摘要
为了分析丝杠推杆式和斜盘式偏转机构的适用性,首先建立了偏转弹头导弹的线运动、角运动方程,总结出弹道、控制系统设计对线运动、角运动方程的要求;然后将安装两种偏转机构后导弹的质量特性代入动力学模型进行仿真。仿真结果表明:丝杠推杆式机构能满足弹道、控制系统设计对线运动、角运动方程的要求,是适用性机构;斜盘式机构仅能满足弹道设计对线运动方程的要求,不是适用性机构。进一步研究中应当重视丝杠推杆式机构的研制。
The nose-deflecting mechanism plays an important role in deflectable nose control. In this article, the applicability of two nose-deflecting control mechanisms including a screw-push beam mechanism and a rolling-sloping plat mechanism are studied. Firstly, the translational equation and the rotational equation of a deflectable nose missile are developed. Secondly, the requirements of trajectory design and control system design to the translational equation and rotational equation are put forward. Then the quality characteristics of a deflectable nose missile with a screw-push beam mechanism and a missile with a rolling-sloping plat mechanism are introduced to the dynamic model for simulations. Finally, a conclusion is achieved that the screw-push beam mechanism is applicable for deflectable nose control, while the rolling-sloping plat mechanism is not applicable.
出处
《应用力学学报》
CAS
CSCD
北大核心
2014年第5期678-684,826,共8页
Chinese Journal of Applied Mechanics
关键词
偏转弹头
丝杠推杆式机构
斜盘式机构
动力学
适用性
deflectable nose control,the screw-push beam mechanism,the rolling-sloping plat mechanism,dynamics,applicability
