| 1. | Error analysis on getting inertial angular position with linear accelerometers is improved
改进了对线加速度计测量惯性姿态角的误差分析。 |
| 2. | Theory of getting inertial angular position from linear accelerometer measurements with double integration algorithm is analyzed
分析了使用线加速度计测量惯性角加速度,通过二次积分算法得到惯性姿态角的原理。 |
| 3. | The work of this paper include : 1 . the 3 - d solid entities of the external store , a missile , and the aircraft are modeled with a commercial cad software
在投放发射分离过程中，外挂物处于载机的近流场中，状态和姿态角的变化可能很大。 |
| 4. | The identification and compensation of the lever - arm effect in the shipboard inertial system are analyzed by which accurate measuring of roll and pitch angle is achieved
4 、分析了舰载晃动基座条件下，杆臂效应的辨识补偿与动态水平姿态角测量问题。 |
| 5. | When the signal of gps is lost for five minutes , the position error is about 1400 meters , its velocity error is about 15m / s and its attitude angle error is about 10 degree
在gps信号丢失5分钟时，位置误差大约为1400米，速度误差大约为15米/秒，姿态角误差大约为10度。 |
| 6. | At the end of the dissertation , the fuzzy pd track tail controller is designed . the pd controller and controller of attitude angle are made up of flight control system of helicopter
最后，本文设计了直升机模糊pd轨迹跟踪控制器，与姿态角控制器相结合，完成了对整个飞行控制系统的设计。 |
| 7. | In the system of tridimensional attitude measurement , the laser beams laser beams , and then shoot to the screen and the attitude of object can be calculated by the light - spot on the screen
三维姿态测量系统中,由激光器发出指示光束,照射至二边的屏幕上,由屏幕上的光斑位置反映出目标的各姿态角。 |
| 8. | Using orthogonal projective analytic method , the simplified formula of imv was deduced , ignoring the effect of aircraft ' s initial rotational angle , presuming the angle is zero
利用正交投影解析法推导像移速度公式，忽略了飞机的姿态角的变化，认为飞机的姿态角为零，所以它是简化的像移速度公式。 |
| 9. | Then the simulative model of six - degree of freedom in ocean current is established . 3 the ultimate angle in the simulation can be resolved when the law of quaternion is applied
3 、为防止仿真过程中出现奇异解，将四元数原理运用到仿真建模过程中，解决了仿真过程中可能出现的极限姿态角无法求解的问题。 |
| 10. | The method can eliminate the conventional fuzzy control system ' s steady - state errors and flutters . considering wind disturbance , the stabilized loop of pitch angle was designed and simulated with this method
9采用带优化修正函数无量化的模糊控制方法设计国产直九c海豚直升机的纵向姿态角稳定回路系统。 |
