraft arresting static test |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110083979A (en) * | 2019-05-15 | 2019-08-02 | 重庆大学 | A kind of heavy helicopter main reducing gear point turns round transmission and carries design method |
| CN118618728A (en) * | 2024-06-18 | 2024-09-10 | 中国航发成都发动机有限公司 | Complete machine dummy for aircraft engine packaging box identification test |
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