Research and test of the adaptive quadrature demodulation technology for silicon micro-machined gyroscope

A program of adaptive quadrature demodulation is proposed to supply the gaps in the traditional analog detection technology of a silicon micro-machined gyroscope (SMG). This program is suitable for digital phase locked loop (DPLL) drive technology that proposed in other papers. In addition the program adopts an adaptive filtering algorithm, which selects the in-phase and quadrature components that are outputs of the DPLL of the SMG's drive mode as reference signals to update the amplitude of the in-phase and quadrature components of the input signal by iteratively. An objective of the program is to minimize the mean square error of the accurate amplitudes and the estimated amplitudes of SMG's detection mode. The simulation and test results prove the feasibility of the program that lays the foundation for the further improvement of the SMG's system performance and the implementation of the SMG system's self-calibration and self-demarcation in future.

Design and simulation of a silicon-based hybrid integrated optical gyroscope system

By combining a silicon-based lithium niobate modulator and a silicon-based Si3N4resonator with silicon-based photonics technology,a highly systematic design of a hybrid integrated optical gyroscope with enhanced reciprocity sensitivity and a dual micro-ring structure is proposed for the first time in this paper.The relationship between the device's structural parameters and optical performance is also analyzed by constructing a complete simulation link,which provides a theoretical design reference to improve the system's sensitivity.When the wavelength is 1550 nm,the conversion frequency of the dual-ring optical path is 50 MHz,the coupling coefficient is 0.2,and the radius R is 1000μm,the quality factor of the silicon-based Si_(3)N_(4)resonator is 2.58×10^(5),which is 1.58 times that of the silicon-on-insulator resonator.Moreover,the effective number of times the light travels around the ring before leaving the micro-ring is 5.93,which is 1.62 times that of the silicon-on-insulator resonator.The work fits the gyro dynamic output diagram,and solves the problem of low sensitivity at low speed by setting the phase offset.This results provide a basis for the further optimization of design and chip processing of the integrated optical gyroscope.

New digital drive phase control for improving bias stability of silicon MEMS gyroscope

In order to improve the bias stability of the micro-electro mechanical system（MEMS） gyroscope and reduce the impact on the bias from environmental temperature,a digital signal processing method is described for improving the accuracy of the drive phase in the gyroscope drive mode.Through the principle of bias signal generation,it can be concluded that the deviation of the drive phase is the main factor affecting the bias stability.To fulfill the purpose of precise drive phase control,a digital signal processing circuit based on the field-programmable gate array（FPGA） with the phase-lock closed-loop control method is described and a demodulation method for phase error suppression is given.Compared with the analog circuit,the bias drift is largely reduced in the new digital circuit and the bias stability is improved from 60 to 19 °/h.The new digital control method can greatly increase the drive phase accuracy,and thus improve the bias stability.

Design and Fabrication of MEMS Gyroscopes on the Silicon-on-insulator Substrate with Decoupled Oscillation Modes

The mode coupling is a major factor to affect the precision of the micro electromechanical systems（MEMS） gyroscope. Currently, many MEMS gyroscopes with separate oscillation modes for drive and detection have been developed to decrease the mode coupling, but the gyroscope accuracy can not satisfy the high-precision demand well. Therefore, high performance decoupled MEMS gyroscopes is still a hot topic at present. An innovative design scheme for a MEMS gyroscope is designed, and in this design, the inertial mass is divided into three parts including the inner mass, the outer mass and the main frame mass. The masses are supported and separated by a set of mutually orthogonal beams to decouple their movements. Moreover, the design is modelled by multi-port-element network（MuPEN） method and the simulation results show that the mode coupling of the gyroscope between driving and sensing mode was eliminated effectively. Furthermore, we proposed a new silicon-on-insulator（SOI） process to fabricate the gyroscope. The scale factor of the fabricated gyroscope is 8.9 mV/（（~）os） and the quality factor（Q-factor） is as high as 600 at atmosphere pressure, and then, the resonant frequency, scale factor and bias drift has been test. Process and test results show that the proposed MEMS gyroscope are effective for decrease mode coupling, furthermore, it can achieve a high performance at atmosphere pressure. Furthermore, the MEMS gyroscope can achieve a high performance at atmosphere pressure. The research can be taken as good advice for the design and fabrication of MEMS gyroscope, meanwhile, it also provides technical support for speeding up of MEMS gyroscope industrialization.

Analysis of mathematical model for micromechanical vibratory wheel gyroscope

By the sketch of structure of MVWG,the working laws of this kind of gyroscope we re explained.To the aid of Euler′s Dynamics Equation,a mathematical model of the gyroscope was constructed,and then by the basic working laws of MVWG the model was simplified.Under the conditions of the three axial direction rotations and general rotation,the mathematical model was resolved.And finally by the solutions, the working laws of the gyroscope, the working disparity among all sorts of gyrations and the influences from the gyrations in the axial directions were analysed.

