CN109583040A

CN109583040A - A kind of optimization method considering composite structure parametric continuity

Info

Publication number: CN109583040A
Application number: CN201811319356.6A
Authority: CN
Inventors: 吴斌; 段婷婷; 杨晔楠; 刘凤楠
Original assignee: Xian Aircraft Design and Research Institute of AVIC
Current assignee: Xian Aircraft Design and Research Institute of AVIC
Priority date: 2018-11-07
Filing date: 2018-11-07
Publication date: 2019-04-05
Anticipated expiration: 2038-11-07
Also published as: CN109583040B

Abstract

The invention belongs to field of airplane structure, specially a kind of optimization method for considering composite structure parametric continuity.Include the following steps: initial configuration analysis, parameter subregion, selected basic area, the ratio for establishing other parameters subregion and basic area, establish ratio constraint condition, optimization design, export optimum results.While realizing composite plys structure parameter optimizing, the continuity of Lay up design is taken into account, Optimum Design Results only need a small amount of amendment, may be directly applied to engineering structure detailed design.This method strong operability is adapted to all kinds of optimization analysis programs, and computational efficiency is high, and consumption resource is few.

Description

A kind of optimization method considering composite structure parametric continuity

Technical field

The invention belongs to field of airplane structure, specially a kind of optimization for considering composite structure parametric continuity Method.

Background technique

Metal structure optimization design only needs to obtain the parameter distribution of each optimization design subregion, but for composite material Structure, the in order to balance craftsmanship of laying, the continuity that the parameter of each optimization design by stages must have.

When tradition is optimized using classic optimization design algorithm (such as planning class algorithm), it is only capable of composite material The overlay thickness of each subregion is as optimal design parameter, and the laying of each by stages is often difficult continuously, thus bring result It is to need to be modified Optimum Design Results, many times, the rebound of weight can be brought to the amendment of optimization design, weakened excellent Change the income of loss of weight.It is as shown in Figure 1 the Optimum Design Results in the area A and the area B, wherein the area A laying carries out thickness to the area B for thick area Transition, if two-way carry out thickness transitions, will cause the distortion in transition zone type face, craftsmanship and force-transfer characteristic are all poor, are Improvement such case, need to carry out modified result (refilling -45 ° of layings in the area A) as shown in Figure 2, and this amendment is so that the area A Weight increases, and counteracts the effect of optimization design acquirement.

Although the evolution class such as genetic algorithm optimization algorithm can take into account the continuity of laying in genome code, for big The structure of Medium Plane, optimal design parameter is more, if to obtain Optimum Design Results, needs to consume a large amount of computing resource, Need several parallel computers that could obtain Optimum Design Results by the calculating iteration of a couple of days.Evolution class optimization algorithm can be made For technological reserve research, but also need to promote computational efficiency from practical implementation.

Summary of the invention

Incorporation engineering design experiences, using traditional planning class optimization algorithm, realization takes into account the successional composite wood of laying Expect Design of Structural parameters, improve optimization efficiency, amendment few as far as possible is carried out to optimization analysis result, that is, is applicable to engineering The detailed design of structure.

Technical solution

Engineering structure Parameters Optimal Design is carried out after laying Path of Force Transfer determines, according to initial load distribution and structure Stress/strain level distribution determines the optimization design subregion of part, for covering or fine strain of millet web class based on two-dimensional cell Part.

Extract the overlay thickness respectively spread in each laying subregion to angle.The area part Shang Hou or thin area is taken to be used as basic subregion, It respectively spreads to the overlay thickness at angle as basic parameter, constructs basic subregion and respectively spreads to angle overlay thickness and the same paving in adjacent sectors Ratio between the overlay thickness at angle: R1, R2 ..., Rn.

According in the loading characteristic of structure and composite structure design requirement to the limit of adjacent caliper zones thickness change System requires, and gives a value interval to each ratio, and a part as optimization constraint condition is introduced into optimization design mould In type, optimization is submitted to calculate.

According to calculated result, the value interval of appropriate adjustment thickness ratio finally obtains composite structure and respectively spreads to angle Overlay thickness optimal value, while guaranteeing that a certain paving in thin area can covered in thick area to the overlay thickness at angle, make laying It is continuous between adjacent sectors.Optimization design process is as shown in Figure 3.

Software, algorithm of this technology method independent of optimization design, it is ensured that in optimum results, each laying of composite material Continuity between adjacent sectors.The adjacent laying subregion thickness change of composite material is converted into laying by stages thickness ratio, Be updated to thickness ratio as optimization one of constraint condition in Optimized model, in the area Shi Hou the thickness of a certain wing flapping be greater than or Equal to the thickness of same wing flapping in thin area, the shape optimum to composite plys is converted into numerical optimization.

