Research on feasibility of missile attitude control based on laser gyroscope

According to the disadvantages of traditional mechanical gyro inertial measurement unit('IMU') for steering system not being available for missile attitude control, a concept based on laser gyro IMU is proposed to realize navigation & positioning and attitude control. The concept will save three single-axis rate gyros compared with traditional missile attitude control system, and is available both for strapdown and platform inertial navigation systems. Firstly, this article analyzes the selection requirements of sensitive device for missile attitude control system, and then analyzes the feasibility of missile attitude control based on laser gyro theoretically, on this basis, from four aspects of error characteristics, anti-vibration characteristics, temperature characteristics and dynamic characteristics, validate the feasibility of the concept practically. Secondly according to the strict requirements of dynamic characteristics on attitude control system, a special design is made for gyro signal filtering used for attitude control. By changing the traditional high order FIR filter to adaptive filter and low order FIR filter, laser gyro's signal phase delay is reduced. The delay time of theoretical design is 1.5 ms. Lastly, this design is validated through an angle vibration test, and test curve indicates that the dynamic characteristics of laser gyro completely meets the requirements of the attitude control system, and the maximum delay time is 1.6144 ms, which satisfies with the attitude update rate of 2 ms per frame. This concept can simplify the missile guidance system design, at the same time, it does not reduce missile guidance accuracy, and also provides reference for the broadening of the application of laser gyro.

Dynamic model and simulation of aseismatic system about laser gyro strapdown inertial measure assembly based on MSTMM

The precision of the laser gyro used in tactical missiles is poor because of dithering frequency,actuating by vibration,shock and overload in dynamical environment.This paper introduces the transfer matrix method of the multibody system（MSTMM）,establishes the dynamic model of the laser gyro strapdown inertial measure assembly aseismatic system,and analyzes the precision affected by dithering of the laser gyro and shocking of the tactical missile.And the dynamic response of the laser gyro strapdown inertial measure assembly aseismatic system is obtained by simulating the multibody system model.The simulation result indicates a theoretical idea to design the vibration isolation for the laser gyro strapdown inertial measure assembly.

Suppression of the G-sensitive drift of laser gyro in dual-axis rotational inertial navigation system

The dual-axis rotational inertial navigation system(INS)with dithered ring laser gyro(DRLG)is widely used in high precision navigation.The major inertial sensor errors such as drift errors of gyro and accelerometer can be averaged out,but the G-sensitive drifts of laser gyro cannot be averaged out by indexing.A 16-position rotational simulation experiment proves the G-sensitive drift will affect the long-term navigation error for the rotational INS quantitatively.The vibration coupling and asymmetric structure of the DRLG are the main errors.A new dithered mechanism and optimized DRLG is designed.The validity and efficiency of the optimized design are conformed by 1 g sinusoidal vibration experiments.An optimized inertial measurement unit(IMU)is formulated and measured experimentally.Laboratory and vehicle experimental results show that the divergence speed of longitude errors can be effectively slowed down in the optimized IMU.In long term independent navigation,the position accuracy of dual-axis rotational INS is improved close to 50%,and the G-sensitive drifts of laser gyro in the optimized IMU are less than 0.0002°/h.These results have important theoretical significance and practical value for improving the structural dynamic characteristics of DRLG INS,especially the highprecision inertial system.

Polarization properties in a prism laser gyro with mechanical dither bias

Theoretical analysis and experimental research on the polarization properties of output light in gyro are carried out to investigate the phenomenon that the amplitude of an output voltage signal is modulated by dither bias in laser gyros consisting of totally reflecting prisms. Taking the effect of prism stress birefringence into account, an analytical formula of the output light intensity in the gyro and the relationship between the polarization parameter and the amplitude modulation of the output signal are obtained and discussed. For the first time, the polarized power value of the output light is adopted as a basis to estimate the output signal amplitude fading extent of laser gyros. Experimental results demonstrate that when the value of polarized power of output light is below 25.5% of that in ideal static case, the standard error is over 0.0337 dBm, and the displacement extent of the prism is higher than 53% of the radius of the beam waist in the gyro cavity, the amplitude modulation extent of gyro output signal can reach up to 16%, which badly influences the measurement accuracy of the laser gyro. Using this polarized power detecting measurement method can repair the gyro immediately during its fabrication process, improve the testing and production efficiency and shorten the product development cycle.