FABRICATION AND TEST OF AN ELECTROMAGNETIC VIBRATING RING GYROSCOPE BASED ON SOI WAFER

Mode matching is the key to improve the performance of micro-machined vibrating ring gyroscopes.Mass and stiffness asymmetries can lend to normal modes badly mismatch for gyroscopes fabricated by single-crystal silicon.The mismatch of the normal nodes results in large normal mode frequency split and degraded sensitivity.To address this issue,a Silicon-On-Insulator(SOI) wafer is used to fabricate the sensor chips.Meanwhile,a compensate disk and the backside coated negative photo resist(AZ303) is employed to weaken the Lag and Footing effect during the Deep Reactive Ion Etching(DRIE) process.Test results reveal that frequency split between the normal modes is of less than 10 Hz before the following electronic tuning.Thus,the mode matching of the electromagnetic vibrating ring gyroscope is probable to be realized.

馈通对硅微机械陀螺零偏影响及其抑制研究

硅微机械陀螺仪激励电极及读出电极间存在寄生电容,进而在读出信号中引入与其同频同相的馈通干扰信号。针对此现象,采用时域法对馈通干扰下力平衡模式的零偏特性进行理论推导,通过Simulink仿真及实验对结论进行验证。研究表明:馈通干扰导致力平衡模式驱动力一定时,陀螺零偏随模态频差改变发生变化。随后根据硅微机械陀螺仪静电力生成原理,设计一种采用半频谐振信号检测环路力平衡的控制系统,并通过实验验证了陀螺零偏在90 Hz模态频差变化范围内波动不超过0.17%,馈通对零偏的影响得到有效抑制。

采用菱形辐条的高对称MEMS蜘蛛网状盘式谐振陀螺仪

微电子机械系统(MEMS)陀螺仪因抵抗制造误差能力差和品质因数低等问题限制了其在高端领域的应用。通过对MEMS陀螺仪的理论分析和有限元仿真,基于绝缘体上硅(SOI)工艺设计并制备出了一种由多个同心嵌套的蜘蛛网环和菱形辐条组成的新型MEMS盘式谐振陀螺仪。实验结果表明,该陀螺仪的驱动谐振频率为42.749 kHz,感应谐振频率为42.798 kHz,频率失配为1.145×10^(-3),实测谐振频率与仿真结果差异为8.5%,优于采用相同工艺制作的环形盘式谐振陀螺仪。该MEMS陀螺仪不仅性能优异、工艺流程简单,而且由于采用全线性结构,所以对制造误差也相对不敏感,适合批量生产,具有较高的产业价值。

基于MEMS工艺的微热加速度计和微热陀螺仪的制备

微热加速度计和微热陀螺仪两者传感芯片结构相似,并且制备工艺完全兼容,在同一块绝缘体上硅(SOI)基板上运用同一工艺流程同时制备出了微热陀螺仪传感芯片和微热加速度计传感芯片。为了准确地创建微尺度的图案和结构,设计了四块光刻掩模版来制作该微热加速度计芯片和微热陀螺仪芯片,分别对应于接触孔开口、热敏电阻、互连布线和背面空腔。轻掺杂硅热敏电阻的可控电阻温度系数(TCR)大于传统金属丝,因此选择p型硅作为热敏电阻材料。TCR由硅片的掺杂浓度决定,使用了三种不同掺杂浓度的硅片进行对比实验,从而选定硅片的掺杂浓度为1×10^(17)cm^(-3),对应的TCR为3500×10^(-6)/℃。选择SOI作为衬底材料,显著增强了微热陀螺仪和微热加速度计的耐高温性,并且提高了其灵敏度。在电感耦合等离子体-反应离子刻蚀(ICP-RIE)和氢氟酸(HF)蒸气工艺过程中,通过光刻胶和聚酰亚胺层成功保护了非常薄和易碎的热敏电阻,在4英寸(1英寸=2.54 cm)SOI基板上一次最多可以成功制备出180个微热陀螺仪传感芯片和108个微热加速度计传感芯片,制备的微热加速度计传感芯片尺寸为2 mm×2 mm×0.4 mm,微热陀螺仪传感芯片尺寸为5.8 mm×5.8 mm×0.4 mm。分别对制备的微热加速度计和微热陀螺仪进行了测试,微热陀螺仪x轴灵敏度为0.107 mV/(°/s),y轴灵敏度为0.102 mV/(°/s),微热加速度计灵敏度为13 mV/g。通过一次工艺流程制备出两种热流体惯性传感器,极大地缩短了制备时间,降低了制备成本,成功实现了高精度的批量生产。

