1.The application of a pressure difference across an injector does not cause an immediate velocity response of the liquid propellant.
经过喷注器的压降发生变化时并不马上引起液体推进剂速度变化。
2.This paper introduces theoretical formulation optimization and ignition and combustion experiments of liquid propellant.
文内简述了液体药理论配方优选和液体药点火、燃烧实验研究。
3.for liquid propellant rocket engine , it is an important condition for effective combustion that propellant be evaporated and mixed quickly.
在液体火箭发动机中，推进剂组元迅速而高效的气化和混和是产生高质量燃烧所必须的重要条件。
4.It is an important and basic issue to choose monitoring parameters of Liquid propellant Rocket Engine(LRE) monitoring system in ground test.
确定监测参数是液体火箭发动机地面试验监控系统的一个重要而基础的问题。
5.The characteristics of NIR in liquid propellant are summarized and particular advantages of NIR in liquid propellant are pointed out.
总结了这种分析方法在液体推进剂中的应用特点。
6.Hydroxylammonium nitrate(HAN) is the main active toxic component of the new HAN based liquid propellant.
硝酸羟胺（HAN）是新型硝酸羟胺基液体推进剂的主要毒理活性成分。
7.Acceptance testing equipment for production of liquid propellant.
生产液体推进剂用的验收试验设备。
8.Based on the properties of combustion of droplets of a HAN-based liquid propellant LP1846, a simplified subarea model is presented.
针对HAN基液体发射药LP1846液滴的燃烧特点，建立相应的分区简化模型。
9.The missile is a single-stage, liquid-propellant design carrying a single nuclear warhead.
导弹是单级，液体推进设计能携带一枚单一的核弹头。
10.Well and layer selection criteria of liquid propellant high energy gas fracturing (HEGF) are included in this paper.
提出了液体药高能气体压裂选井、选层的条件。