The part is covering or fine strain of millet web class based on two-dimensional cell

Technical effect

1. realize composite plys structure parameter optimizing, the continuity of Lay up design, optimization design have been taken into account As a result a small amount of amendment is only needed, may be directly applied to engineering structure detailed design.

2. this method strong operability is adapted to all kinds of optimization analysis programs, computational efficiency is high, and consumption resource is few.

Detailed description of the invention

Fig. 1 is optimum design of laminate layup result figure

Fig. 2 is the correction map of Optimum Design Results

Fig. 3 is to consider the successional composite structure parameter optimization flow chart of laying

Fig. 4 is typical composite plys thickness change schematic diagram

Fig. 5 is typical aerofoil optimal design parameter block plan

Fig. 6 is typical optimal design parameter continuity definition figure

Specific embodiment

Case one:

Certain part has tri- thickness subregions of t1, t2, t3, as shown in figure 4, wherein arrow instruction direction is thickness change side To.It is basic subregion with the most area Hou t1, sets up t1 subregion respectively and the adjacent by stages t2, t3 is same spreads to angle laying Thickness ratio relationship (by taking 0 ° spreads to angle overlay thickness as an example, other, which spread to angle laying, can also establish identical ratio): R1 =t1_0°/t2_0°, R2=t2_0°/t3_0°.Bonded composite Structural Design Requirement contrast ratio range carries out constraint appropriate: 1≤R1 ≤ 1.2 (more apparent thickness changes from thick area to thin area), 0.85≤R2≤1.15 (relatively unsharp thickness change), if Base thickness is relatively thin, then constraining bound can relax, for example, for 90 ° of layings, bound can be arranged to 0.5~ 2.0, it, can be by constraint bound tightening if base thickness is thicker.A part of band by above-mentioned constraint as optimization constraint condition Enter to Optimized model, Optimum Design Results can be such that 0 ° of laying in the area t3 is covered completely by the area t2, and 0 in the area t2 ° is spread Also the area Neng Bei t1 covers floor, and while final guarantee part obtains optimal design parameters, 0 ° of laying is to connect in entire inside parts Continuous.

Case two:

Fig. 5 show the optimization design partial parameters subregion of MA700 aircraft vertical stabilization covering, is arranged according to structure, The area 10000x1 is the bonding pad of covering and beam, is the main Path of Force Transfer of aerofoil, and 1000011st area are root docking area, 1000081 Area is end docking area, is main supporting region, is the supporting region and common supporting region of load transition between remaining region, covering Thickness is always transitioned into common supporting region by Gao Zaiqu, and reaches stable and uniform distribution at a certain thickness subregion.It uses The SOL200 solver of Nastran, has worked out parameter Optimization Analysis file, and Fig. 6 show the corresponding 0 ° of overlay thickness in each region Design variable and its ratio, from 1000011st to 1000041 area, 0 ° of thickness in thin area is the 0.8~1.0 of thick area, from 0 ° of thickness in 1000051st to 1000081 area, thin area is the 0.8~1.0 of thick area, and 1000041st to 1000051 area, and thickness becomes Change is less apparent, and rate of change range is set to 0.8~1.1.

Other laying subregions and spreading also define in this way between angle.This model is optimized, box section knot is obtained Structure overall weight 129.7Kg, compared with 8% or more same type aircraft vertical stabilization structural weight reduction, wherein siding optimizes weight 31.8Kg, covering parameter only need to be adjusted ply stacking-sequence, and after the check of intensity profession, without increasing laying, and intensity is abundant Degree between 0.1~0.2, final wall panel structure detailed design weight be 32.5Kg (containing paint and fastener), optimization design and in detail Thin design weight accordance is very consistent.

Claims

1. a kind of optimization method for considering composite structure parametric continuity, which is characterized in that

Engineering structure Parameters Optimal Design is carried out after laying Path of Force Transfer determines, answers according to initial load distribution and structure Power/Strain Distribution is horizontal, determines the optimization design subregion of part；

Extract the overlay thickness respectively spread in each laying subregion to angle；Take the area part Shang Hou or thin area as basic subregion, it is each Spread to the overlay thickness at angle as basic parameter, construct basic subregion respectively spread to angle overlay thickness with adjacent sectors are same spreads to angle Overlay thickness between ratio: R1, R2 ..., Rn；

The limitation of adjacent caliper zones thickness change is wanted according in the loading characteristic of structure and composite structure design requirement It asks, a value interval is given to each ratio, and a part as optimization constraint condition is introduced into mathematical optimization models, Optimization is submitted to calculate；

According to calculated result, the value interval of appropriate adjustment thickness ratio finally obtains composite structure and respectively spreads paving to angle Thickness degree optimal value, while guaranteeing that a certain paving in thin area can covered in thick area to the overlay thickness at angle, make laying in phase Adjacent by stages is continuous.

2. a kind of optimization method for considering composite structure parametric continuity according to claim 1, which is characterized in that The part is the two-dimensional cell of covering or fine strain of millet web class.