集成微光学陀螺研究现状、发展趋势和挑战

随着集成光子学和微纳工艺的飞速发展,微光学陀螺以其在芯片化、集成化上的优势广泛应用于下一代高精度小型化惯性导航系统中,在国防武器、微型飞行器以及无人机器控制等领域发挥重要作用。充分调研了国内外微光学陀螺研制方案及研究现状,介绍了包括干涉式、谐振式、布里渊散射式光学陀螺以及微光机电陀螺等四类微光学陀螺的工作原理和性能指标;光学微腔作为微光学陀螺中角速度核心敏感器件,其性能直接决定着陀螺系统精度指标,因此充分论述了氮化硅波导以及回音壁模式等新体制微腔的特性及优点,并针对其传输损耗、品质因子和陀螺性能等指标进行了对比和分析;最后总结了微光学陀螺芯片化的发展趋势以及在分立元器件性能提升、系统耦合与封装上遇到的机遇和挑战。

硅基光子集成芯片光纤陀螺

光纤陀螺用于敏感载体旋转角速率,是惯性导航系统的核心传感器之一。未来军用及民用领域对小体积、低成本的光纤陀螺需求巨大。利用光子集成芯片代替传统光纤分立器件,借助集成光学光刻工艺大规模批量生产的优势,降低生产成本,提高出货量,是光纤陀螺发展的重要方向。因此,在充分考虑目前国内微纳加工水平基础上,提出了一种工艺实现相对简单、可快速工程化的硅基光子集成芯片光纤陀螺设计方案。基于开环光纤陀螺架构,设计并加工了硅基光子芯片,实现了陀螺全部无源器件的片上集成,光子芯片尺寸约4 mm×3 mm;设计加工了四通道超细径保偏光纤阵列,实现波导与光纤多个耦合点的一次对准,大幅提高耦合封装效率;实现了光子集成芯片光纤陀螺样机25℃时零偏稳定性达到0.2°/h,性能优于相同结构的传统全光纤器件光纤陀螺。

窄频差硅基环形陀螺检测闭环控制系统设计

针对窄频差硅基环形波动陀螺动态性能差的问题,提出了一种基于比例积分微分-惯性环节(proportion integral differential-inertial element,PID-IE)的串联式相位校正检测闭环系统控制器。以硅微机械陀螺仪结构运动方程为基础建立了理想的窄频差U形弹性梁硅基环形波动陀螺仪的系统模型。通过对环形陀螺开环工作状态下的系统模型及其外围电路的传递函数和波特图分析,设计了一种基于PID-IE的检测闭环系统控制器。通过对其系统模型及外围电路时域仿真,验证了该检测闭环控制系统的可行性,通过仿真发现,加入该控制器后的陀螺输出稳定时间减少了50%,陀螺检测位移输出减小了2个数量级,基本实现了该陀螺的检测位移抑制。在模拟电路中实现了该检测闭环控制系统后,通过实验测试了陀螺检测闭环控制前后的各项性能指标。通过实验测试发现,实现闭环控制后,陀螺输出稳定时间约为0.15 s,陀螺检测位移在闭环工作状态下比开环工作状态减小了97%,陀螺的标度因数比检测开环提高了10倍,零偏及零偏不稳定性与检测开环相比分别提升了3倍和8倍,且闭环控制系统的工作带宽比开环工作带宽提高了30倍。

硅微机械陀螺同相信号的温度系数研究

同相信号的温度系数是影响硅微机械陀螺零偏温度漂移的主要原因。同相信号温度系数理论模型的建立可以为降低陀螺在温度环境中零偏漂移提供理论指导。本文从硅微机械陀螺的多层封装结构入手,结合陀螺自身的特征以及同相信号产生机理建立了同相信号温度系数的理论模型,根据该理论模型得到同相信号的温度系数为2170ppm/℃。将封装后的硅微机械陀螺置于不同温度条件下进行测试,测试结果表明同相信号的温度系数为1870 ppm/℃,测试结果和理论的误差为16%。结果表明,同相信号温度系数的理论模型是可靠的,可以为降低硅微机械陀螺零偏温度漂移的提供实际指导。

微硅陀螺性能影响因素及其对策研究

论述了微硅陀螺的发展概况 ,总结了微硅陀螺的几类典型结构 ,分析了微硅振动陀螺总体性能的影响因素。从制作工艺、材料特性、系统模型的确立及接口设计上详细分析了性能约束因子。针对这些约束因素 。

一种基于滑膜阻尼效应的新型微机械陀螺

介绍了一种基于滑膜阻尼效应的新型音叉式微机械陀螺。该陀螺包括两个驱动质量块和由各自驱动质量块支撑的检测质量块 ,通过检测质量块上的栅形电极与玻璃衬底上的固定检测电极之间的电容变化实现角速度信号的检测。对陀螺进行了结构设计和分析。在陀螺芯片的制作过程中 ,解决了深反应离子刻蚀过程中的根部效应和滞后效应等问题。初步测试结果表明 ,该陀螺灵敏度和非线性度比较理想。

