论文部分内容阅读
提出了在大姿态角情况下飞行器姿态参数的使用方法以实现像移速度的精确计算。根据飞行器轨道坐标系转换到飞行器坐标系的转换矩阵,推导了在大姿态角存在时轨道坐标系下的姿态角速度与飞行器坐标系下的姿态角和姿态角速度的关系式。通过计算得出,在侧摆角为30°时对飞行器坐标系绕飞行器轨道坐标系的转动角速度ωS1、ωS2和ωS3的影响最大误差分别为1.175%、50%和13.223%;在前后摆角为30°时对ωS1、ωS2和ωS3的影响最大误差分别为63.397%、0.1745%和63.397%。根据空间相机像移速度计算精度要求比较高,确定了在一定的姿态角情况下飞行器姿态参数使用方法。提出的方法简单,易于实现,适用于空间相机像移补偿的研究。
The method of using the attitude parameters of the aircraft under the condition of large attitude angle is proposed to realize the accurate calculation of the image movement speed. According to the conversion matrix of the orbital coordinate system converted to the aircraft coordinate system, the relationship between the attitude angular velocity in the orbiting coordinate system and the attitude angle and attitude angular velocity in the aircraft coordinate system when the large attitude angle exists is derived. By calculation, the maximum error of the angular velocity ωS1, ωS2 and ωS3 of the aircraft coordinate system about the orbital coordinate system of the aircraft when the roll angle is 30 ° are 1.175%, 50% and 13.223% respectively. When the swing angle is The maximum errors of ωS1, ωS2 and ωS3 at 30 ° are 63.397%, 0.1745% and 63.397%, respectively. According to the relatively high precision of the space camera image shift velocity, the method of using the attitude parameters of the aircraft under a certain attitude angle is determined. The proposed method is simple and easy to implement and is suitable for the research of space camera image shift compensation.