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首页> 外文会议>Saint Petersburg international conference on integrated navigation systems >THE CONCEPT OF ACCURATE EQUATIONS OF ERRORS AND ESTIMATIONS OF QUANTUM LIMITS OF ACCURACY OF STRAPDOWN INERTIAL NAVIGATION SYSTEMS BASED ON LASER GYROS,FIBER-OPTICAL GYROS, AND ATOM INTERFEROMETERS ON DE BROGLIE WAVES
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THE CONCEPT OF ACCURATE EQUATIONS OF ERRORS AND ESTIMATIONS OF QUANTUM LIMITS OF ACCURACY OF STRAPDOWN INERTIAL NAVIGATION SYSTEMS BASED ON LASER GYROS,FIBER-OPTICAL GYROS, AND ATOM INTERFEROMETERS ON DE BROGLIE WAVES

机译：基于德陀螺波的激光陀螺仪，光纤陀螺仪和原子干涉仪的捷联惯导系统误差的精确方程概念和精确度的量子极限估计

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Accurate equations of errors (EE) of strapdown inertial orientation systems (SIOS) and strapdown inertial navigation systems (SINS) are discussed. The differences between accurate dynamic and kinematic EE and approximated dynamic and kinematic EE (the equations in variations) are commented. Examples of the effects which can not be seen on the base of approximated EE are presented. Usually, the EE are used in two tasks: l)for the forecast of accuracy of system taking into account the models of errors of gyros and accelerometers, the errors of gravitational field modeling and errors of initial conditions; 2) for working out the requirements for admissible levels of errors and noises of sensitive elements and methodical errors of algorithms at demanded accuracy of system. In the report a new class of algorithms of SINS in which for the purpose of correction the output parameters in parallel with regular algorithms the EE are integrated is proposed. The limitation of accuracy of SIOS and SINS by quantum noises of gyros based on Sagnac effect (SEG) of three generations - laser gyros (LG), fiber-optical gyros (FOG), and atom interferometers (AI) on de Broglie waves (AIWB) is discussed. On the basis of analytical solutions of dynamic EE of SINS, corresponding to some types of corrected SINS and trajectories of movement, the contribution of SIOS error to resultant SINS error is analyzed. This contribution depends on trajectory of movement because it is proportional to the overload. For movements with overload equals to unit and with arbitrary rotation the limit of achievable SINS accuracy, i.e. limited by ineradicable quantum noises of gyros (Gaussian white noises), is following: 1) (55-75) m/h in case of SINS on LG with level of noise (3-4) x 10-~(-4) deg/h~(1/2); 2) 10 m/h in case of SINS on FOG with level of noise 5 x I0~(-5) deg/h~(1/2); 3) less than I m/h in case of SINS on AIWB with level of noise 3 x 10~(-6) deg/h~(1/2).
机译：讨论了捷联惯性定向系统（SIOS）和捷联惯性导航系统（SINS）的精确误差方程（EE）。评论了精确动态和运动EE与近似动态和运动EE（变化方程）之间的差异。给出了在近似EE的基础上看不到的效果的示例。通常，EE用于两个任务：l）考虑陀螺仪和加速度计的误差模型，重力场建模的误差和初始条件的误差来预测系统的精度; 2）在系统要求的精度下，确定敏感元件的误差和噪声的可接受水平以及算法的系统误差的要求。在该报告中，提出了一种新的SINS算法，其中为了校正输出参数与常规算法并行集成了EE。基于三代Sagnac效应（SEG）的陀螺仪的量子噪声对SIOS和SINS精度的限制-激光陀螺仪（LG），光纤陀螺仪（FOG）和德布罗意波（AIWB）上的原子干涉仪（AI） ）进行了讨论。在对SINS动态EE的解析解的基础上，针对修正后的SINS类型和运动轨迹，分析了SIOS误差对所得SINS误差的贡献。该贡献取决于运动轨迹，因为它与过载成比例。对于过载等于单位且任意旋转的运动，可达到的SINS精度的极限（即受陀螺无法消除的量子噪声（高斯白噪声）的限制）如下：1）（55-75）m / h（在SINS开启的情况下） LG噪声水平（3-4）x 10-〜（-4）deg / h〜（1/2）; 2）FOG上的SINS情况下为10 m / h，噪声水平为5 x I0〜（-5）deg / h〜（1/2）; 3）如果AIWB上的SINS的噪声水平为3 x 10〜（-6）deg / h〜（1/2），则小于I m / h。

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