摘要
以气压力传动动力学和机构动力学为理论基础 ,建立氮气作动筒系统动特性数字仿真模型 ,提出了基于导弹俯仰角和俯仰角速度的双目标优化函数 ,利用小波算法中的奇异性检测原理 ,求得系统优化中的最佳初始迭代点 ,再用混合罚函数法求得系统最优解 ,并用试验对优化设计结果进行了验证 .
A physical and mathematical model is proposed for describing pneumatic device system based on the dynamics of pneumatics and mechanisms,and a digital simulation program is developed to analyze the dynamic performance of system.The multi objective optimization for the pitching angle and velocity of missile was proposed for the first time.Singularity detection in wavelet analysis was conducted to find the optimum iteration point of system's optimization.The sequence unconstrained minimization technology based on wavelet and complex method were compared to show the former was better for optimal design.And the optimization results agrees well with the experiment ones.
出处
《弹道学报》
CSCD
北大核心
2002年第1期73-76,83,共5页
Journal of Ballistics
