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首页> 外文期刊>International Journal of Engineering & Technology >Design and analysis of attitude control algorithm for low earth orbiting satellite with magnetic torquer concepts using nonlinear unscented Kalman filter
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Design and analysis of attitude control algorithm for low earth orbiting satellite with magnetic torquer concepts using nonlinear unscented Kalman filter

机译：使用非线性无限卡尔曼滤波器用磁性彩色扭矩概念的低地轨道轨道姿态控制算法的设计与分析

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Attitude control system plays the important role for to maintain the satellite to desired orientation. To control the satellite it is necessary to do the attitude stabilization. Attitude stabilization achieved by Star sensor, sun sensor, Earth sensors. Attitude control is mainly use for antenna pointing accuracy, camera focus to earth surface and solar panel pointing toward sun. Due to tumbling effects, satellite will rotate all the direction in the space. To maintain the orientation of the satellite it is necessary to design the attitude determination and control. Satellite consider as the rigid body. Inertia matrix describes the rigid body dynamics. The orientation of the satellite determine by Euler angle and Quaternion. The Low earth orbiting satellite will have enormous amount of aerodynamic drag stinking the satellite body and gravitational attraction another problem. Because of that satellite dwell, time is reduced. It means satellite more time spending particular part of the earth. The attitude estimation is measures by the orientation of vectors. Attitude estimation means to find the position and orientation of flying object with respect to the fixed reference of reference. Vector remains considered in the frame of reference to compute for find the orientation of the body of the satellite in the inertial reference system. The Earth is an inertial reference frame, and Satellite is a body frame. Attitude sensor used to measure the satellite orientation in the reference frame. This will help in accurately predicting the orbit deviation and a control system to correct if any by providing the satellite momentum means ‘mass in motion’ changes in a body rapidly in Low earth orbit due to centripetal force acting on a satellite. Attitude control system (ACS) need the numerical simulation to find the required torque demand by the help of difference between reference input (Attitude) signal and feedback signal measure by attitude sensor to trim the control surface maintain the actuator required orientation . The results will consist of two parts the first part consisting of the attitude estimation using Euler angle and Quaternion method, second part consist of estimate the control torque from magnetic torquer and error estimation using non-linear filter (Unscented Kalman Filter) with MATLAB simulation.
机译：姿态控制系统对维持卫星保持所需方向的重要作用。控制卫星有必要做姿态稳定。态度稳定通过星传感器，太阳传感器，地球传感器实现。姿态控制主要用于天线指向精度，相机焦点到地球表面和太阳能电池板指向太阳。由于扭曲效果，卫星将在空间中旋转所有方向。保持卫星的方向，有必要设计姿态确定和控制。卫星认为是刚体。惯性矩阵描述了刚体动态。卫星的方向通过欧拉角和四元数确定。低地球轨道卫星将具有大量的空气动力学阻力，使卫星体系和引力吸引力另一个问题。因为卫星停留，时间减少了。这意味着卫星在地球的特定部分花费更多时间。态度估计是通过向量的方向衡量的。姿态估计意味着找到飞行对象的位置和方向相对于固定参考的参考。向量仍然在参考框架中考虑，以计算惯性参考系统中卫星体的定向。地球是惯性参考框架，卫星是车身框架。用于测量参考框架中的卫星取向的态度传感器。这将有助于准确地预测轨道偏差和控制系统，以校正如果通过在低地球轨道上迅速地在卫星上迅速地改变体内的卫星动量意味着“质量”。姿态控制系统（ACS）需要数值模拟，通过姿态传感器的参考输入（姿态）信号和反馈信号测量的差异来找到所需的扭矩需求，以修剪控制表面，维持致动器所需的方向。结果将由使用欧拉角和四元度方法组成的第一部分组成的第一部分，第二部分包括使用MATLAB模拟的非线性滤波器（Unscented Kalman滤波器）估计来自磁头的控制扭矩和误差估计。

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