CAJ | 학술논문

针对小型尾坐式飞行器姿态估计问题，设计了由陀螺、加速度计、磁强计组成的姿态测量系统。为了抑制MEMS陀螺漂移导致的姿态误差，以四元数为状态变量，以加速度计和磁强计的输出作为观测变量，建立了滤波模型。采用平方根无迹卡尔曼滤波( SRUKF)对传感器信息进行融合，保证了滤波算法的数值稳定性。由于小型尾坐式飞行器抗干扰能力弱，引入自适应算法，解决了量测信息受到干扰时滤波精度下降的问题，提高了系统的鲁棒性和可靠性。仿真结果表明，存在外界磁场干扰时，姿态误差小于1o。通过实际飞行实验，验证了算法的可行性。
침대소형미좌식비행기자태고계문제，설계료유타라、가속도계、자강계조성적자태측량계통。위료억제MEMS타라표이도치적자태오차，이사원수위상태변량，이가속도계화자강계적수출작위관측변량，건립료려파모형。채용평방근무적잡이만려파( SRUKF)대전감기신식진행융합，보증료려파산법적수치은정성。유우소형미좌식비행기항간우능력약，인입자괄응산법，해결료량측신식수도간우시려파정도하강적문제，제고료계통적로봉성화가고성。방진결과표명，존재외계자장간우시，자태오차소우1o。통과실제비행실험，험증료산법적가행성。
For attitude estimation of small tail-sitter aircraft, the attitude measurement system composed of gyroscope,accelerometer and magnetometer is designed. In order to prevent the attitude error caused by drift of MEMS gyroscope,the filter model is established with quaternion as state variables and the output of accelerometer and magnetometer as measurement information. Square root kalman filter ( SRUKF ) is carried out on the sensor information fusion to guarantee the numerical stability of filtering algorithm. Due to the weak anti-interference ability of small tail-sitter aircraft, the adaptive algorithm is introduced, which solves the problem of the decline of the filtering precision when measurement information is interferenced and improves the robustness and reliability of the system. Simulation results show that attitude error is less than 1ounder the condition of magnetic disturbance. Actual flight test verifies the feasibility of the algorithm.