Signal processing circuit of laser gyro based on FPGA and DSP

This is a paper about laser gyro sign a l processing circuit which is designed based on field-programmable gate array(FPGA) and digital signal processor(DSP).Through a pre-amplifier circuit,FPGA and DSP,a weak current signal is converted and transferred,then sent to the computer to display the final results.Through the laser gyro performance te sting,the obtained results coincide with those of the existing methods.Thus th e d esigned circuit realizes the function of laser gyro signal processing.

基于超短脉冲激光刻蚀的双解耦MEMS陀螺仪调频技术研究

以双解耦双质量硅微陀螺仪为主要研究对象,从微观结构入手,分析其工作原理和双解耦运动模型,并提出影响模态特征频率的因素。提出一种改变陀螺仪弹性梁结构厚度来调整其特征频率的方法,建立模型通过Comsol软件仿真陀螺仪梁厚度变化对特征频率的影响关系,并选择皮秒激光刻蚀系统刻蚀陀螺弹性梁厚度,测试其两模态特征频率。测试结果表明:对应频率变化符合理论推导和仿真趋势。

激光陀螺引燃技术研究及应用

针对棱镜式激光陀螺引燃不可靠的现象,系统地研究了基于外置电极加载高频电场激励激光器件谐振腔的引燃方法,理论上分析了影响激光陀螺引燃电压的获取因素,在此基础上提出了两种增加谐振腔引燃可靠性的措施,通过缩短引燃阴极和引燃阳极之间的距离,有效降低了谐振腔所需的引燃电压值,从而使工作气体局部更容易被激发,进而产生雪崩效应,使整个内部空间的工作气体被激发,实现激光器件谐振腔的正常持续工作。实验结果表明,优化后的激光陀螺谐振腔在高、低、常各温度段可实现大于99.9%的可靠引燃。

AN IMPROVED ROTATION VECTOR ATTITUDE ALGORITHM FOR LASER STRAP-DOWN INERTIAL NAVIGATION SYSTEM

The laser gyro is most su it able for building the strap down inertial navigation system (SINS), and its acc uracy of attitude algorithm can enormously affect that of the laser SINS. This p aper develops three improved algorithmal expressions for strap down attitude ut ilizing the angular increment output by the laser gyro from the last two and cur rent updating periods according to the number of gyro samples, and analyses the algorithm error in the classical coning motion. Compared with the conventional algorithms, simulational results show that this improved algorithm has higher precision. A new way to improve the rotation vector algorithms is provided.

激光陀螺实验中谐振腔调节的分析与讨论

本文在非傍轴近似条件下利用几何光学理论推导了激光陀螺实验中谐振腔大小、反射镜曲率及偏转角度等因素与腔内自再现谐振激光空间位置关系的公式,比较了其与通常傍轴近似下矩阵光学结果的差异,讨论了实验时调节反射镜偏转角度对谐振腔有效腔长、光路面积、陀螺比例因子及激光出光位置的影响规律,对激光陀螺实验中谐振腔的调节有指导意义.

