液体火箭发动机后效冲量的测量方法  

Measuring Methods of Cutoff Impulse for Liquid Propellant Rocket Engine

作　　者：陈鸿彦 

出　　处：《宇航计测技术》1989年第6期37-42,共6页Journal of Astronautic Metrology and Measurement

摘　　要：本文叙述在地面条件下试验液体火箭发动机时,通过测量发动机后效段推力与测量发动机燃烧室压力两种方法来求得模拟高空后效冲量,并对这两种方法作简单评论。Through two methods measuring cutoff thrust and pressure of com- bustion chamber when testing liquid propellant rocket engine on ground, cu- toff impulse as simulated altitude condition is obtained. These methods are revie- wed simply, too.

关 键 词：火箭发动机 液体火箭 后效冲量 

分 类 号：V434.1[航空宇航科学与技术—航空宇航推进理论与工程]