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.

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.

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.

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.

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.

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。

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。

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。

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.

小波域中值滤波在激光陀螺信号处理中的应用

各种随机噪声是导致激光陀螺产生误差的主要因素,且其性质特殊,很难用传统的滤波方法去除。为了减小激光陀螺的随机误差,提高测量精度,提出了小波域的中值滤波器滤波方法,对激光陀螺零漂数据进行了滤波,并采用Allan方差法对滤波效果进行了定量分析。结果表明,此方法的滤波效果优于中值滤波和小波软阈值滤波效果,能有效地减小激光陀螺零漂信号中的角度随机游走、角速度随机游走、速率斜坡、零偏不稳定性和量化噪声,提高激光陀螺零漂输出的稳定性。

激光陀螺锁区特性的研究

从理论和试验两个方面,研究了四边形腔环行激光陀螺的锁区特性·利用环行腔中背向散射光束具有相干性,导出了环行谐振腔综合背向散射与反射镜、反射镜之间的相对位置的关系·在有两个位移反射镜的四边形谐振腔中,理论上得到了综合背向散射系数与谐振腔腔长具有双波长周期·利用综合背向光强实验及锁区与陀螺工作模数实验分别验证了理论的正确性·试验证实散射光的强度与谐振腔的工作模数存在双模周期性,综合背向散射系数大,陀螺锁区大,反之亦然·

几种光学陀螺的研究进展

除了He-Ne气体激光陀螺外,国内外提出了研制新型光学陀螺的多种方案。该文介绍了其中干涉式光纤陀螺、循环再入式光纤陀螺、集成光学陀螺、半导体激光陀螺的研究现状,着重介绍了超短脉冲激光陀螺研究;同时指出了光学陀螺的发展趋势。

速率偏频激光陀螺过锁区误差特性分析

分析了速率偏频激光陀螺过锁区的误差特性。根据激光陀螺的闭锁方程,分别从数值模拟和理论分析两种途径对速率偏频激光陀螺过锁区误差特性进行了研究。结果一致表明:速率偏频激光陀螺过锁区的误差与锁区大小成正比,与过锁区的加速度的平方根成反比,与刻度因子的平方根成反比。文中具体给出了速率偏频激光陀螺过锁区的误差方程。过锁区误差为速率偏频激光陀螺的主要误差源。

基于空域相关的激光陀螺信号滤波方法研究

针对传统滤波方法滤除激光陀螺随机噪声性能低的特点,提出了一种改进的空域相关滤波方法。该算法通过引入阈值系数概念,选取一个合适的阈值终止算法的迭代过程来去除残留的噪声信息。实验采用Allan方差法对滤波效果进行定量分析,结果表明基于改进的空域相关滤波方法能够减少迭代次数节约计算量,有效地减小随机误差,提高测量精度。