Research and Analysis of Micro-Motion Characteristic Based on Linear Swing of Missile
According to the unique micro-motion state of missile body in space flight, a micro-motion mathematical model of missile spatial linear swing was built by rigid attitude dynamics and radar detection equation, the internal relationship between micro-motion characteristic and attitude motion of missile body was analyzed, and the analytical relationship between micro-Doppler and radial velocity of radar was derived, then micro-motion state parameters were estimated、 simulated and the micro-Doppler information was extracted by the CW radar echo signal to judge the stability、motion attitude or something like these of flying missile body, it laid the practical value theoretical basis for the analysis and design of missile guidance and control system.
missile micro-motion linear swing micro-Doppler
ZHANG Wanjun WANG Fei Hu Cheng YANG Jun LENG Xuebing
The Academy Armored Forces Engineering, Department of Arms Engineering, Beijing, China,100072 School of Mechatronic Engineering, Beijing Institute of Technology,Beijing,100081 Department of Logi Common Equipment Support Department of General Department of Equipment, Beijing, 100720 Baicheng Ordnance Test Center Baicheng, China 137001
国际会议
第八届国际测试技术研讨会(8th International Symposium on Test and Measurement)
重庆
英文
427-430
2009-08-01（万方平台首次上网日期，不代表论文的发表时间）