Attitude Estimation of Guided Artillery Shells based on GPS/INS
In this paper, an algorithm is developed to estimate the attitude of guided artillery shells based on a GPS and an IMU sensor. The operation stages of the guided artillery shells are composed of the parabolic trajectory phase of free flight and the gliding phase with guidance to the target. By evaluating the convergence rate of the GPS/INS algorithm as well as observability of the shell attitude during each flight phase, we checked the applicability of the algorithm in real world. Because of the slow the convergence rate of the algorithm, a roll attitude estimation filter is designed using only a GPS and rate gyro signals without accelerometer measurement signals. The estimated roll attitude angle is used the initial value of roll angle in the GPS/INS algorithm. The performance of the combined system of the GPS/INS algorithm and the roll attitude estimation algorithm was evaluated by comparing the convergence rate of attitude estimation through various numerical simulation. It is concluded that the initial roll attitude angle estimation improves the instability of the GPS/INS algorithm and resolves the slow convergence rate problem of the algorithm.
GPS/INS Kalman Filter Gliding Artillery Shell Attitude estimation,Observability
Jaemin Sung Ihnseok Rhee Byoung Soo Kim
School of Aerospace Engineering, Gyeongsang National University,900 Gazwa, Jinju,Gyeongnam, South Ko School of Mechatronics Engineering, Korea University of Technology and Education,Byeongcheon, dongna
国际会议
2011年亚太航空航天技术学术会议(APISAT 2011)
澳大利亚
英文
1-13
2011-02-28（万方平台首次上网日期，不代表论文的发表时间）