摘要
讨论了在火箭固有振动频率下测量振型斜率的几种计算和测试方法，分析了影响振型斜率测量和符号误判的误差源，提出了按秒状态变化进行振型斜率修正的最小二乘曲线拟合法。研究表明，以参照点陀螺信号为基准计算相位角，可以避免相位符号的误判。这一改进对于以相位符号作为稳定性判别准则的控制系统来说是至关重要的。
In this paper, a few mode shape slopes calculateing and measureing methods are discussed inrocket natural vibrtion frequency. The error source effected on mode shape slopes measurment and phasesign error judgement was analyzed. The least-squares curve fit methods for the mode shape slopes cor-recteing as a variety of test secorid condition was proposed. The research results show that phase angle cal-culate according to normalized point gyro as refrence signal then mode splpe sign judgement error can be e-liminated. The innovation is very important and valuable for useing phase sign as control stability criterionin control system design analysis.
出处
《强度与环境》
北大核心
1996年第3期46-53,共8页
Structure & Environment Engineering
关键词
运载火箭
结构动力学
模态振动试验
模态参数
Launch vehicle, Structural dynamics, Modal vibration test, Modal parameter
