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簡(jiǎn)介：航天器多信源測(cè)控?cái)?shù)據(jù)融合及應(yīng)用研究重慶大學(xué)博士學(xué)位論文學(xué)生姓名張志芬指導(dǎo)教師柴毅教授專業(yè)控制理論與控制工程學(xué)科門類工學(xué)重慶大學(xué)自動(dòng)化學(xué)院二OO八年十月STUDYONDATAFUSIONWITHAPPLICATIONSFROMAIRCRAFTMULTIINFMATIONMEASUREMENTCONTROLATHESISSUBMITTEDTOCHONGQINGUNIVERSITYINPARTIALFULFILLMENTOFTHEREQUIREMENTFTHEDEGREEOFDOCTOFENGINEERINGBYZHANGZHIFENSUPERVISEDBYPROFCHAIYIMAJCONTROLTHEYCONTROLENGINEERINGCOLLEGEOFAUTOMATIOMOFCHONGQINGUNIVERSITYCHONGQINGCHINAOCTOBER2008

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簡(jiǎn)介：圖書分類號(hào)H133§§UDC620V密級(jí)韭蜜碩士學(xué)位論文航天發(fā)射塔回轉(zhuǎn)平臺(tái)狀態(tài)質(zhì)量檢測(cè)技術(shù)研究塞蠶筮指導(dǎo)教師姓名、職稱潘塞迭熬授塑漫起煎攮申請(qǐng)學(xué)位級(jí)別工堂亟±專業(yè)名稱信呈皇信皇處堡論文提交日期2鯉1年月論文答辯日期2魚旦年學(xué)位授予日期年至臼5月19日月日論文評(píng)閱人塞篷羞副塾援蕙置墓副熬授答辯委員會(huì)主席整漁起熬撞2007年4月27日THESTUDYONSTATEQUALITYTESTTECHNOLOGYOFROTARYFLATINTHESPACEFLIGHTLAUNCHTOWERABSTRACTTHESPACEFLIGHTLAUNCHSITEEQUIPMENTISTHEMATTERFOUNDATIONFOREXPERIMENT,WHICHISDIRECTLYRELATEDTOTHESUOL3CSSORFAILUREOFIT．THISPAPERCONTRIBUTESEFFECTIVETHEORYANDMETHODSFORTHESPACEFLIGHTLAUNCHSITEEQUIPMENT．THEKEYPARTOFTHEROTARYFLATISTHEROLLINGBEARINGOFRECIPROCATING，LOWSPEED，NONFULLROTATIONANDHEAVYLOAD．BECAUSEOFTHEROLLINGBEARING’SSPCCIALWORKCHARACTERISTIC,TRADITIONALFAULTDIAGNOSISDON’TDIRECTLYUSE．ITISFULLYNEWSTUDYAREAFORTHEFAULTDIAGNOSISOFTHEROLLINGBEARING．THEPAPERFIRSTLYSTUDYTHECAUSEANDTYPEOFFAULTINROLLINGBEARING，ANALYZETHEVIBRATIONFEATUREOFAUKINDSOFFAULTSANDSUMMARIZETHEVIBRATIONDETECTIONTHEORYOFTHISTYPEBEARING．THEYARETHEPRINCIPLEBASISOFSTATEQUALITYTEST．TESTSYSTEMISDESIGNED．BASEDONTHEEXPERIMENT，ITFWSFLYPUTFORWARDPULSEENERGYFORTHESTATEQUAFITYTESTFORTHETONINGBEARINGOFRECIPROCATING，LOWSPEED,NONFULLROTATIONANDHEAVYLOADBYANALYZINGONOFFVIBRATIONSIGNALS．