文章陈述了自旋稳定通信卫星姿态确定的矩阵方法及其工程应用的七种情况。
The matrix method of the attitude determination for spin-stabilized geostationary communication satellite and its cases of practical engineering application are described in this paper.
利用改进的自适应增益卡尔曼滤波器在随机模式下建立一个小型姿态确定系统。
An extended Kalman filter with adaptive gain was used to build a miniature attitude and heading reference system based on stochastic model.
直接将太阳电池板电流作为量测量进行姿态确定，不仅可观性不高，也不利于计算量的减少。
If the current generated by solar panels are used as measurements for attitude determination, not only the observability is low, but also it is disadvantageous to the decrease of computation.
仿真结果表明，采用联邦滤波器对多敏感器卫星姿态确定系统进行信息融合，具有计算量小、精度高、可靠性好等优点。
Simulation results show that federated filtering based information fusion method for the multi-sensor satellite system is characterized by small computation cost, high precision and good reliability.
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。
A filtering algorithm for high precision attitude determination of a specific satellite is presented based on star-sensors and fiber optic gyroscopes (FOG).
在确定卫星姿态确定的状态估计法中，经典的扩展卡尔曼滤波(ekf)和新提出的非线性预测滤波(NPF)这两种实时滤波算法各有优缺点。
In state estimation of satellite attitude determination, both traditional extended Kalman filter (EKF) and the proposed nonlinear predictive filter (NPF) have their own merits and defects.
华盛顿谦逊的态度和他的私人信件完全一致，所以这肯定不是故作姿态。他只是不确定自己是不是能够胜任这一职位，因为他从来没有从事过类似的工作。
This sentiment of modesty jibed so perfectly with Washington’s private letters that it could not have been feigned: he wondered whether he was fit for the post, so unlike anything he had ever done.
提出了一种利用姿态测量数据确定卫星初始轨道的新方法。
A new method of determining the satellite initial orbit with attitude data is presented.
本文提出了确定单足跳跃机器人落地姿态的最小能耗方法，该方法对其他动态步行多足机器人的研究也有参考价值。
In this paper, least energy method of determining landing posture of a hopping robot is introduced. The method is also reference to other dynamic walking robot of legs.
仿真结果表明：即使系统存在不确定性和外界干扰，仍可在闭环系统中实现精确的姿态控制。
Simulation results show that, in the closed-loop system, precise attitude control is accomplished in spite of the uncertainties and external disturbances in the system.
文章给出在发射静止卫星过程中，固体远地点发动机点火时间和点火姿态的最佳值确定方法。
This paper provides a method for determining the optimum time and attitude in process of geostationary satellite launch at which the solid-apogee motor to be fired.
提出了双目立体视觉确定机器人末端工具空间位置、姿态的方案。
The scheme of binocular stereo is planned for making sure the position, pose of the ending tools.
求出控制轴与主轴部件铰接点中心坐标，以确定刀具加工姿态。
Center coordinate of hinge joining point between control shaft and host shaft parts is calculated to determine machining posture of cutter.
人脸检测是指在视频序列或图像中寻找所有人脸信息，并确定人脸大小、位置、运动轨迹、姿态，进一步对人脸上的眼睛、嘴唇等特征进行提取的过程。
Face detection find faces information in the video sequence or image and determine facial size, position, trajectory, attitude, and further human face eyes, lips and other features extraction process.
结合矢量观测的特点，基于最小模型误差准则给出了一种确定卫星姿态的实时估计算法，称为预测滤波算法。
Considering the character of vector observation, a real time predictive filter based on minimum model error (MME) criterion is presented for satellite attitude estimation.
星图识别则是星敏感器确定空间飞行器姿态的关键技术。
Star pattern recognition is the key technic of satellite position confirmation from start sensor.
运用正交试验设计原理验证了用冗余度法所确定的最优关节对机械手姿态影响的显著性。
This paper uses the intersection experiment design principle to verify outstanding performance of the optimal joints, determined by redundancy method, for the manipulator posture.
通过对舰船运动姿态统计分析，以及对ARMA模型和AR模型等价性论证，确定了AR模型作为船舶姿态运动预报的数学模型。
By the statistical analysis of ship motion attitude and equivalent argument about ARMA model and ar model, ar model was identified to be the mathematic model for ship motion attitude prediction.
航天器间相对位置和姿态的确定是实现航天器编队飞行的重要基础。
The precise detection of the relative position and attitude between spacecrafts is very important, which is the base of autonomous control for spacecraft formation-flight.
GPS姿态系统是利用GPS载波相位测量来确定载体的航向和姿态角。
The GPS carrier phase measurements are used to determine the attitude of a vehicle.
针对存在不确定惯量矩阵和外干扰的刚体航天器姿态跟踪系统，提出了一种自适应滑模控制方法。
For rigid spacecraft attitude tracking system with uncertain inertia matrix and external disturbances, an adaptive sliding mode approach is presented.
研究了具有参数不确定和外部干扰的飞艇姿态跟踪控制问题。
The attitude tracking control problem for an airship with parameter uncertainties and external disturbances was considered.
最后，基于优化的总体最小二乘解确定光学特征点相对世界坐标系的姿态。
Finally, the attitude of optical characteristic points relative to the word coordinate system was obtained based on the optimization solution.
编队卫星的控制和应用需要确定编队卫星的运动状态，包括卫星绝对的和相对的位置、姿态以及钟差。
Control and application of satellite formation require measurement of the formation states, including absolute and relative position, attitude and clock bias separately.
基于正规性分析结果，使用系统不确定性反馈摄动描述对姿态控制系统的正规矩阵设计方法进行研究。
Based on the results, a normal matrix design approach for spacecraft attitude control systems is developed by using a feedback perturbation description for system uncertainties.
通过标定试验，确定了模型参数，获得了可用于姿态输出的角度计算公式。
Based on the calibration test, the model parameters are determined, and the output Angle function can be gotten.
通过标定试验，确定了模型参数，获得了可用于姿态输出的角度计算公式。
Based on the calibration test, the model parameters are determined, and the output Angle function can be gotten.
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