【摘要】：隨著航天技術(shù)的發(fā)展，人類并不滿足于在太空作短暫的旅游，越來越多的衛(wèi)星、空間站等新航天器不斷被送入太空。航天器在發(fā)射過程中經(jīng)歷著復(fù)雜嚴(yán)酷的動(dòng)力學(xué)環(huán)境。同時(shí)，為了有效傳遞運(yùn)載火箭的推力，，傳統(tǒng)的星箭連接結(jié)構(gòu)采用剛度很大的錐殼適配器，這就導(dǎo)致衛(wèi)星受到多種低中高頻的振動(dòng)和沖擊載荷的作用。劇烈的振動(dòng)會(huì)造成衛(wèi)星結(jié)構(gòu)疲勞破壞、敏感元件失效。為了減少或抑制這些載荷對衛(wèi)星及其部件的作用，國內(nèi)外航天界通常采用加固衛(wèi)星結(jié)構(gòu)或?qū)π阅苤笜?biāo)達(dá)不到要求的部件進(jìn)行單獨(dú)隔振。但是，這些措施會(huì)增加衛(wèi)星的無用質(zhì)量并擠占運(yùn)載器有限的發(fā)射重量和空間。二十世紀(jì)九十年代提出的整星隔振思想為降低運(yùn)載火箭傳遞到衛(wèi)星上的各種振動(dòng)和沖擊載荷提供了高效適用的方法。 本文對提出的粘彈性約束阻尼桁架整星被動(dòng)隔振器及基于Volterra泛函級數(shù)理論對整星隔振系統(tǒng)的非線性特性作了深入、系統(tǒng)的研究。本文主要研究了以下幾個(gè)方面的內(nèi)容： 針對傳統(tǒng)的有效載荷適配器，提出了替代式粘彈性約束阻尼桁架隔振器。研究了整星隔振器中粘彈性阻尼結(jié)構(gòu)的動(dòng)態(tài)行為，并設(shè)計(jì)了粘彈性材料性能測試裝置。通過實(shí)驗(yàn)對模型參數(shù)進(jìn)行了辨識(shí)，討論了阻尼結(jié)構(gòu)剛度隨頻率和阻尼面積的變化規(guī)律，為基于粘彈性材料的粘彈性約束阻尼桁架隔振器的研究奠定了基礎(chǔ)。 基于Volterra泛函級數(shù)理論，以本文所研究隔振器的實(shí)際模型參數(shù)為基礎(chǔ)，對具有剛度非線性特征的非線性系統(tǒng)的五階廣義頻率響應(yīng)函數(shù)進(jìn)行了推導(dǎo)，并分析了其頻響特性。在不同輸入激勵(lì)下，對非線性系統(tǒng)的輸出頻率響應(yīng)特性進(jìn)行了研究，并將用Volterra泛函級數(shù)方法得到的響應(yīng)特性與諧波平衡法進(jìn)行了比較，驗(yàn)證了理論分析結(jié)果的正確性。 利用輸出頻率響應(yīng)函數(shù)對基礎(chǔ)位移激勵(lì)下，具有剛度非線性和阻尼非線性的非線性隔振系統(tǒng)的相對位移輸出響應(yīng)進(jìn)行了研究，分析了非線性阻尼參數(shù)對輸出響應(yīng)的影響，并基于Volterra泛函級數(shù)理論對這一結(jié)果給出了理論上的證明。在此基礎(chǔ)上，分析了非線性剛度參數(shù)和非線性阻尼參數(shù)在不同的頻率范圍對絕對位移傳遞率的影響。 建立了整星隔振系統(tǒng)的非線性動(dòng)力學(xué)模型，在基礎(chǔ)位移激勵(lì)下，采用輸出頻率響應(yīng)函數(shù)分析了一階共振區(qū)和二階共振區(qū)及其它非共振區(qū)系統(tǒng)的非線性表征參數(shù)對從隔振器底部到衛(wèi)星的振動(dòng)傳遞率的影響。基于改進(jìn)的自適應(yīng)蟻群算法對提出的粘彈性約束阻尼桁架隔振器進(jìn)行了結(jié)構(gòu)參數(shù)優(yōu)化，并對隔振性能進(jìn)行了有限元分析，同時(shí)對添加整星隔振平臺(tái)的全箭動(dòng)特性進(jìn)行了仿真研究。 設(shè)計(jì)加工制造粘彈性約束阻尼桁架整星被動(dòng)隔振平臺(tái)，并對隔振平臺(tái)原理性樣機(jī)進(jìn)行了實(shí)驗(yàn)研究。將仿真結(jié)果與實(shí)驗(yàn)結(jié)果對比，驗(yàn)證本文所提出的約束粘彈性阻尼桁架隔振平臺(tái)的有效性，并通過實(shí)驗(yàn)分析了整星隔振系統(tǒng)非線性因素對輸出響應(yīng)和共振頻率的影響，同時(shí)也驗(yàn)證了本文基于Volterra泛函級數(shù)法理論分析的正確性。
[Abstract]:With the development of space technology, more and more satellites, space stations and other new spacecrafts are constantly sent into space. Spacecrafts undergo a complex and harsh dynamic environment during the launch process. At the same time, in order to effectively transmit the thrust of launch vehicles, the traditional spacecraft-rocket connection structure uses stiffness. In order to reduce or restrain the effect of these loads on satellites and their components, the aerospace circles at home and abroad usually adopt reinforcement of satellite structures or performance indicators. These measures, however, will increase the useless mass of the satellite and squeeze the limited launch weight and space of the carrier. The idea of Whole-Satellite vibration isolation proposed in the 1990s provides an efficient and applicable method for reducing the various vibration and impact loads transmitted to the satellite by the carrier rocket.
In this paper, the viscoelastic constrained damping truss passive vibration isolator and the nonlinear characteristics of the whole satellite vibration isolation system based on Volterra functional series theory are studied systematically.