THEPARAMETEROFPULSEENERGYANDPULSETIMESARECONSTRUCTED，WHICHISUSEDTOSOLVETHESTATEQUALITYTESTFORROTARYFLAT．SETUPTHESTATEQUALITYPATTERNRECOGNITIONSYSTEMBASEDONBPNEURALNETWORK．THEPERFORMANCETESTANDEVALUATIONONSTATEQUALITYOFROTARYFLATALEPRIMARILYREALIZED．THEMETHODHASCERTAINAPPLICATIONFOREGROUNDANDHIGHPRACTICALITYVALUE．KEYWORDSROTARYPLAT，STATEQUALITYTEST,PULSEENERGY,BPNEURALNETWORK

簡(jiǎn)介：工學(xué)碩士學(xué)位論文航天器姿態(tài)動(dòng)力學(xué)系統(tǒng)魯棒自適應(yīng)控制方法研究郭金花哈爾濱工業(yè)大學(xué)2008年6月CLASSIFIEDINDEXTP273UDC68152DISSERTATIONFTHEMASTER’SDEGREEINENGINEERINGROBUSTADAPTIVECONTROLALGITHMSRESEARCHFTHESYSTEMOFSPACECRAFTATTITUDEDYNAMICSCIDATEGUOJINHUASUPERVISPROFSONGSHENMINACADEMICDEGREEAPPLIEDFMASTEROFENGINEERINGSPECIALITYCONTROLSCIENCEENGINEERINGAFFILIATIONDEPTCONTROLSCIENCEENGINEERINGDATEOFDEFENCEJUNE2008DEGREECONFERRINGINSTITUTIONHARBININSTITUTEOFTECHNOLOGY

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簡(jiǎn)介：洳專J、碩士學(xué)位論文論文題目照丞電連接墨綾金廑力受靠性建槿叢統(tǒng)讓驗(yàn)逛學(xué)科專業(yè)扭越遞鹽厘理論所在學(xué)院扭撼皇篚近王程堂瞳浙江大學(xué)碩士學(xué)位論文ABSTRACTINTHISMASTERDISSERTATIONTOOKMODELYLLP1419ELECTRICALCONNECTORASTHEOBJECTBYANALYZINGTHEFAILUREMECHANISMUNDERTEMPERATUREANDDBMFIONSTRESSES，BUILTTHERELIABILITYMODEL，ANDDEEPLYRESEARCHEDDEMONSTRATIONOFTHEMODELFIRSTLYINTRODUCEDTHESIGNIFICANCEOFRELIABILITYRESEARCH，BRIEFLYSTATEDTHEDEVELOPINGHISTORYANDCURRENTSITUATIONOFRELIABILITYENGINEERINGINTRODUCEDTHEMETHODSANDTRENDSOFRELIABILITYSTATISTICALANALYSIS，ANDREVIEWEDELECTRICALCONNETCTORS’CURRENTRESEARCHSITUATIONANDEXISTINGPROBLEMSSECONDLYTHROUGHANALYZINGTHEFAILUREMECHANISMOFELECTRICALCONNECTORSUNDERTEMPERATUREANDVIBRATIONSTRESSES，EDUCEDTHEFAILUREPHYSIESEQUATIONMADEOUTTHEFAILURELIFEDISTRIBUTIONOFELECTRICALCONNECTORS，LAIDAFOUNDATIONFORWORKINGOUTELECTRICALCONNECTO巧’ACCELERATEDLIFETESTUNDERMULTIPLESTRESSESTHIRDLYBASEDONCOMPARINGSEVERALTESTDESIGNMETHODS，DETERMINEDTHECOMBINEDSCHEMEOFTESTINGSTRESSESBYTHEUNIFORMLYTESTTHEORYONTHEPRINCIPLEOFKEEPINGTHEFAILUREMECHANISMUNCHANGED，AFTERTHEACCELERATEGOALWASSATISFIEDPROPOSEDATESTINGPLANBYUSINGTHEMONTECARLOMETHOD，SIMULATEDANDEVALUATODTHEUNIFORMTESTINGPLANANDCOMPREHENSIVETESTPLANBYCOMPARINGTHEIRMEANVARIANCESANDSTANDARDDISTANCEVALUESOFESTIMATEDMEDIANLIVES，PROVEDTHATTHEUNIFORMTESTINGPLANISFEASIBLEFOTMHLYBYUSINGTHEPROBABILITYPAPERANDVANMONFFORTMETHODITWASDEMONSTRATEDTHATTHEFAILURELIFEDISTRIBUTIONOFELECTRICALCONNECTORSISWBIBULLMODELBYMAKINGUSEOFTHEMAXIMUMLIKELIHOODESTIMATIONESTIMATEDTHEDISTRIBUTIONPARAMETERSOFTHEMODELUNDERALLSTRESSLEVELS，ANDVERIFIEDTHATTHEACCELERATEDLIFETESTINGKEEPSTHEFAILUREMECHANISMOFTHEELECTRICALCONNECTORSUNCHANGEDFIFTHLYAFTERLOGARITHMSTRANSITIONTHEACCELERATEDLIFEEQUATIONISCHANGEDFROMEYDNGWEIBUUMODELTOLINEAREXTREMEMODELBYUSINGLEASTSQUAREESTIMATIONESTIMATEDTHEPARAMETERSOFTHELINEARMODEL，BASEDONANALYSISOFVARIANCE，INVOKEDSIGNIFICANCETESTINGOFTHEREGRESSIONEQUATIONANDREGRESSIONPARAMETERS，AFTERANALYZINGTHERESIDUALSCATTERCHART，VERIFIEDTHERELIABILITYSTATISTICALMODELOFELECTRICALCONNECTORSISLINEAREXTREMEMODELFINALLYBYUSINGTHEMODEL，ASSESSEDTHERELIABILITYLEVELSOFTHEELECTRICALCONNECTORSSTATISTICALLYANALYZEDELECTRICALCONNECTORS’ACCELERATEDLIFETESTDATAANDOBTAINEDTHEELECTRICALCONNECTORRELIABILITYESTIMATEDCHARACTERISTICVALUESEVENTUALLYGAVEAEONCLASIONOFTHERESEARCHCONTENTOFTHEENTIREMASTERDISSERTATIONANDPROPOSEDTHEFURTHERRESEARCHCONTENTOFELECTRICALCONNECTORRELIABJLI吼KEYWORDSELECTRICALCONNECTORMULTIPLESTRESSES，RELIABILITYSTATISTICALMODEL，TESTDEMONSTRATIONLI