激光陀螺全温度下选模控制策略设计

针对激光陀螺稳频装置易受温度变化的干扰的问题,为保证全温度范围内激光陀螺的稳频效果,提出了一种选模控制策略:根据陀螺扫模过程中得到的不同模态,通过比较各个模态下背向散射特征电压的大小,在常温下筛选出合适的陀螺及其控制模态,再经过温循实验进一步筛选出合适的模态,并固定用于全温度下的稳频控制以保证陀螺全温精度。最后通过实验验证,使用该筛选策略下获得的最佳模态,实现激光陀螺全温下稳定工作,满足实际工作要求。

基于激光陀螺测角仪的角度计量动态特性分析

为了使动态角度测量结果可靠、可信,在使用激光陀螺测角仪进行动态角度测量前,需要对其动态特性进行分析。首先,通过同步触发装置将激光陀螺测角仪分布与转台和激光干涉仪分别同步触发;然后,使转台模拟出脉冲响应运动、阶跃响应运动和正弦运动;最后,比较分析在不同运动过程中激光陀螺测角仪与转台的圆光栅和激光干涉仪的输出数据。结果表明,激光陀螺测角仪具有良好的动态特性,且在不同频率下激光陀螺测角仪的动态测角精度在0.6″左右,为激光陀螺测角仪进行动态角度测量结果的可靠性提供了保证。

采用激光光源线宽展宽的光纤陀螺标度因数性能提升技术

光纤陀螺中使用激光光源代替传统宽谱光源有利于提升性能和降低成本,但激光光源作为一种窄线宽的高相干光源,将其用于光纤陀螺又会引入瑞利散射、克尔效应和偏振交叉耦合等干扰,因此有必要对激光光源进行线宽展宽。首先对基于高斯白噪声外部相位调制的激光光源线宽展宽方法进行理论分析,建立光谱展宽卷积模型。其次采用延迟自相关测量方法验证了高斯白噪声外部相位调制对激光光源线宽的展宽效果。最后基于仿真分析结论,搭建了激光器线宽展宽光源装置,将激光光源的光谱展宽成线宽20 GHz的光谱,应用于光纤陀螺并验证了标度因数性能,为激光光源在光纤陀螺中的应用提供了理论基础,具有一定的工程应用价值。

Algorithm implementation of high-speed laser g yro signal demodulation filter

Based on the characteristics of field-programmable gate array(FPGA) such as multi-task,high-speed,parallelity,etc,a filtering algorithm is presented to filter the output signal of laser gyr o with high-speed and high accuracy.The filter is composed of basic logic cell s,multipliers an d memory inside FPGA.By using an multiplication decomposition method and design ing reliable time-sequence,the filter is realized,which is easy to be transpl anted and of low cost.Furthermore,all the signal demodulation algorithms of t he laser gyr oscope can be integrated in only one FPGA,which reduces the cost and complexity of the system.

光学陀螺背向散射问题综述(特邀)

光学陀螺作为光电惯性导航系统的核心器件,在众多领域发挥着举足轻重的作用。随着科学技术的不断进步,传统的激光陀螺、轻质化的光纤陀螺以及集成化的微光陀螺齐头并进、蓬勃发展,但无论是哪一种陀螺样式,在性能优化的过程之中都不可避免地需要考虑背向散射的问题。背向散射是光学陀螺中的一种噪声源,其会带来陀螺的输出偏置或闭锁效应,从而影响其性能。为了更好地理解光学陀螺中的背向散射机制,首先从半经典理论下的自洽方程组出发讨论背向散射的基本原理,而后依照光学陀螺的发展脉络,分析各种光学陀螺的背向散射分析方法、测量手段以及抑制方法,最后对目前光学陀螺中有关背向散射亟待解决的问题进行总结并展望。

全反射棱镜式激光陀螺标度因数补偿技术

针对全反射棱镜式激光陀螺标度因数随温度周期性变化的现象,根据矩阵光学方法研究了稳频状态下温度变化对环形激光面积的影响,获得了全反射棱镜式激光陀螺标度因数与稳频电压的关系,并得出光束偏移是引起标度因数随温度周期性变化的原因。根据标度因数与稳频电压的关系,建立了全反射棱镜式激光陀螺标度因数补偿模型,通过实验对比了补偿前后标度因数的非线性度。结果表明,根据该补偿模型对全反射棱镜式激光陀螺标度因数进行补偿,标度因数非线性度提高了一个数量级以上,对提高全反射棱镜式激光陀螺的性能具有一定的参考价值。

