Abstract
When the aircraft is under large angular acceleration maneuvering, the predicted deviation in the star-tracking algorithm of star sensor will be enlarged due to the widened scanning region, longer identification time and lower data update rate. In this paper, a new star-tracking algorithm is presented which exploits the information of the star sensor and gyro to solve these problems. First, the aircraft attitude at next time is calculated out by using the attitude data from integrated navigation and the angle velocity data from gyro. Second, star coordination in star image at next time is achieved by coordination transformation. The theoretic analysis and simulation indicate that the predicted deviation is within 10 pixels when the aircraft is under extreme situations with a maximum angular acceleration of 30°/s2 and a maximum angular velocity of 30°/s. Therefore star scanning and star pattern recognition can be rapidly finished, and the performances of star sensor are improved.
| Original language | English |
|---|---|
| Pages (from-to) | 706-710 |
| Number of pages | 5 |
| Journal | Zhongguo Guanxing Jishu Xuebao/Journal of Chinese Inertial Technology |
| Volume | 18 |
| Issue number | 6 |
| State | Published - Dec 2010 |
Keywords
- Integrated navigation
- Large angular acceleration
- Prediction deviation
- Star tracking algorithm
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