簡(jiǎn)介：上海交通大學(xué)博士學(xué)位論文航天器熱網(wǎng)絡(luò)理論及其在熱控設(shè)計(jì)中的應(yīng)用研究姓名李鵬申請(qǐng)學(xué)位級(jí)別博士專業(yè)工程熱物理指導(dǎo)教師程惠爾20070401角系數(shù)實(shí)現(xiàn)數(shù)據(jù)共享，從而大大減小了計(jì)算工作量。其次，進(jìn)行了空間對(duì)接機(jī)構(gòu)熱分析。在單機(jī)設(shè)備形狀的規(guī)則化處理和機(jī)構(gòu)輻射換熱的近似假定的基礎(chǔ)上，建立了對(duì)接機(jī)構(gòu)熱分析的物理模型，并進(jìn)行了節(jié)點(diǎn)劃分，利用熱網(wǎng)絡(luò)理論，建立了空間對(duì)接機(jī)構(gòu)熱分析的數(shù)學(xué)模型，利用龍格一庫塔法計(jì)算得到對(duì)接機(jī)構(gòu)在軌溫度。了解了對(duì)接機(jī)構(gòu)各構(gòu)件周期溫度的變化規(guī)律和對(duì)接機(jī)構(gòu)溫度場(chǎng)的分布特點(diǎn)，著重分析了收攏情況下，對(duì)接機(jī)構(gòu)外部構(gòu)件、框架構(gòu)件以及內(nèi)部構(gòu)件表面輻射特性對(duì)在軌溫度的影響，為對(duì)接機(jī)構(gòu)熱控涂層的選擇提供了重要的參考。計(jì)算結(jié)果表明只靠熱控涂層的熱控措施很難保證空間對(duì)接機(jī)構(gòu)的溫度滿足設(shè)計(jì)要求，還需要采用多層隔熱材料包覆或者電加熱措施等。第三，進(jìn)行了空間用多層打孔隔熱材料熱計(jì)算模型及應(yīng)用研究。多層隔熱材料是航天器被動(dòng)熱控制的最基本手段之一，為了盡快地使材料排氣，減小殘余氣體導(dǎo)熱的影響，提高隔熱性能，通常采用打孔的方法。分析了空間多層打孔隔熱材料中導(dǎo)熱和輻射的復(fù)合傳熱問題，在一定假設(shè)的基礎(chǔ)上，建立了反射屏穩(wěn)態(tài)、瞬態(tài)溫度計(jì)算模型和投射輻射數(shù)值分析模型。分析瞬態(tài)溫度計(jì)算結(jié)果，明確了空間多層打孔隔熱材料在軌溫度分布特點(diǎn)。分析在陰影區(qū)的惡劣環(huán)境下，多層打孔隔熱材料的穩(wěn)態(tài)計(jì)算結(jié)果，明確了幾何參數(shù)、表面特性參數(shù)對(duì)材料熱性能的影響。該研究對(duì)提高材料的隔熱效果，實(shí)現(xiàn)材料的優(yōu)化設(shè)計(jì)具有積極的指導(dǎo)意義。第四，對(duì)接機(jī)構(gòu)初步熱控設(shè)計(jì)及熱分析。借鑒國(guó)內(nèi)外航天器熱控設(shè)計(jì)經(jīng)驗(yàn)，首先針對(duì)對(duì)接機(jī)構(gòu)結(jié)構(gòu)和工作特點(diǎn)，對(duì)不同位置處的設(shè)備構(gòu)件，進(jìn)行不同形式的多層隔熱材料包覆，提出了被動(dòng)熱控方案，然后在熱分析的基礎(chǔ)上，在部分構(gòu)件上施加了電加熱的主動(dòng)熱控措施，并確定了加熱功率。對(duì)有熱控情況下，對(duì)接機(jī)構(gòu)處于自主飛行階段和對(duì)接階段，不同軌道艙體邊界條件的多種工況下計(jì)算結(jié)果分析，表明采用了初步的熱控方案包括被動(dòng)、主動(dòng)熱控措施后，對(duì)接機(jī)構(gòu)各構(gòu)件的溫度滿足設(shè)計(jì)要求。不同邊界條件下的溫度數(shù)據(jù)可為對(duì)接機(jī)構(gòu)和航天器艙體更有效的連接提供有意義的參考。第五，進(jìn)行了太陽電池陣在軌熱分析，并通過地面熱真空試驗(yàn)對(duì)熱計(jì)算模型進(jìn)行了驗(yàn)證。航天器上大型外懸結(jié)構(gòu)對(duì)在軌溫度非常敏感，以太陽電池陣為例，數(shù)值模擬得到其在軌溫度的分布，分析了電池陣表面輻射特性和軌道高度對(duì)太陽電池陣溫度的影響。該熱分析Ⅱ

