| タイトル | Attitude determination and calibration using a recursive maximum likelihood-based adaptive Kalman filter |
| 本文（外部サイト） | http://hdl.handle.net/2060/19910007775 |
| 著者（英） | Kelly, D. A.; Lee, G. K. F.; Fermelia, A. |
| 著者所属（英） | Hughes Aircraft Co. |
| 発行日 | 1990-12-01 |
| 言語 | eng |
| 内容記述 | An adaptive Kalman filter design that utilizes recursive maximum likelihood parameter identification is discussed. At the center of this design is the Kalman filter itself, which has the responsibility for attitude determination. At the same time, the identification algorithm is continually identifying the system parameters. The approach is applicable to nonlinear, as well as linear systems. This adaptive Kalman filter design has much potential for real time implementation, especially considering the fast clock speeds, cache memory and internal RAM available today. The recursive maximum likelihood algorithm is discussed in detail, with special attention directed towards its unique matrix formulation. The procedure for using the algorithm is described along with comments on how this algorithm interacts with the Kalman filter. |
| NASA分類 | ASTRODYNAMICS |
| レポートNO | 91N17088 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/134229 |
|
