航空时敏炸弹SINS/GNSS组合导航系统设计(英文)  

Design of SINS/GNSS integrated navigation system for aerial time-critical guided bomb

作　　者：陈帅[1] 雷浩然[1] 薄煜明[1] 徐芹丽 

机构地区：[1]南京理工大学自动化学院,南京210094

出　　处：《中国惯性技术学报》2014年第2期195-199,共5页Journal of Chinese Inertial Technology

基　　金：国家自然科学基金委员会和中国工程物理研究院联合基金资助(U1330133);江苏省自然科学基金(BK20130774)

摘　　要：为满足机载精确制导弹药小型化、高可靠性方面的要求,设计了一体化闭环光纤惯导/GNSS紧凑型组合导航系统,该样机基于DSP C6747+FPGA浅并行架构,运用自适应卡尔曼滤波算法实现组合导航系统的信息融合,样机整体尺寸为13 cm×14 cm×12 cm。为验证系统性能,搭建了弹载组合导航半实物仿真平台,通过计算机仿真模拟目标信息和炸弹飞行全过程,分析了在组合导航系统辅助下制导炸弹对目标的打击精度,最后对样机进行了地面跑车试验的考核。半实物仿真与地面跑车试验结果表明,该组合导航系统具有较好的实时性和稳定性,导航精度满足精确打击的要求。To satisfy the requirements of miniaturization and high reliability for airborne precision guided munitions, a compact close-loop FOG IMU/GNSS integrated navigation system is designed based on DSP C6747+FPGA shallow-parallel architecture. An adaptive Kalman filter is designed for information fusion, and the principle prototype's overall size is 13 cm× 14 cm × 12 cm. A hardware-in-loop simulation scheme is designed for analyzing the integrated navigation system performance through computer simulation of target information and flight course. The simulation and ground test results show that the integrated navigation system offers better stability and real-time performance, and its accuracy meets the requirement for precision strike.

关 键 词：组合导航系统 卡尔曼滤波 制导炸弹 半实物仿真 

分 类 号：V249.3[航空宇航科学与技术—飞行器设计]