大气下工作的微机械陀螺的设计及其噪声特性

设计了一种基于体微机械加工技术的新型音叉式微机械陀螺 .该陀螺在驱动模态和检测模态的空气阻尼均为滑膜阻尼 ,有效提高了微机械陀螺的Q值和灵敏度 ,同时降低了陀螺的热机械噪声 .对陀螺噪声特性进行的分析表明 ,该陀螺具有相对很低的热噪声 .制作了陀螺芯片 ,并测试了其机械性能和噪声特性 .结果表明 ,该陀螺的噪声谱密度不超过 6 0 μV/Hz,灵敏度为 10mV/(°·s-1) .

硅微陀螺正交误差直流校正设计与分析

为硅微陀螺设计了一种正交误差直流校正方法,通过设计校正结构和加载直流电压实现正交校正。建立了存在正交误差时敏感质量的运动微分方程,分析明确了正交响应的成因和对驱动运动轨迹的影响。为硅微陀螺设计了正交校正结构,实现构建静电耦合弹性系数并利用驱动运动产生校正静电力。校正力的频率和相位无需电路控制,使该方法相较于传统校正方法具备特殊优势。设计并分析了校正电压的两种加载方式,通过实验测试验证了正交响应幅值随校正电压的变化规律。实测校正电压接近理论值,证明了校正结构设计的正确性。该方法在双线振动式硅微陀螺中具有重要应用价值。

硅微振动陀螺仪驱动器自激驱动研究

为了提高硅微机械陀螺仪的检测精度,稳定驱动振动速度的幅度和频率,采用了硅微机械陀螺仪自激驱动方式。该方式能够使驱动振动自动稳定在陀螺仪驱动模态的谐振频率上。同时,采用自动增益控制(AGC)保持恒定的驱动振动幅度。根据自激驱动电路原理和现有的陀螺样品,建立了陀螺仪驱动动力学方程的等效电路模型。设计、制作了自激驱动电路,仿真和实验结果表明该方法切实可行。

双质量解耦硅微陀螺仪的非理想解耦特性研究和性能测试

为了分析双质量解耦硅微陀螺结构中的机械耦合误差,对微陀螺结构的非理想解耦特性进行了研究。首先,阐述了双质量解耦硅微陀螺仪的结构原理,推导了双质量解耦硅微陀螺仪的检测位移;接着构建检测框架在驱动模态下非理想的解耦模型,推导了由非理想解耦导致检测框架的平动位移与转动位移的公式;然后进行了结构非理想解耦特性仿真分析,对驱动模态时检测框架和检测模态时驱动框架的非理想运动特性进行仿真,结果表明检测框架的残余平动位移达到驱动位移的0.86%,最大转动残余位移达到了驱动位移的2.7%,而驱动框架的平动残余位移达到了检测位移的1.36%,转动残余位移达到了检测位移的0.87%;最后,对加工的双质量解耦硅微陀螺结构芯片的非理想解耦误差进行了测量,结果表明非真空封装下的正交误差达到158.65(o)/s,失调误差为19.03(o)/s,偏置稳定性达到12.01(o)/h。

基于偶极子补偿法的硅微机械陀螺仪带宽拓展

硅微机械陀螺仪的机械灵敏度与驱动和检测模态的谐振频率差Δf成反比,而Δf处的谐振峰是影响陀螺带宽的直接因素,带宽约0.54Δf,因此,带宽和机械灵敏度往往成为两个互为矛盾的指标。基于自动控制原理中介绍的偶极子理论提出了偶极子补偿控制技术,该方法在不影响机械灵敏度的前提下可有效拓展陀螺带宽。首先,对涉及到的双质量硅微机械陀螺仪的结构形式和工作原理进行了介绍,指出陀螺实际工作的检测模态是由检测同相和反相模态叠加而成,设计了陀螺开环检测回路,分析了带宽是由驱动反相和检测反相模态的谐振频率差决定,并结合检测力反馈激励法验证了上述结论;其次,根据偶极子工作原理设计了偶极子补偿控制器的系统传递函数和电路,并对相关内容进行了仿真,验证了电路参数的准确性;最后,基于偶极子补偿控制器建立了硅微机械陀螺仪闭环检测系统,分析了该系统的稳定性,并对该系统的带宽特性进行了仿真和测试,结果显示带宽由原来的13 Hz拓展到了76 Hz,很好地证明了本文提出方法的可行性。此外,鉴于双质量陀螺的实际检测模态,在消除了第一个Δf谐振峰对带宽的影响后,由检测同、反相模态叠加产生的共轭零点引起的幅值谷为带宽进一步提高的限制因素。