發(fā)布時(shí)間：2018-05-02 21:34

  本文選題：直升機(jī)座椅 + 磁流變阻尼器��； 參考：《哈爾濱工業(yè)大學(xué)》2014年碩士論文

【摘要】：直升機(jī)飛行過(guò)程中產(chǎn)生的振動(dòng)以及墜落時(shí)受到的沖擊是影響飛行員身體健康和生命安全的重要因素。在座椅懸架中加裝磁流變阻尼器，并采用合適的控制方法進(jìn)行控制是改善直升機(jī)座椅系統(tǒng)隔振性能的一種便捷有效方式。本文以減小振動(dòng)、緩和沖擊為目標(biāo)，利用磁流變阻尼器和緩沖器配合作用，采用線性二次型最優(yōu)控制算法，建立了磁流變阻尼器半主動(dòng)控制直升機(jī)座椅系統(tǒng)，并進(jìn)行仿真和實(shí)驗(yàn)研究，結(jié)果表明了該設(shè)計(jì)的合理性和有效性。 建立了磁流變阻尼器的雙曲正切模型、BP神經(jīng)網(wǎng)絡(luò)模型和自適應(yīng)神經(jīng)模糊推理系統(tǒng)模型以及磁流變阻尼器控制器的BP神經(jīng)網(wǎng)絡(luò)模型和自適應(yīng)神經(jīng)模糊推理系統(tǒng)模型。測(cè)試了實(shí)際磁流變阻尼器的動(dòng)力學(xué)特性，根據(jù)測(cè)試所得數(shù)據(jù)，對(duì)磁流變阻尼器模型及其控制器模型進(jìn)行了參數(shù)識(shí)別和訓(xùn)練，選擇綜合性能最佳的磁流變阻尼器模型及磁流變阻尼器控制器模型構(gòu)建了磁流變阻尼器系統(tǒng)模型。檢驗(yàn)了磁流變阻尼器系統(tǒng)模型對(duì)實(shí)測(cè)數(shù)據(jù)的擬合能力，驗(yàn)證了所建模型的可靠性。 針對(duì)直升機(jī)座椅系統(tǒng)的工作環(huán)境和隔振要求，設(shè)計(jì)了直升機(jī)座椅懸架結(jié)構(gòu)，確定了磁流變阻尼器和緩沖器的安裝位置，建立了直升機(jī)座椅系統(tǒng)的數(shù)學(xué)模型。分別采用天棚阻尼控制算法和線性二次型最優(yōu)控制算法設(shè)計(jì)了直升機(jī)座椅系統(tǒng)的控制器，采用動(dòng)力學(xué)仿真分析方法比較二者的位移及加速度控制效果，選擇效果最佳者作為直升機(jī)座椅系統(tǒng)的控制器。 在Simulink環(huán)境下建立了被動(dòng)控制、主動(dòng)控制及磁流變阻尼器半主動(dòng)控制的直升機(jī)座椅系統(tǒng)模型，分別在階躍位移激勵(lì)、正弦位移激勵(lì)和脈沖力激勵(lì)下對(duì)座椅系統(tǒng)的減振及抗沖擊性能進(jìn)行仿真分析。以座椅懸架承載質(zhì)量的加速度為評(píng)價(jià)指標(biāo)，對(duì)比了半主動(dòng)控制與其他控制方法的作用效果，證明了半主動(dòng)控制能夠顯著地減小振動(dòng)和沖擊，并分析了座椅系統(tǒng)參數(shù)變化對(duì)半主動(dòng)控制效果的影響。 根據(jù)座椅系統(tǒng)模型搭建了直升機(jī)座椅系統(tǒng)控制性能實(shí)驗(yàn)臺(tái)，基于xPC Target實(shí)時(shí)控制技術(shù)，測(cè)定了座椅懸架承載質(zhì)量加速度在階躍位移激勵(lì)下的響應(yīng)。實(shí)驗(yàn)結(jié)果表明所設(shè)計(jì)的磁流變阻尼器半主動(dòng)控制座椅系統(tǒng)具有明顯的減振效果，為直升機(jī)座椅系統(tǒng)設(shè)計(jì)提供了指導(dǎo)。
[Abstract]:The vibration generated by the helicopter during flight and the impact during the fall are the important factors affecting the health and life safety of the pilot. It is a convenient and effective way to improve the vibration isolation performance of helicopter seat system by installing Mr damper and adopting appropriate control method in seat suspension. The aim of this paper is to reduce vibration and mitigate impact. By using the cooperation of magneto-rheological damper and buffer, a semi-active control helicopter seat system with magneto-rheological damper is established by using linear quadratic optimal control algorithm. The simulation and experimental results show that the design is reasonable and effective. The hyperbolic tangent model of magnetorheological damper, the BP neural network model and the adaptive neural fuzzy inference system model, as well as the BP neural network model and the adaptive neural fuzzy inference system model of the magnetorheological damper controller are established. The dynamic characteristics of the actual Mr damper are tested. According to the measured data, the model of Mr damper and its controller model are identified and trained. The magneto-rheological damper model and the magnetorheological damper controller model are selected to construct the magneto-rheological damper system model. The fitting ability of the model of Mr damper system to the measured data is tested, and the reliability of the model is verified. Aiming at the working environment and vibration isolation requirements of helicopter seat system, the structure of helicopter seat suspension is designed, the installation position of Mr damper and buffer is determined, and the mathematical model of helicopter seat system is established. The controller of helicopter seat system is designed by using ceiling damping control algorithm and linear quadratic optimal control algorithm respectively. The displacement and acceleration control effects of the two methods are compared by dynamic simulation analysis. Select the most effective as the helicopter seat system controller. The helicopter seat system models of passive control, active control and magneto-rheological damper semi-active control are established in Simulink environment, which are excited by step displacement, respectively. The vibration absorption and shock resistance of seat system are simulated and analyzed under sinusoidal displacement excitation and impulse force excitation. With the acceleration of seat suspension load mass as the evaluation index, the effects of semi-active control and other control methods are compared, and it is proved that semi-active control can significantly reduce vibration and shock. The effect of the change of seat system parameters on the semi-active control effect is analyzed. According to the seat system model, a helicopter seat system control performance test platform was built. Based on xPC Target real-time control technology, the response of seat suspension mass acceleration under step displacement excitation was measured. The experimental results show that the designed magneto-rheological damper semi-active control seat system has obvious damping effect and provides guidance for the design of helicopter seat system.
【學(xué)位授予單位】：哈爾濱工業(yè)大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2014
【分類(lèi)號(hào)】：V275.1;TB535

【參考文獻(xiàn)】

相關(guān)博士學(xué)位論文 前2條

1 張志勇;半主動(dòng)座椅懸架控制理論與實(shí)驗(yàn)研究[D];湖南大學(xué);2008年

2 宗路航;磁流變阻尼器的動(dòng)力學(xué)模型及其在車(chē)輛懸架中的應(yīng)用研究[D];中國(guó)科學(xué)技術(shù)大學(xué);2013年

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本文編號(hào)：1835586