An alternative viscoelastic constrained damping truss isolator is proposed for the traditional payload adapter. The dynamic behavior of viscoelastic damped structure in the whole spacecraft isolator is studied, and a testing device for the performance of viscoelastic materials is designed. The variation law lays a foundation for the study of viscoelastic constrained damping truss isolators based on viscoelastic materials.
Based on the Volterra functional series theory and the actual model parameters of the isolator studied in this paper, the fifth-order generalized frequency response function of the nonlinear system with stiffness and nonlinearity is derived and its frequency response characteristics are analyzed. The response characteristics obtained by the Volterra functional series method are compared with those obtained by the harmonic balance method, and the correctness of the theoretical analysis results is verified.
The output displacement response of a nonlinear vibration isolation system with stiffness nonlinearity and damping nonlinearity under displacement excitation is studied by using the output frequency response function. The influence of nonlinear damping parameters on the output response is analyzed. The result is proved theoretically based on Volterra functional series theory. On this basis, the influence of nonlinear stiffness and damping parameters on absolute displacement transfer rate in different frequency range is analyzed.
The nonlinear dynamic model of the whole satellite isolation system is established. The output frequency response function is used to analyze the influence of the nonlinear characterization parameters of the first-order resonance region and the second-order resonance region and other non-resonance regions on the vibration transmission rate from the base of the isolator to the satellite. Based on the improved adaptive ant colony algorithm The structural parameters of the viscoelastic constrained damping truss isolator are optimized, and the vibration isolation performance is analyzed by finite element method. The full rocket dynamic characteristics of the isolation platform are simulated.
The Whole-Satellite passive vibration isolation platform with viscoelastic constrained damping truss is designed and manufactured, and the principle prototype of the platform is experimentally studied. The effectiveness of the platform is verified by comparing the simulation results with the experimental results, and the nonlinear factors of the Whole-Satellite vibration isolation system are analyzed through experiments. The effect of output response and resonance frequency also verifies the validity of the theoretical analysis based on Volterra functional series method.
【學(xué)位授予單位】：哈爾濱工業(yè)大學(xué)
【學(xué)位級別】：博士
【學(xué)位授予年份】：2014
【分類號】：TB535.1;V414

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