| 1. | Satellite attitude determination with modified rodrigues parameters without gyro
里格参数的星体姿态确定 |
| 2. | A micro - satellite attitude determination algorithm based on unscented kalman filter
基于平淡卡尔曼滤波器的微小卫星姿态确定算法 |
| 3. | The simulation results showed the methods represented in this thesis were effective and feasible
仿真结果证明了本文提出的svom卫星姿态确定和控制方法的有效性和可行性。 |
| 4. | Chapter studies attitude determination problem by multi - antenna . the coordinate system and ad - algorithm is introduced firstly
第三章研究卫星导航系统中多天线姿态确定问题。 |
| 5. | A test platform for three dimensions attitude and relative attitude determination is established . the algorithms and the test platform is tested
建立了gps三维姿态确定和编队卫星相对姿态确定实验系统，编制了姿态确定、相对姿态确定软件。 |
| 6. | In this thesis , the method of the attitude determination by gps is developed . the method consists of two parts : ambiguity resolution and attitude determination
Gps姿态确定问题分两大部分，一部分是模糊度求解，另一部分是姿态确定算法。 |
| 7. | In general , the estimation accuracy not only lies on the performance of the hardware of the measurement , but also the attitude estimation algorithm
姿态确定的精度不仅取决于姿态测量系统硬件配置的性能与精度,还与所采用的姿态确定算法密切相关。 |
| 8. | Satellite attitude determination system is the important part of the attitude control system ( acs ) , and its accuracy is the key factor for the performance of the acs
卫星姿态确定系统是卫星姿态控制系统中的重要组成部分,其精度是影响姿态控制系统精度水平的决定性因素。 |
| 9. | Second , draw a comparison of various estimate method of position and attitude , we adopt to make use of kalman filter to estimate position and attitude of lunar rover
最后,为了测试不同的运动轨迹对月球车位置、姿态确定的影响,根据月球车的运动规律,设计了三个不同的动力学模型。 |
| 10. | 5 . aiming to a specific satellite , a kind of scheme of high accuracy fault - tolerant satellite ' s attitude determination system is designed , and testified by mathematical simulation
针对某太阳同步极轨卫星，设计一种高糟度容错卫星姿态确定系统方案，井邀过羟学仿真验证了该方案的可行性。 |
