The circuit and software of attitude algorithm is designed.
设计了姿态解算模块的硬件电路和软件实现程序。
Sensor errors are the main factors which have influence on attitude algorithm accuracy.
传感器误差是影响姿态解算精度的主要因素。
The random constant drift of the low accuracy gyroscope has a serious effect for attitude algorithm.
弹载低精度陀螺仪的随机常值漂移严重影响到弹体姿态解算的精度。
Abstract : A method to realize attitude algorithm module in strapdown inertial guidance is presented.
摘要 ：提出了捷联惯性导航系统姿态解算模块的一种实现方法。
Coning error and quantizing error are two kinds of primary errors in the attitude algorithm of laser strap-down inertial system.
圆锥误差和量化误差是激光捷联惯性导航系统姿态解算误差的两个最主要的误差源。
This paper introduces the principle of fiber optic gyro, studies the attitude algorithm of fiber optic gyro ship attitude system, introduces the quaternion algorithm and rotation vector algorithm.
对四元数法和等效转动矢量法的滚转弹姿态解算精度进行比较，并通过打击机动目标的仿真试验验证了姿态解算精度对制导精度的影响。
The algorithm has been embedded in the attitude control system of a small unmanned helicopter.
该算法已应用于小型无人直升机的姿态控制中。
The simulation results show that compared with the traditional quaternion algorithm, the method can smooth the effect of noise while resolving the system attitude.
仿真表明，与传统四元数算法比较，该方法在解算系统姿态的同时，能够较好地平滑噪声的影响。
The control algorithm of attitude follow-up stabilization and tracking antenna platform adopts position feed-forward control, speed control and position feedback control.
姿态随动稳定跟踪天线平台的控制算法，采用位置前馈、速度和位置反馈控制。
The sample and static error compensation, quaternion and attitude updating and algorithm of station and velocity updating were researched.
研究了采样与静差补偿，以及四元数、姿态、位置和速度更新的算法。
Borrowing the traditional two-speed approach originally developed in conventional attitude integration, we design one new numerical integration algorithm to solve the three kinematic equations.
借鉴成熟的姿态四元数积分的双速算法结构，设计了一个数值积分算法求解以上三个运动学方程，构建了基于对偶四元数的捷联惯性导航算法。
A novel monocular vision-based relative position and attitude measurement algorithm named as the Similar Iteration algorithm is presented for non-cooperative spacecrafts in this paper.
对非合作航天器的相对位置和姿态测量问题进行了研究，提出了一种新的单目视觉测量算法——相似迭代算法。
The introduction of the new algorithm is a new idea to calculate attitude error compensation of FOG strapdown inertial navigation(SINS) under the condition of high dynamic angular motion.
新算法的提出为高动态环境下光纤陀螺捷联系统的姿态误差补偿提供了一个新的思路。
DSP controller is chose as the system CPU and the attitude control demo experiment is achieved by generalized the incomplete integral PID control algorithm.
采用不完全积分PID控制算法初步实现了姿态控制的演示实验。
With this measured data, information fusion algorithm is able to design a high precision Attitude and Heading Reference system. Therefore it can accord with the control system demand.
依据这些原始数据设计适当的信息融合算法可以构建高精度的姿态航向参考系统，从而满足控制系统的要求。
The main contents of this dissertation are as follows. A structurized attitude pointing algorithm based on target vectors, was constructed in an event-driven manner.
论文的主要研究内容包括：从事件驱动的思想出发，建立了基于目标矢量的姿态定向结构化算法。
As a spacecraft attitude measurement instrument, CCD star tracker has a lot of advantages. But it needs an all-sky autonomous star map identification algorithm to support its operation.
CCD星跟踪器作为飞行器的姿态测量仪器有许多优点，它必须有一种全天自主星图识别算法来支持其工作。
A spatially attitude constraints monitor method was described, and an attitude pointing mode reconfiguration algorithm was proposed to solve the constraints problem with stabilization pointing mode.
描述了一种空间化的姿态约束表达方法，并针对稳定定向模式面临的约束问题提出了姿态定向的模式重构算法。
A filtering algorithm for high precision attitude determination of a specific satellite is presented based on star-sensors and fiber optic gyroscopes (FOG).
为了达到卫星三轴姿态确定的精度要求，以某一对地定向的小卫星为研究对象，提出了基于滤波算法的星敏感器和光纤陀螺组合定姿的方案。
An algorithm to extract flight attitude from a space vector, which was connected by two track points, was proposed.
提出了一种用飞机前后两个位置点空间连线矢量提取飞行姿态算法。
LR analysis of expression grammar for the bottom-up parsing algorithm everyone operations for reference purposes only, attitude is everything.
LR分析法对表达式文法进行自底向上语法分析的算法个个作业仅供参考，态度决定一切。
To solve the attitude maneuver of a flexible satellite, this article presents a variable structure tracking control algorithm based on output feedback.
为解决柔性航天器姿态机动的控制问题，给出了基于输出反馈的变结构跟踪控制算法。
In order to solve this problem, an algorithm which adopts attitude matching transfer alignment method to estimate the random constant drift of the low accuracy gyroscope is introduced.
为了解决这一问题，提出了以装订值作为姿态基准，采用姿态匹配传递对准对弹载低精度陀螺仪的随机常值漂移进行估计的算法。
Study on attitude-updating algorithm.
捷联姿态算法研究。
A new star pattern recognition algorithm without any apriori attitude knowledge is described.
讨论了一种新的无须任何先验知识的星图识别算法。
The attitude of the carrier is obtained by further using an attitude measurement algorithm through the fixed solutions.
通过固定解进一步利用姿态测量算法得到载体的姿态。
To study the attitude system of spacecraft, an adaptive inverse control algorithm is presented.
针对航天器姿态系统，提出了一种基于自适应神经网络动态逆的控制算法。
A damped LAMBDA algorithm is used for single epoch GPS positioning combining the condition that baseline length on vessel is fixed, a new method for attitude determination with GPS is put forward.
在作者提出的GPS单历元阻尼lambda算法的基础上，结合固定边长条件，给出了一种GPS姿态定位的新方法。
An algorithm is presented to determine the SAR satellite attitude with the aid of the SAR satellite kinematics model and the information of GPS wide-band carried phase.
针对姿态对星载SAR成像质量的重要影响，提出一种借助于SAR卫星姿态运动学特性和GPS宽波载波相位信息进行SAR卫星姿态测量的算法。
An algorithm is presented to determine the SAR satellite attitude with the aid of the SAR satellite kinematics model and the information of GPS wide-band carried phase.
针对姿态对星载SAR成像质量的重要影响，提出一种借助于SAR卫星姿态运动学特性和GPS宽波载波相位信息进行SAR卫星姿态测量的算法。
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