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《考慮復(fù)合材料蒙皮穩(wěn)定性的飛機翼面結(jié)構(gòu)布局優(yōu)化設(shè)計》由會員上傳分享，免費在線閱讀，更多相關(guān)內(nèi)容在行業(yè)資料-天天文庫。
1、第31卷第10期航空學(xué)報Vol131No1102010年10月ACTAAERONAUTICAETASTRONAUTICASINICAOct.2010文章編號:100026893(2010)1021985208考慮復(fù)合材料蒙皮穩(wěn)定性的飛機翼面結(jié)構(gòu)布局優(yōu)化設(shè)計1112劉穎卓,張永存,劉書田,王向明(1.大連理工大學(xué)工程力學(xué)系,遼寧大連116023)(2.沈陽飛機設(shè)計研究所,遼寧沈陽110035)LayoutOptimizationDesignofWingStructureswithConsiderationof
2、StabilityofCompositeSkin1112LiuYingzhuo,ZhangYongcun,LiuShutian,WangXiangming(1.DepartmentofEngineeringMechanics,DalianUniversityofTechnology,Dalian116023,China)(2.ShenyangAircraftDesignResearchInstitute,Shenyang110035,China)摘要:復(fù)合材料蒙皮穩(wěn)定性是飛機翼面結(jié)構(gòu)設(shè)計需要考慮的重要方面。
3、由于翼面結(jié)構(gòu)穩(wěn)定性理論分析的復(fù)雜性,工程中,通常采用與理論分析相比擬的簡化方法、使用簡便可靠的經(jīng)驗公式在設(shè)計過程中進行穩(wěn)定性校核。多墻式結(jié)構(gòu)是當(dāng)前翼面結(jié)構(gòu)中普遍采用的結(jié)構(gòu)形式,墻的布局和蒙皮的厚度對復(fù)合材料蒙皮的臨界屈曲載荷有著重要影響。因此,針對多墻式翼面結(jié)構(gòu),以工程經(jīng)驗公式為基礎(chǔ),以蒙皮單位長度上的的重量為優(yōu)化目標(biāo),以墻的布局參數(shù)和蒙皮厚度為設(shè)計變量,以臨界失穩(wěn)載荷為約束,建立了一種考慮復(fù)合材料蒙皮穩(wěn)定性的翼面結(jié)構(gòu)布局優(yōu)化問題的數(shù)學(xué)模型,導(dǎo)出了目標(biāo)函數(shù)敏度計算的解析式,并提出了優(yōu)化問題的求解方法。以翼盒
4、結(jié)構(gòu)為例,驗證了該方法的有效性。關(guān)鍵詞:翼面結(jié)構(gòu);布局優(yōu)化;穩(wěn)定性;復(fù)合材料;優(yōu)化設(shè)計中圖分類號:V214.8文獻標(biāo)識碼:AAbstract:Ensuringthestabilityofthecompositeskinisofgreatsignificanceinthedesignofaircraftwingstructures.Theoretically,itisverydifficulttosolvethestabilityofwingstructures.Therefore,asimpleandrel
5、iableempiricalformula,whichisasimplifiedmethodbyanalogizingwiththetheoreticalanalysis,isadoptedinengineeringdesign.Atpresent,themulti2sparstructureiswidelyusedinaircraftwingstructures.Whenamulti2sparstructureisdesigned,thefocusistoreducethestructuralweight
6、throughtheoptimalarrangementoftheload2carryingcomponentswithinthewing2boxstructuresandtheminimalthicknessoftheskinunderaspecifiedair2loadingcondition.Thelayoutofthewingsparsandthethicknessoftheskinhavegreateffectonthestabilityofthecompositeskin.Therefore,a
7、mathematicalmodelonthelayoutoptimizationofwingstruc2turesisdevelopedwiththeconstraintofthestabilityofthecompositeskin.Tosolvethisoptimizationprob2lem,thestabilityofthecompositeskinissolvedbasedontheempiricalformula,andasensitivityformulaisal2soestablished.
8、Finally,awingboxstructureistakenasanexample,andtheoptimalresultsprovethatthemethodpresentedinthisarticleisveryeffectiveinaircraftwingdesign.Keywords:wingstructure;layoutoptimization;stability;compositemateria
