摘要
对于腰部支承的发射装置,需要避免飞行器起飞分离后,发射装置支撑部分干涉飞行器喷管结构。一种集后倒功能、支承功能于一体的发射装置支承臂为弹簧作动筒和支承臂的支承组合方式,在被支承物离开支承臂时,支承臂在弹簧作动筒带动下可以实现迅速后倒并产生少量回弹。支承臂后倒及回弹动力学特性影响火箭分离过程中的安全间隙。考虑不同材料的减振、吸能特性,基于动力学仿真,对弹簧作动筒内部的弹性元件进行分析,对比分析影响支承臂后倒回弹量的特征参数,提出采用橡胶减振器替代弹簧的技术方案,同时开展试验研究,实现了支承臂回弹量的有效控制。
For an aircraft launcher supported at the waist,it is necessary to avoid interfering with the nozzle structure of a vehicle after its leaving the launch pad completely.This article proposes a study on a support arm of a launch pad that integrates backward and supportive functions.A support arm contains a spring-actuator and an arm,and,when the rocket leaves the arm,it quickly falls backward and rebounds slightly driven by the spring actuator.Kinetic characteristic on fall-back and rebound of the support arm affects the safety clearance during the rocket’s separation.Considering damping and energy-absorption of different materials,based on dynamic simulation,the elastic elements inside the spring actuator are analyzed,a technical solution to replace the spring with a rubber damper is proposed,and,meanwhile,experimental research is carried out,which achieves effective control of the rebound amount of the support arm.
作者
周彦均
张雁思
徐铮
黎定仕
ZHOU Yanjun;ZHANG Yansi;XU Zheng;LI Dingshi(Beijing Institute of Space Launch Technology,Beijing 100076,China)
出处
《兵器装备工程学报》
CAS
CSCD
北大核心
2022年第S02期380-386,共7页
Journal of Ordnance Equipment Engineering
关键词
弹簧作动筒
动力学仿真
减振器
spring actuator
dynamic simulation
rubber damping