本文選題：蝶翼式硅微陀螺 + 模態(tài)耦合��； 參考：《國防科學(xué)技術(shù)大學(xué)》2014年碩士論文

【摘要】：硅微陀螺具有體積小、功耗低、價格便宜等優(yōu)點(diǎn),特別適用于需求量大、追求成本低的應(yīng)用場合,在軍事和民用各領(lǐng)域具有廣泛的應(yīng)用前景。蝶翼式硅微陀螺驅(qū)動模態(tài)與檢測模態(tài)之間存在相互耦合。為了探索新的控制方法與測控方案,以提高陀螺系統(tǒng)的總體性能;論文著重研究了蝶翼式硅微陀螺的模態(tài)耦合特性,深入對被控對象的認(rèn)識;為下一步研究陀螺系統(tǒng)雙模態(tài)控制方案,打下理論基礎(chǔ),并提供基本模型。論文在研究陀螺模態(tài)耦合特性的基礎(chǔ)上,建立了蝶翼式硅微陀螺模態(tài)耦合系統(tǒng)的數(shù)學(xué)模型,并圍繞模態(tài)耦合系統(tǒng)的系統(tǒng)辨識方法展開了研究,主要研究內(nèi)容如下:1、深入研究了蝶翼式硅微陀螺的模態(tài)耦合特性,分析了蝶翼式硅微陀螺模態(tài)耦合的產(chǎn)生機(jī)理,以及模態(tài)耦合因素對陀螺系統(tǒng)性能的影響,提出了在陀螺系統(tǒng)設(shè)計(jì)中對模態(tài)耦合因素進(jìn)行處理的必要性。2、分析認(rèn)為蝶翼式硅微陀螺系統(tǒng)是一個關(guān)聯(lián)結(jié)構(gòu)的、雙輸入雙輸出的模態(tài)耦合系統(tǒng)。建立了蝶翼式硅微陀螺模態(tài)耦合系統(tǒng)的數(shù)學(xué)模型,推導(dǎo)了系統(tǒng)的傳遞函數(shù)矩陣表達(dá)式以及輸入輸出方程。3、用頻率響應(yīng)擬合估計(jì)的方法,對蝶翼式硅微陀螺模態(tài)耦合系統(tǒng)進(jìn)行了辨識,分析了結(jié)果的有效性與適用性。認(rèn)為:擬合軌跡法,只考慮了數(shù)學(xué)上的最優(yōu)化,而忽略了實(shí)際的限制和約束,適用性不強(qiáng);因此,有必要在考慮實(shí)際約束的前提下,探索新的系統(tǒng)辨識方法。4、分析發(fā)現(xiàn)蝶翼式硅微陀螺模態(tài)耦合系統(tǒng)的零極點(diǎn)包括一對偶極子和一對共軛主導(dǎo)極點(diǎn),由此得到系統(tǒng)傳遞函數(shù)基本構(gòu)型�；诨緲�(gòu)型,設(shè)計(jì)了利用系統(tǒng)頻率響應(yīng)曲線,辨識系統(tǒng)傳遞函數(shù)的方法;該方法具有符合實(shí)際、測定方便、解算簡單等優(yōu)點(diǎn)。此外,還介紹了蝶翼式硅微陀螺模態(tài)參數(shù)與耦合系數(shù)的測定方法與實(shí)驗(yàn)方案。
[Abstract]:Silicon micro gyroscope has the advantages of small size, low power consumption and low price. It is especially suitable for applications with large demand and low cost. It has a wide application prospect in military and civilian fields.There is a coupling between the driving mode and the detecting mode of the butterfly wing silicon micro gyroscope.In order to explore new control methods and measurement and control schemes to improve the overall performance of gyroscope, this paper focuses on the mode coupling characteristics of butterfly wing silicon micro gyroscope, and deeply understands the controlled object.It provides the theoretical foundation and the basic model for the next step to study the double mode control scheme of gyroscope system.On the basis of studying the characteristics of mode coupling of gyroscope, the mathematical model of mode coupling system of butterfly wing silicon micro gyroscope is established, and the identification method of mode coupling system is studied.The main research contents are as follows: 1. The mode coupling characteristics of butterfly wing silicon micro gyroscope are studied, and the mechanism of mode coupling and the influence of mode coupling factors on the performance of the gyro system are analyzed.The necessity of dealing with modal coupling factors in the design of gyroscope is presented. It is considered that the butterfly wing silicon micro gyroscope system is a modal coupling system with two inputs and two outputs.The mathematical model of the mode coupling system of butterfly wing silicon micro gyroscope is established. The transfer function matrix expression of the system and the input and output equation. 3 are derived. The method of fitting and estimating the frequency response is used.The mode coupling system of butterfly wing silicon micro gyroscope is identified, and the validity and applicability of the results are analyzed.It is considered that the fitting trajectory method only considers the optimization in mathematics, but neglects the actual restriction and constraint, and the applicability is not strong, so it is necessary to consider the practical constraint.A new system identification method .4 is explored. It is found that the zero poles of the mode coupling system of butterfly wing silicon micro gyroscope include a pair of dipoles and a pair of conjugate dominant poles, and the basic configuration of the system transfer function is obtained.Based on the basic configuration, a method is designed to identify the transfer function of the system by using the frequency response curve of the system, which has the advantages of being in line with the actual situation, convenient in measurement and simple in calculation.In addition, the measurement method and experimental scheme of mode parameters and coupling coefficient of butterfly wing silicon micro gyroscope are introduced.
【學(xué)位授予單位】：國防科學(xué)技術(shù)大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2014
【分類號】：TN96

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本文編號：1738579