本文選題：星箭結構 + 蜂窩夾芯板　； 參考：《東南大學》2016年碩士論文

【摘要】：航天器在發(fā)射和服役時面臨復雜的振動和噪聲動力學環(huán)境,而準確的動力學聲振環(huán)境預示是指導航天器總體設計、結構設計、以及地面試驗方案與試驗條件制定的重要依據。本文以星箭結構為研究對象,重點開展三方面的研究工作：研究星箭結構的動力學建模方法,建立能較為準確反映結構動力學特性的模型；研究星箭結構的聲-固耦合動響應預示方法,揭示聲振環(huán)境下的動響應規(guī)律；研究整流罩結構的聲傳遞特性,為星箭結構的優(yōu)化設計以及減振降噪設計提供指導。準確的動力學模型是后續(xù)聲-固耦合響應預示的基礎。首先開展星箭結構中典型的包帶連接的等效建模方法研究,推導包帶連接結構在不同預緊力下的軸向剛度,并探討包帶連接結構軸向剛度對星箭結構固有特性的影響。然后針對運載火箭整流罩中常用的蜂窩夾芯結構,分別采用等效板理論和三明治夾芯板理論進行等效建模,分析蜂窩夾芯板和等效板在平面波作用下考慮聲-固耦合時的傳聲損失和聲輻射響應,研究等效模型在動力學分析時的精度與效率,從而探索一種適用于大型航天器結構聲學分析以及動響應分析的等效建模方法。準確的聲-固耦合動響應預示是后續(xù)動強度評估的基礎。基于FEM-BEM法分別進行隨機振動激勵、噪聲激勵以及隨機振動／噪聲聯合作用等復合激勵下星箭結構的聲-固耦合動響應預示研究。給出不同激勵下的聲振響應規(guī)律,探討不同激勵成分對結構動響應的貢獻,并重點研究耦合效應以及包帶連接剛度對結構固有特性和動響應的影響。準確的星箭力學環(huán)境是進行星箭結構動響應預示和聲學優(yōu)化設計的基礎。針對運載火箭整流罩典型薄壁圓柱殼結構,基于Love理論給出薄壁圓柱殼的聲傳遞表達式,分析柱狀聲波作用下的聲傳遞損失以及聲輻射響應,探討整流罩壁厚、肋骨數目以及飛行角度對整流罩傳聲損失以及聲輻射的影響�；诼晜鬟f向量法進行整流罩結構的聲學板塊貢獻量分析,重點分析場點處聲壓響應在各頻帶內的分布,以及在特定頻率處結構各板塊的貢獻量。此研究對結構的優(yōu)化設計以及減振降噪設計具有一定的指導作用。
[Abstract]:Spacecraft are faced with complex dynamic environment of vibration and noise during launch and service. Accurate prediction of dynamic acoustic environment is an important basis to guide spacecraft overall design, structural design, ground test scheme and test conditions. In this paper, the star-arrow structure is taken as the research object, and the research work is focused on three aspects: the dynamic modeling method of the star-arrow structure is studied, and the model which can accurately reflect the dynamic characteristics of the structure is established; The prediction method of acousto-solid coupling dynamic response of star-arrow structure is studied to reveal the law of dynamic response in acousto-vibration environment, and the acoustic transfer characteristics of fairing structure are studied to provide guidance for the optimization design of star-arrow structure and the design of vibration and noise reduction. Accurate dynamic model is the basis of prediction of acousto-solid coupling response. In this paper, the equivalent modeling method of the typical envelope connection in star-arrow structure is studied, the axial stiffness of the envelope connection structure under different pretightening forces is deduced, and the influence of the axial stiffness on the inherent characteristics of the star-arrow structure is discussed. Then the equivalent plate theory and sandwich theory are used to model the honeycomb sandwich core structure commonly used in the fairing of launch vehicle. The sound transmission loss and acoustic radiation response of honeycomb sandwich panels and equivalent plates considering acousto-solid coupling under plane wave are analyzed. The accuracy and efficiency of the equivalent model in dynamic analysis are studied. Thus an equivalent modeling method suitable for structural acoustic analysis and dynamic response analysis of large spacecraft is explored. Accurate prediction of acousto-solid coupling dynamic response is the basis of subsequent dynamic strength evaluation. Based on the FEM-BEM method, the prediction of acousto-solid coupling dynamic responses of star-arrow structures under random vibration excitation, noise excitation and combined random vibration / noise excitation is studied respectively. In this paper, the law of acoustic and vibration response under different excitations is given, and the contribution of different excitation components to the dynamic response of the structure is discussed. The coupling effect and the influence of the coupling stiffness on the natural characteristics and dynamic response of the structure are studied. Accurate mechanical environment of star-arrow is the basis of prediction of dynamic response of star-arrow structure and acoustical optimization design. Aiming at the typical thin-walled cylindrical shell structure of the fairing of launch vehicle, the expression of acoustic transfer of thin-walled cylindrical shell is given based on Love theory. The sound transfer loss and acoustic radiation response under the action of cylindrical acoustic wave are analyzed, and the wall thickness of the fairing is discussed. The influence of the number of ribs and the flight angle on the sound transmission loss and sound radiation of the fairing. Based on the acoustic transfer vector method, the acoustic plate contribution of the fairing structure is analyzed, and the distribution of the acoustic pressure response at the field point in each frequency band and the contribution of each plate in the structure at a specific frequency are analyzed. This research has certain guiding function to the optimization design of structure and the design of vibration and noise reduction.
【學位授予單位】：東南大學
【學位級別】：碩士
【學位授予年份】：2016
【分類號】：V414

【參考文獻】

相關期刊論文 前10條

1 李彥斌;張鵬;鄒元杰;吳邵慶;費慶國;;隨機基礎激勵下承力筒—蒙皮結構的聲—固耦合分析[J];宇航學報;2015年02期

2 姜東;吳邵慶;費慶國;韓曉林;;蜂窩夾層復合材料不確定性參數識別方法[J];振動與沖擊;2015年02期

3 姜東;江智遠;費慶國;韓曉林;;考慮膠層的蜂窩夾層復合材料動態(tài)特性[J];東南大學學報(自然科學版);2013年05期

4 夏齊強;陳志堅;;殼間新連接結構形式下雙層圓柱殼聲振性能分析[J];噪聲與振動控制;2013年02期

5 任樹偉;辛鋒先;盧天健;;蜂窩層芯夾層板結構振動與傳聲特性研究[J];力學學報;2013年03期

6 邱吉寶;張正平;李海波;;航天器與運載火箭耦合分析相關技術研究進展[J];力學進展;2012年04期

7 鄒元杰;韓增堯;張瑾;;航天器全頻域力學環(huán)境預示技術研究進展[J];力學進展;2012年04期

8 潘忠文;曾耀祥;廉永正;邢譽峰;;運載火箭結構動力學模擬技術研究進展[J];力學進展;2012年04期

9 黃文虎;曹登慶;韓增堯;;航天器動力學與控制的研究進展與展望[J];力學進展;2012年04期

10 馬興瑞;韓增堯;鄒元杰;丁繼鋒;;航天器力學環(huán)境分析與條件設計研究進展[J];宇航學報;2012年01期

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