飞行器推力偏心及质心漂移总体估算方法研究  

Estimate Methods Research on Thrust Eccentricity and Centroid Drift of the Exoatmosphere Aircraft

作　　者：张朋[1] 谭湘霞[1] 

机构地区：[1]北京电子工程总体研究所,北京100854

出　　处：《现代防御技术》2015年第4期62-67,共6页Modern Defence Technology

摘　　要：对于在大气层外采用直接侧向力控制的飞行器来说,由于推力偏心以及质心漂移的存在,飞行器轨控发动机在工作时,会在滚转、俯仰、偏航等通道中产生附加的姿态干扰力矩。若干扰力矩过大,就会导致姿态失稳。首先建立了一个完整的基于直接侧向力控制的飞行器仿真模型,以动力学模型为基本方程,分别采用扩展卡尔曼滤波(EKF)和无迹卡尔曼滤波(UKF)推导出了飞行器推力偏心和质心漂移的滤波模型。最后给出了仿真算例,验证了滤波模型的正确性并对2种滤波模型的特性进行了对比。For the will cause them to roll, exoatmosphere aircraft that are controlled by direct lateral yaw and on. If the disturbance torque is model of the aircraft based on th centroid drift model is deduced pitch and generate attitude interference torque du too large, it can lead to loss of stability attitude. e force, divert thruster ring thruster switching Firstly, a simulation direct lateral force is established. Secondly, a thrust eccentricity and through extended kalman filter （EKF） and unscented kalman filter （UKF） based on kinetic equation. Finally, a simulation example is given to verify the correctness of the model and two filter models＇characteristics was compared.

关 键 词：大气层外 直接侧向力 推力偏心 质心漂移 扩展卡尔曼滤波 无迹卡尔曼滤波 

分 类 号：TJ765.2[兵器科学与技术—武器系统与运用工程] TP391.9[自动化与计算机技术—计算机应用技术]