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1、航天返回與遙感第37卷第2期26SPACECRAFTRECOVERY&REMOTESENSING2016年4月某無人機(jī)橫向圓柱排氣式氣囊著陸裝置緩沖過程研究邵志建裴錦華(南京航空航天大學(xué)中小型無人機(jī)先進(jìn)技術(shù)工業(yè)和信息化部重點(diǎn)實(shí)驗(yàn)室,南京210016)摘要排氣式氣囊作為一類有效緩沖裝置,在諸多回收領(lǐng)域廣泛使用。通過設(shè)計(jì)適當(dāng)氣囊尺寸和排氣孔大小可以實(shí)現(xiàn)對(duì)回收對(duì)象的過載和接地速度的有效控制,從而避免反彈和側(cè)翻現(xiàn)象的發(fā)生。文章以某無人機(jī)圓柱排氣式氣囊為對(duì)象,研究了該類氣囊的仿真分析方法。首先從理論角度出發(fā),將氣囊緩沖階段
2、分為封閉壓縮和排氣釋放兩個(gè)階段,基于氣體狀態(tài)方程和動(dòng)力學(xué)推導(dǎo)了橫向圓柱型排氣氣囊模型的運(yùn)動(dòng)微分方程,并給出了相應(yīng)的計(jì)算方法;然后,采用大型有限元仿真分析技術(shù),實(shí)現(xiàn)了該類氣囊結(jié)構(gòu)和著陸過程的數(shù)學(xué)和力學(xué)建模,獲得全向式緩沖氣囊著陸的動(dòng)態(tài)過程仿真。最后對(duì)比兩種模型與試驗(yàn)在樣機(jī)重心處的過載與速度變化曲線。研究結(jié)果表明,文章提出的理論近似模型能夠較好的反映該類排氣式氣囊的著陸緩沖特性,相比有限元模型,可以兼顧分析精度與效率,這為后續(xù)氣囊系統(tǒng)的改進(jìn)設(shè)計(jì)提供了可靠的分析工具。關(guān)鍵詞氣囊固定排氣孔著陸緩沖有限元仿真分析無人機(jī)中圖
3、分類號(hào):V244.1文獻(xiàn)標(biāo)志碼:A文章編號(hào):1009-8518(2016)02-0026-08DOI:10.3969/j.issn.1009-8518.2016.02.004SimulationofBi-cylindricalAirbagCushioningSystemforPilotlessAircraftSHAOZhijianPEIJinghua(KeyLaboratoryofUnmannedAerialVehicleTechnology,NanjingUniversityofAeronauticsandAs
4、tronautics,MinistryofIndustryandInformationTechnology,Nanjing210016,China)AbstractVentedairbag,whichcanbedeployedwithamoretargetedarrangementduetoitsdeterminis-ticimpactloaddirection,iscommonlyusedinmodernunmannedaerialvehicles(UAVs),mannedspacecraft,andheavy
5、cargoairdrops.Aventedairbagofsuitablesizeandventholedimensioncankeepoverloadwithinanallowedrange,controltouchdownspeedofrecoveryobject,andpreventbouncingbyproperlydesignedairbag.AsimulationanalysismethodofacylindricalairbagforUAVisstudiedinthispaper.Firstly,t
6、helandingprocessofairbagisdecomposedintoadiabaticcompressionandreleaseoflandingshockenergy;thedifferentialequationofcylindricalgas-filledbagispresentedtheoreticallybasedontheidealgasstateequa-tionanddynamicequation.Then,landingmathematicandmechanicalmodelsare
7、establishedbyuseofmod-ernFEManalysis,andthesimulationprocessisdeveloped.Finally,thesimulationresultsandthetestdataarecomparedintermsofimportantparametersincludingdynamicprocessofwholeairbagtocushionthelandingandoverloadanalysisofimportantstructuralparts.There
8、sultsshowthatthetheoreticalapproximationmodel,收稿日期:2015-12-04第2期邵志建等:某無人機(jī)橫向圓柱排氣式氣囊著陸裝置緩沖過程研究27asatoolforimprovingthedesignofairbag,canbetterbalancetheaccuracyandefficiencyofsimulationanal