Attitude Algorithm of MEMS IMU for Advanced Rocket Ammunitions with Swing Markov IMM
The error correction of MEMS Inertial Measure ment Unit (IMU) is often implemented by the model filtering as well as the compensation of instrument error, which effectiveness of filtering is determined by the coherence between the models of filter and the maneuver modes of weapons. As the maneuverability of advanced rocket ammunitions with the lateral thrust greatly increased, the traditional filter models such as Constant Velocity (CV) are hardly matched against the rocket attitude oscillations with high frequency. Fortunately the attitude oscillations after the lateral thrust boost are similar to the damped oscillations with natural frequency, which natural frequency and damp ratio could be obtained from the aerodynamic analysis for rocket body. This paper introduced Swing Markov model into describing the attitude oscillations and proposed Swing Markov Interacting Multiple Model (IMM) with two models to establish the combinational filter, which corresponded with the attitude motion of advanced rocket ammunitions. The results and analysis of digital simulation for advanced rocket ammunitions demonstrated the satisfied accuracy of Swing Markov IMM filtering for attitude angle and angular ratio.
inertial measurement unit swing markov attitude filtering rocket ammunitions
Lu Xiaodong Zhou Jun He Yuanjun
College of Astronautics Northwestern Polytechnical University Xian, China Center of Research and Development Sichuan Academy of Aerospace Technology Chengdu, China
国际会议
成都
英文
166-169
2010-06-12（万方平台首次上网日期，不代表论文的发表时间）