运载火箭静电带电理论研究与试验验证  

Theoretical research and experimental verification of launch vehicle electrostatic charging

作　　者：郗琦 晁鲁静[2] 王海涛 胡晓峰[3] 

机构地区：[1]北京宇航系统工程研究所 [2]中国运载火箭技术研究院研究发展中心,北京100076 [3]军械工程学院静电与电磁防护研究所,石家庄050003

出　　处：《航天器环境工程》2016年第3期282-288,共7页Spacecraft Environment Engineering

摘　　要：运载火箭在大气中飞行会使箭体、发动机等表面带电,当静电累积达到一定量级并产生静电放电时,可能对箭上电气设备造成灾难性后果。在众多起电原因中,文章重点研究发动机喷流起电和摩擦起电过程,提出这2种起电方式的计算模型,并结合相关静电测量试验,确定这2种起电方式的等效充电电流,定量分析火箭最大静电带电电位,为指导单机设计及系统防护提供参考。The surface of a launch vehicle and its engine will be charged during the flight, with drastic consequences when the electronic static charges have accumulated to some extent. Among many causes, this paper focuses on the electrification process of the engine’s jet flow and friction. The calculation model of these two kinds of electrification is established. The equivalent charging current of these two kinds of electrification is determined combined with the electrostatic measurement experiment, thus the maximal charging potential is analyzed, to provide a guidance for the product design and the system protection.

关 键 词：运载火箭 摩擦起电 喷流起电 静电电位 

分 类 号：O441[理学—电磁学]