簡(jiǎn)介：碩士學(xué)位論文碩士學(xué)位論文再入航天器結(jié)構(gòu)設(shè)計(jì)與優(yōu)化方法研究THERESEARCHONDESIGNOPTIMIZATIONMETHODOFREENTRYVEHICLESTRUCTURE馮韶偉馮韶偉2010年7月CLASSIFIEDINDEXV4482UDC62978DISSERTATIONFTHEMASTERDEGREEINENGINEERINGTHERESEARCHONTHEDESIGNOPTIMIZATIONMETHODOFREENTRYVEHICLESTRUCTURECIDATEFENGSHAOWEISUPERVISPROFSUNZHAOWEIACADEMICDEGREEAPPLIEDFMASTEROFENGINEERINGSPECIALITYSPACECRAFTDESIGNAFFILIATIONRESEARCHCENTEROFSATELLITETECHDATEOFDEFENCEJULY2010DEGREECONFERRINGINSTITUTIONHARBININSTITUTEOFTECHNOLOGY

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簡(jiǎn)介：大連理工大學(xué)博士學(xué)位論文復(fù)合材料結(jié)構(gòu)隨機(jī)振動(dòng)的虛擬激勵(lì)法及在航空航天領(lǐng)域的應(yīng)用姓名戴新進(jìn)申請(qǐng)學(xué)位級(jí)別博士專業(yè)工程力學(xué)指導(dǎo)教師林家浩陳浩然20070601復(fù)合材料結(jié)構(gòu)隨機(jī)振動(dòng)的虛擬激勵(lì)法及在航空航天領(lǐng)域的應(yīng)用3研究飛機(jī)對(duì)大氣紊流響應(yīng)的主要方法是隨機(jī)振動(dòng)功率譜法。用高效、精確的分析方法計(jì)算不同飛行環(huán)境下飛機(jī)的響應(yīng)，以預(yù)測(cè)飛機(jī)疲勞壽命和可靠度等是航空工程領(lǐng)域研究熱點(diǎn)。本文在考慮了二維平面流中簡(jiǎn)諧振動(dòng)平板產(chǎn)生的非定常力基礎(chǔ)上，又按照虛擬激勵(lì)法的特點(diǎn)同時(shí)考慮了豎向簡(jiǎn)諧風(fēng)的影響，進(jìn)而研究了復(fù)合材料二維機(jī)翼的大氣紊流響應(yīng)。隨機(jī)激勵(lì)譜選用了DRYDEN紊流頻譜模型。結(jié)果表明，在處理二維機(jī)翼在大氣紊流響應(yīng)的隨機(jī)問題中，基于簡(jiǎn)諧響應(yīng)分析的虛擬激勵(lì)法不但是精確算法，而且效率非常高，具有很大的實(shí)用優(yōu)勢(shì)。發(fā)展這一方法對(duì)于該領(lǐng)域的數(shù)值計(jì)算是很有價(jià)值的。4計(jì)算流體動(dòng)力學(xué)CFD是研究流體動(dòng)力學(xué)的有力工具。本文為計(jì)算機(jī)翼顫振，抖陣分析中的氣動(dòng)參數(shù)，首次使用雷諾平均湍流模型對(duì)二維翼型截面的顫振導(dǎo)數(shù)進(jìn)行了求解?；贒ILSUN等最新提出的CFD網(wǎng)格控制算法以及所建立的數(shù)值風(fēng)洞，計(jì)算了結(jié)構(gòu)簡(jiǎn)諧運(yùn)動(dòng)下的氣動(dòng)力，并識(shí)別了湍流場(chǎng)中NACA0012翼型的顫振導(dǎo)數(shù)。