结论液体火箭推进剂致伤后的远期效应明显。
Conclusion Chronic effect, induced by liquid rocket propellant, was observed in our study.
目的复制冲击波和液体火箭推进剂中毒致冲毒复合伤的动物模型。
Objective To establish model of the blast-toxicosis combined injury caused by the explosion of the liquid propellant.
研制了一种能有效防护液体火箭推进剂的正压式轻型防护服，利用电动送风技术，极大提高了穿着的舒适性。
Positive pressure light protective appliance for liquid propellant was manufactured, by using the electric airing technology, the dressed comfortability was enhanced.
结论利用生物激波管冲击和染毒柜染毒相结合的形式可以模拟复制现场液体火箭推进剂爆炸致冲毒复合伤的动物模型。
It was stable, economical, practical and easy to repeat. Conclusions Injury caused by the explosion of liquid propellant can be simulated by using the blast wave tube and the intoxication tank.
本研究针对我国航天发射场液体火箭推进剂作业中存在的危险性，利用安全系统工程原理，对推进剂作业的危险因素进行了系统分析。
This research aimed at the fatalness for using liquid rocket propellant in our country spaceflight launch site, applied the principle of safe system engineering to analysis the dangerous factors.
分析了固液发动机推进剂的燃烧特性和发动机性能特性、与液体和固体火箭发动机的不同，以及研制的技术难度等。
The propellant feature of burning behavior and engine in hybrid engine, the differences to liquid and solid engine and the difficulties of technology in development were analyzed.
液体推进剂的晃动特性对大型液体运载火箭以及战略弹道导弹的飞行动力稳定性有着很大的影响。
The dynamic behavior of the liquid sloshing has great effect on the dynamic stability of the liquid filled space vehicle and the strategical ballistic missile.
液体推进剂的晃动特性对大型液体运载火箭以及战略弹道导弹的飞行动力稳定性有着很大的影响。
The dynamic behavior of the liquid sloshing has great effect on the dynamic stability of the liquid filled space vehicle and the strategical ballistic missle.
针对采用液体推进剂火箭发动机的空间推进系统，推导了系统液路和气路的通用积分形式方程。
The general integral equations are derived for liquid and gas components of space propulsion systems with liquid propellant rocket engine.
研究了常温推进剂液体火箭发动机充填过程的建模问题。
The modeling of priming process of Liquid Propellant Rocket Engines (LPRE) was studied.
研究了低温推进剂液体火箭发动机供应管道系统充填过程的建模问题。
The priming process of feed lines of cryogenic propellant liquid rocket engines was studied.
为了分析液体推进剂火箭发动机燃烧室中存在的非稳态环境，必须很好地了解稳态状态。
To appreciate the unsteady environment existing in liquid propellant rocket chambers it is necessary that the steady state be well understood.
第一个使用液氧碳氢推进剂的国产液体燃料火箭发动机被安装在了火箭的E段上，它可以提供5.6吨的推力。
The first native liquid-fueled rocket engine used a liquid oxygen and carbon-hydrogen propellant, provided 5.6 tons of thrust, and was installed in unit e.
以液氧加注控制系统为例，介绍液体运载火箭低温推进剂加注控制所采用的两级分布式系统。
The two level distributed control system for cryogenic propellant loading is introduced, taking the Lox loading control system for example.
而印度的极卫星运载火箭（PSLV）只能使用固体和液体推进剂，载荷能力也小于两吨。
The Polar Satellite Launch Vehicle (PSLV) uses only solid and liquid propellants and is capable of carrying payloads less than 2 tonnes.
利用液体火箭发动机作动力装置的火箭，又称液体推进剂火箭。
Steady state fault detection and diagnosis of liquid propellant rocket engines based on decision tree method;
利用液体火箭发动机作动力装置的火箭，又称液体推进剂火箭。
Steady state fault detection and diagnosis of liquid propellant rocket engines based on decision tree method;
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