摘要
针对难以配置高精度部件的皮纳卫星姿态测量系统,当卫星处于阴影区或任何太阳敏感器不可用的状态下,MEMS陀螺与磁强计的组合便成为卫星在轨姿态测量精度的重要保障。本文基于MEMS陀螺与磁强计的低功耗、全轨、全天时、最小姿态敏感组合,提出一种适用于皮纳卫星在轨运行的滤波系统方案。该方案通过滑窗ARMA建模降低陀螺随机噪声的影响,并由姿态滤波器估计所得的零偏在线去除陀螺常值分量,以保证其建模的长期有效性。本文以浙江大学皮星二号卫星搭载的敏感部件以及姿态测量算法为研究基础,结合在轨实测数据,仿真对比表明,该系统方案有效降低了陀螺随机噪声,抑制比达50%以上;陀螺零偏估计精度提高310%,可达到0.001°/s;姿态确定精度提升190%,可达1.212 7°。该系统方案是对皮纳卫星姿态确定最小系统精度提升及实用方案设计的有益探索。
For Pico and Nano-satellites which can hardly configure high-precision attitude sensors,the sensor combination of MEMS gyro and magnetometer has become an important guarantee of satellite in-orbit attitude measurement,especially when sun-sensor is not available. Based on this low-cost,all-orbit,all day,and minimum sensor combination,a filter system was proposed suitable for on-orbit operation. In this system,a sliding window ARMA modeling is used to reduce the gyro random noise,and the gyro bias is removed online by the attitude filter to ensure the long-term validity of the mathematical model. Based on the on-board sensors and algorithms of ZDPS-2 satellite,and combined with the on-orbit data,the simulation results show that the proposed filter system can effectively reduce the random noise of gyro,and the suppression ratio is more than 50%. The accuracy of gyro bias estimation is improved by 310%,reaching 0.001 °/s,and the accuracy of attitude estimation is improved by 190% to 1.212 7°. The proposed system can be a useful exploration and a practical design for Pico and Nano-satellite attitude determination.
作者
杜超禹
蒙涛
金仲和
DU Chaoyu;MENG Tao;JIN Zhonghe(School of Information Science and Electrical Engineering, Zhejiang University, Haagzhoa 310027, China;School of Aeronautics and Astronautics ,Zhejiang University,Hangzhou 310027,China)
出处
《传感技术学报》
CAS
CSCD
北大核心
2018年第1期152-157,共6页
Chinese Journal of Sensors and Actuators
基金
国家自然科学基金项目(61525403,61503334)