將由此得到的顫振導(dǎo)數(shù)和氣動(dòng)力應(yīng)用到大氣紊流引起的隨機(jī)振動(dòng)計(jì)算中，并將計(jì)算結(jié)果與基于THEODORSEN函數(shù)得出的響應(yīng)解析解進(jìn)行比較，得到了相當(dāng)滿意的一致。本文計(jì)算的CFD氣動(dòng)參數(shù)充分考慮了氣體的分子粘性和紊流祜性，其作用相當(dāng)于附加阻尼，因此比THEODOSON函數(shù)方法限制更少、應(yīng)用范圍更廣，而且在此基礎(chǔ)上還可以考慮三維流和可壓縮性。因此本文實(shí)旄的基于CFD的氣動(dòng)力計(jì)算方法具有廣闊的應(yīng)用前景，將成為應(yīng)用虛擬激勵(lì)法于航空航天結(jié)構(gòu)時(shí)確定氣動(dòng)參數(shù)的有力工具。可以說，這一成功的嘗試為隨機(jī)振動(dòng)方法更廣泛地應(yīng)用于航空航天工程走出了很重要的一步。關(guān)鍵詞復(fù)合材料；隨機(jī)振動(dòng)；虛擬激勵(lì)法；粘彈性阻尼；大氣紊流；FFD

簡(jiǎn)介：隨著高精度航天器的快速發(fā)展，航天器對(duì)于空間力學(xué)環(huán)境的要求越來越苛刻。然而，作為一類典型的姿態(tài)控制部件，單框架控制力矩陀螺（SGCMG）工作時(shí)不可避免會(huì)產(chǎn)生微振動(dòng)，進(jìn)而降低航天器平臺(tái)的指向精度和穩(wěn)定度。為了減小SGCMG對(duì)空間任務(wù)的干擾，本文針對(duì)SGCMG開展了微振動(dòng)隔離技術(shù)的研究，提出了一種新型的被動(dòng)隔振裝置，仿真分析并實(shí)驗(yàn)驗(yàn)證了該裝置的隔振性能。論文的主要工作如下分析了SGCMG的微振動(dòng)擾動(dòng)輸出特性，并有針對(duì)性地提出了一種低剛度被動(dòng)隔振方法，設(shè)計(jì)了一種新型的彈性粘彈性復(fù)合結(jié)構(gòu)被動(dòng)隔振裝置。該裝置主要由彈性支承單元和粘彈性阻尼單元組成。測(cè)量了定溫變頻條件下粘彈材料的動(dòng)態(tài)性能，采用標(biāo)準(zhǔn)流變模型和分?jǐn)?shù)導(dǎo)數(shù)模型描述材料頻變特性，結(jié)合實(shí)驗(yàn)數(shù)據(jù)辨識(shí)了模型參數(shù)。結(jié)果表明相比于標(biāo)準(zhǔn)流變模型，分?jǐn)?shù)導(dǎo)數(shù)模型的描述精度更高，最合理的擬合結(jié)果為分?jǐn)?shù)導(dǎo)數(shù)五參數(shù)模型。建立了SGCMG隔振系統(tǒng)參數(shù)化有限元模型，分析了隔振系統(tǒng)的動(dòng)力學(xué)特性和隔振性能。仿真結(jié)果表明該被動(dòng)隔振裝置能有效隔離各自由度50HZ以上的擾動(dòng)輸入，并且粘彈材料的阻尼對(duì)共振區(qū)域響應(yīng)有良好抑制作用。開展了SGCMG隔振裝置的結(jié)構(gòu)靈敏度分析，得到結(jié)構(gòu)參數(shù)對(duì)隔振系統(tǒng)固有頻率的影響趨勢(shì)，在此基礎(chǔ)上開展了隔振裝置的結(jié)構(gòu)優(yōu)化設(shè)計(jì)。優(yōu)化前后對(duì)比分析可知優(yōu)化后，各自由度有效隔振的頻率范圍擴(kuò)展了1346HZ以上；在SGCMG的工作轉(zhuǎn)速下，六個(gè)自由度上的擾動(dòng)傳遞率均小于25DB，相比優(yōu)化前降低了1688％以上。搭建了微振動(dòng)測(cè)量系統(tǒng)，開展了SGCMG隔振裝置的地面驗(yàn)證實(shí)驗(yàn)，測(cè)量了工作轉(zhuǎn)速下裝置的隔振性能。實(shí)驗(yàn)結(jié)果表明該隔振裝置能有效隔離SGCMG六個(gè)自由度上的擾動(dòng)，驗(yàn)證了該隔振方法的正確性和隔振裝置的合理性。