摘要
研究了多管火箭非满管射击密集度试验方法及仿真技术,提供了一种新的减少多管火箭密集度用弹量的试验方法。应用发射动力学和多体系统传递矩阵法理论,建立了多管火箭发射动力学模型,推导出了多管火箭振动特性和动力响应方程,形成了基于等起始扰动思想的多管火箭非满管射击密集度试验方法。对某多管火箭的密集度和射击精度进行了仿真预测,仿真结果得到了试验验证。对满管齐射和非满管射击方案的起始扰动进行了仿真,仿真结果表明起始扰动相同是系统密集度相同的前提。形成的非满管试验方案可减小某多管火箭密集度试验用弹量75%。
Test method and simulation technology of the non-full loading firing dispersion for multiple launch rocket system （MLRS） are studied. A new test method for reducing rocket consumption in dispersion test of MLRS is presented. Launch dynamics and transfer matrix method of muhibody system are used to develop a launch dynamics model, equations of vibration characteristics and dynamic response. The firing dispersion test method of a non-full loading fire rocket based on the idea of equal initial disturbance is presented. The firing dispersion and the precision of a MLRS are simulated. The simulation results are validated by test results. The initial disturbance of full loading and non-full loading firing scheme is simulated. The simulation results show that the equal initial disturbance is the precondition for the equal firing dispersion. The number of rocket consumption in firing dispersion experiment of a MLRS can be decreased by 75% using the non-full loading test scheme.
出处
《南京理工大学学报》
EI
CAS
CSCD
北大核心
2009年第1期83-87,共5页
Journal of Nanjing University of Science and Technology
基金
江苏省自然科学基金(BK2008046)
关键词
等起始扰动
密集度
非满管
试验方法
equal initial disturbance
firing dispersion
non-full loading
test method
