|Table of Contents|

Integrated Navigation Technology of Reusable Booster Vehicle

《南京理工大学学报》(自然科学版)[ISSN:1005-9830/CN:32-1397/N]

Issue:
2011年03期
Page:
316-320
Research Field:
Publishing date:

Info

Title:
Integrated Navigation Technology of Reusable Booster Vehicle
Author(s):
HAN Peng-xinMU Rong-junCUI Nai-gang
Department of Astronautics Engineering,Harbin Institute of Technology,Harbin 150001,China
Keywords:
reusable booster vehicle integrated navigation partitioned matrix inversion partial information fusion
PACS:
V249.328
DOI:
-
Abstract:
To improve the navigation accuracy of a rocket powered reusable booster vehicle(RBV)in a fly-back mode,an integrated navigation scheme is designed.The system error models under the launch point inertial coordinate are established.The multi-sensor information fusion technology based on federated filters is improved.According to the characteristics of the estimation error covariance matrix,a new kind of partial information fusion method of inversion of partitioned matrix is proposed.The relative simulations under the typical flight situation validate that the integrated navigation scheme and algorithm improves the navigation accuracy of RBV fly-back process,especially the landing point.Compared with the inertial navigation system,the positioning error of the integrated navigation system decreases from hectometer to within 5 m,the speed trial error decreases from 0.2~1.0 m/s to within 0.01 m/s,the attitude determination accuracy improves from 0.1′ to 0.02′.

References:

[1] Bandu N P,Paul V T,Brett R S. Ascent, stage separation and glideback performance of a partially reusable small launch vehicle[A]. 42nd AIAA Aerospace Sciences Meeting and Exhibit[C]. Reno,Nevada,USA: AIAA, 2004: 1 - 16.
[2] Deneu F,Malassigne M,Le-couls O,et al. Promising solutions for fully reusable two-stage-to-orbit configurations [J]. Acta Astronautica, 2005, 56( 8) : 729 - 736.
[3] Martin S,Chiara M,Holger B. Long-term/strategic scenario for reusable booster stages[J]. Acta Astronautica, 2006, 58( 4) : 209 - 221.
[4] Yoshinori M, Ishimoto S,Mori T, et al. Design study on a small-sized partially reusable launch system[A]. AIAA/CIRA 13th International Space Planes and Hypersonic Systems and Technologies[C]. Tokyo, Japan: AIAA, 2005: 1 - 12.
[5] 李跃,邱致和. 导航与定位———信息化战争的北斗 星[M]. 2 版. 北京: 国防工业出版社,2008: 100 - 110.
[6] 董绪荣. GPS /INS 组合导航定位及应用[M]. 长沙: 国防科技大学出版社, 1998: 89 - 91.
[7] 付梦印,邓志红,张继伟. Kalman 滤波理论及其在导 航系统中的应用[M]. 北京: 科学出版社,2003: 158 - 173.
[8] 杨元喜. 自适应动态导航定位[M]. 北京: 测绘出版 社, 2006: 287 - 288.
[9] 崔乃刚,韩鹏鑫,穆荣军. 基于微小型传感器的惯 性/卫星/天文组合导航方法[J]. 中国惯性技术学 报, 2008, 16( 1) : 68 - 72.

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Last Update: 2012-06-30