无依托瞄准技术在运载火箭基准确立上应用的研究

针对大型运载火箭无人值守瞄准的需求,提出一种基于激光捷联惯组与瞄准仪相结合的无依托瞄准方法,通过激光惯组自主寻北获得北向基准,再测量出箭上惯性单元棱镜法线与返回光束的准直偏差角,将数据进行合成、解算,最终获得箭上惯组棱镜的初始方位。无依托瞄准技术具有组成简单、自动化程度高、操作流程简化、精度指标可靠的特点,可以提供不大于2’的瞄准综合误差,技术成果满足中国航天发射任务的应用需求,可供未来大型运载火箭瞄准方式参考。

激光陀螺表面多层膜微结构表征与分析

本文针对激光陀螺长期稳定性技术研制要求,通过透射电子显微镜(TEM)、扫描电子显微镜(SEM)、扫描透射电镜(STEM)、聚焦离子束刻蚀(FIB)、X射线光电子能谱(XPS)以及X射线能量散射谱(EDX)等微观结构和组分表征技术,对激光陀螺反射镜的微观结构和组分进行表征,研究反射镜在不同镀制工艺条件及高低温等外部工作条件下,反射镜膜层界面、膜-基界面以及膜层本身微结构特性的变化规律,建立反射镜微结构特性和不同变化之间的映射关系。本研究结果为激光陀螺表面多层膜的结构表征提供坚实的实验参考和理论依据。

基于激光陀螺测角仪的转台角定位误差多点测量与补偿方法

目的:提高激光陀螺测角仪测量转台的角位置精度,实现转台的全圆周内任意角度测量与补偿。方法:采用全新测量方式,利用环形激光原理实现转台任意角度高精度测量。首先提出激光陀螺测角仪进行多位置平均的偏置标定方法;然后采用激光陀螺测角仪进行全圆周小角度范围测量,并得到角位置误差函数;最后以自准直仪数据为真值作比对。结果:激光陀螺测角仪测试转台的精度由0.6″提高到了0.3″,并且实现转台在全圆周范围内测角精度为0.3″。结论:多位置平均的偏置标定方法能够有效地提高激光陀螺测角仪的测量精度,并且可以对转台进行全圆周任意角度的测量。

基于ZYNQ的激光陀螺寻北仪的设计

在现代化战争中的武器系统以及民用勘测领域中,寻北技术发挥着无与伦比的作用。基于此背景,该文设计了一种基于ZYNQ的光纤陀螺寻北仪。该系统由XB185D单轴闭环光纤陀螺通过串行422通信接口将数据发送给ZYNQ,并通过AD模块AD7693对两路石英加速度计进行数据采集,利用温度传感器DS18B20进行温度数据采集。以XC7Z020为逻辑控制核心,通过四位置寻北算法解析北向角度,通过串口总线将结果发送到上位机上。经测试表明,该系统稳定可靠,能准确地定位北向,其误差范围在0.3°内。

一种完整测量膜片法拉第效应和损耗的方法

提出了一种能完整测量零锁区激光陀螺法拉第偏频组件中旋光膜片的法拉第旋光效应和超低损耗的方法和自动测量系统.该方法利用双光路正交分解平衡测量原理,通过测量两束光光强平衡时起偏器的偏振方向来确定旋光膜片的法拉第转角和超低损耗.测量结果表明:系统对法拉第转角的测量分辨率小于0.9″,损耗测量分辨率为10ppm.环境温度的波动对法拉第转角的测量变化很小,但对膜片超低损耗测量影响很大,温度变化8.1K,膜片损耗测量值变化一个周期.实验及结果证明,该系统能满足超高精度测量的要求.