典型弹道下的火箭弹MEMS-INS/GNSS组合导航姿态误差可观性分析

doi:10.3969/j.issn.1000-1093.2014.06.015

摘要/Abstract

摘要： 以炮射火箭弹的MEMS-INS/GNSS组合导航系统为研究对象，在奇异值法分析系统可观性的基础上，提出了系统状态的等效奇异值概念，作为系统状态可观性的度量标准。在此基础上，重点分析了火箭弹在无控、俯仰机动以及偏航机动3种弹道条件下的姿态角误差的等效奇异值(可观性)的变化规律，并据此得出：滚转角误差在弹体机动时可观性较好；当弹体所在垂面存在较大的加速度时，俯仰角误差可观性较好；方位角误差在弹体水平加速度较大时可观性较好。通过仿真，验证了可观性分析结果的正确性。

关键词: 控制科学与技术, 火箭弹, 微机电系统, 可观性

Abstract: MEMS-INS/GNSS integrated navigation system for artillery launched rockets is taken as the research object. Based on the singular value decomposition of system observability matrix, a new concept, “equivalent singular value”, is proposed to test the observability of a system state. The method is used to analyze the observability of Euler angle errors in three kinds of trajectories without maneuver and with pitch and yaw maneuvers. The curves of “equivalent singular value” (observability) of three Euler angles errors are plotted, which illustrate that the roll error observability becomes better when projectile body maneuvers, the pitch angle error observability is mainly related to the acceleration in the axis of the body symmetry, and the azimuth error observability is proportional to horizontal acceleration. The simulation results are consistent with the analysis results.

Key words: control science and technology, rocket, MEMS, observability

中图分类号:

E927

董进龙, 莫波. 典型弹道下的火箭弹MEMS-INS/GNSS组合导航姿态误差可观性分析[J]. 兵工学报, 2014, 35(6): 850-856.

DONG Jin-long, MO Bo. Observerbility Analysis of Rocket MEMS-INS/GNSS Integrated Navigation System Attitude in Classic Trajectories[J]. Acta Armamentarii, 2014, 35(6): 850-856.

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