摘要
为了在多管火箭发射过程中能获得准确的定向器管口振动信号,研究了多管火箭发射过程中定向器管口振动特性;利用多体系统传递矩阵法和发射动力学理论,建立了多管火箭发射动力学模型和仿真系统,通过多管火箭模态试验验证了模型的正确性;仿真获得了在发射过程中定向器管口振动的时域历程,利用离散傅里叶变换(DFT)技术,获得了在发射过程中定向器管口振动位移、速度和加速度信号的频域特性;在此基础上设计了椭圆滤波器,并通过对发射过程中定向器管口的加速度采集信号的滤波前后对比,验证了该研究内容的正确性和重要性,为多管火箭发射过程中定向器运动信号的采集和控制提供了重要参考价值。
To exactly obtain the vibration characteristic of launch guider muzzle of a multiple launch rocket system （MLRS） in firing process, its dynamic behavior was studied. The dynamic model of MLRS and its simulation system were established by using transfer matrix method of multibody system and the theory of firing dynamics. The model was validated with modal test results of the original vibration characteristic of MLRS. The time history of vibration signals of the launch guider muzzle in firing process was obtained with the simulation system ; by using the technology of discrete Fourier transformation （DFT） , the frequency characteristic of displacement, velocity and acceleration of the launch guider muzzle in firing process was obtained. Based on these, an elliptic filter was designed. By comparing the acceleration signal of the launch guider muzzle with the filter and that without the filter, the correctness and the importance of this study were verified. The study results provided a reference for collecting and controlling vibration signals of the launch guider of a MLRS in firing process.
出处
《振动与冲击》
EI
CSCD
北大核心
2012年第1期35-38,139,共5页
Journal of Vibration and Shock
基金
江苏省自然科学基金攀登计划资助项目(BK2008046)
国家自然科学基金(11102089)
关键词
多管火箭
振动
仿真
多体系统传递矩阵法
离散傅里叶变换
滤波器
multiple launch rocket system （MLRS）
vibration
transfer matrix method of multibody system
simulation
transfer matrix method of multibody system
discrete Fourier transformation
filter
