推进剂

基本解释 (translations)

propellants  ·  propellent  ·  propulsor  ·  propulser

词组短语

propulsive agent

与推进剂相关的网络例句 [注：此内容来源于网络，仅供参考]

Because of the fuel-rich propellant's high heat value and combustion temperature, the common stainless steel crucible and oxygen bomb's parts are always burned in the combustion heat testing process. In order to realize the proper testing of combustion heat, some fireproof materials characteristics and their application in the combustion heat testing of fuel-rich propellant were studied. Those fireproof materials include acid washing asbestos, C/C compound materials, Al2O3 chinaware and tungsten crucible.

含金属富燃料推进剂由于热值高、燃温高，在燃烧热测试过程中普通的不锈钢坩埚及附件经常被烧毁，为了正确测试金属富燃料推进剂燃烧热，对酸洗石棉、碳／碳复合材料、Al2O3陶瓷坩埚和金属钨坩埚的基本耐烧蚀特性和在金属富燃料推进剂燃烧热测试中的应用进行了实验研究。

Studied present measuring methods" advantages and disadvantages, and presented the necessity and importance of researching propellant transient heat transfer.2.according to 130 and aeronautic 90 rocket projectiles" structure, analysed and acquired physical and mathematical models for propellant transient heat transfer, also designed propellant temperature field simulation units for test.3.acquired discrete transient heat balance equation and temperature calculation program, and gave contrasting curves between experimental temperature values and program calculating temperature values as well as maximum errors and average square root errors between them.4.by programs based on the first class boundary condition, worked out temperature distribution in propellant temperature field simulation units at different time, analysed temperature field distribution law and main elements affecting heat transfer, acquired propellant mass weighted average temperature and one at the half position of propellant maximum thickness as well as maximum errors and average square root errors between them.5.established transient heat transfer mathematical model and temperature calculation program for the third class boundary condition, drew contrasting curves between temperature experimental values and calculation values and gave maximum errors and average square root errors between them, got temperature distribution in the simulation unit at different time and main elements affecting heat conduction, figured out propellant mass weighted average temperature and one at the half position of propellant maximum thickness as well as maximum errors and average square root errors between them.

分析了现有测试方法的优缺点，提出了研究推进剂瞬态导热的必要性和重要性。 2。根据130和航90两种火箭弹的结构，分析得到了推进剂传热的物理模型和数学模型，设计了推进剂温度场模拟实验装置。 3。得到了离散形式的瞬态热平衡方程和温度场计算程序，给出了实验温度与程序计算温度值的对比曲线及其最大偏差与均方差。 4。利用程序求出了第一类边界条件下、不同时刻推进剂温度场模拟装置中的温度分布，分析了温度场的分布规律和影响传热的主要因素，求出了推进剂质量加权平均温度和最大肉厚1／2处的温度时间曲线并给出了两者之间的最大偏差与均方差。 5。建立了第三类边界条件下的瞬态导热数学模型和温度计算程序，求出了温度实测值与计算值的对比曲线并给出了两者之间的最大偏差与均方差，得到了不同时刻温度场模拟装置的温度分布与影响导热的主要因素，求出了推进剂质量加权平均温度和最大肉厚1／2处温度及两者之间的最大偏差与均方差，讨论并确定了能代表130和航90推进剂温度的特征点的位置。

The safety detection methods of the rocked propellent in the launch ing field were also discussed.

并讨论了卫星发射场推进剂安全监测方法，液体推进剂的3级卫生防护措施，液体推进剂中肼类推进剂的急性、亚急性、慢性毒性及对中枢神经、血液、循环、消化、呼吸是否、免疫、肝脏、肾脏、皮肤、眼等器官系统的毒理学和遗传毒理学。

Because the nitramine explosive has high mechanical sensitivity and shock wave sensitivity,the attention is given to the security of modern high energy propellant.In order to evaluate the security of NEPE high energy propellant,it's necessary to study and calculate the TNT equivalence of high energy propellant.

1引言硝酸酯增塑的聚醚高能固体推进剂是二十世纪70年代发展起来的新型固体推进剂，它突破了传统的复合和双基推进剂的界限，综合它们各自的优点于一身，是目前已服役的能量最高的推进剂[1]。

On the basis of composite solid propellants combustion model, we have modifiedthe surface structure factor of nitroamine propellants and a new function have be used tomodified the decomposition products of nitroamine according to predecessors researchfindings in combustion mechanism of nitroamine propellants, these work make originalmodel is indicated for a wide range of pressure and particle size.

2在原有的复合推进剂燃烧模型基础上，根据前人在硝胺推进剂及燃烧机理方面研究成果对硝胺推进剂表面结构因子f_进行修正，并引入ξ函数对硝胺的分解产物中的氧化性气体含量进行修正，使原有的燃速预估模型能适用于更宽的粒度及压力范围。

And some applications of DNTF in the explosive composition, CMDB and related item are also revie

同时，对DNTF在高能混合炸药、改性双基推进剂等方面的应用研究进行了综述，从能量性能，安定性和安全性能上分析了其在改性双基推进剂中应用的可行性，并指出了目前DNTF-CMDB推进剂存在的问题。

Firstly, the principle and method of designing the combustion characteristics ofsmall grain-binding high-burning-rate propellant are analyzed and discussed, theburning behaviors and energy characteristic of the component content and binder andsmall grain propellant are respectively calculated by the estimating burning rateprocedure based on the chemical structure and characteristic of propellant, and theREALthermodynamics system software. The selection principle of component contentwhen designing the burning behavior and energy characteristic is analyzed.

首先，分析讨论了小球粘结高燃速推进剂燃烧性能设计原理及方法，采用基于推进剂化学结构与特征反应关系的燃速预估程序和REAL热力学系统软件分别计算了组分含量与黏结剂和小球药燃烧性能、能量性能的关系，分析了推进剂燃烧性能、能量性能设计时组分含量的选择原则。

Based on the prediction model for uncatalytic double base propellant burning rate the dissertation, carrys on the mathematical treatment to the hypothesis of polyemerization and disintegration, deduces the formula of catalytic double base propellant burning rate and pressure exponent; The results of experimental tests show that it can re-present quantitatively various stage of plateau combustion: super rate, plateau and mesa. The calculated results conform with the experimental results very well.

在非催化双基推进剂燃速预估理论的基础上，对聚合裂解的假设进行数学处理，导出催化双基推进剂的燃速公式和燃速压力指数公式；实验验证结果表明，模型中的公式可以定量地再现双基平台推进剂燃烧中的超速，平台和麦撒现象，而且计算值和实测值符合得较好。

2 The measurement of temperature of solid propellant plume by remote sensing FTIR The infrared radiance spectra was obtained by remote sensing FTIR. The temperatures of four plumes of propellants and a infrared reagent were calculated according to the gas vibration rotation band fine structure such as CO, HF, H2O and HC1 in plume of solid rocket propellant. The results have a agreement with the theoretical data.

2.2 FTIR遥测固体推进剂羽流温度本文利用遥感FTIR测试技术测得了固体火箭推进剂羽流的红外辐射亮度分布图，并根据谱图中CO、HF、HZO、HCI四种气体振转谱带精细结构计算了推进剂羽流温度及红外辐射药剂的燃烧温度，计算结果与理论预测值基本一致。

Liquid propellants ; density specific impulse ; monopropellant ; bipropellant ; atomic propellant

液体推进剂；密度比冲；单组元推进剂；双组元推进剂；原子推进剂

与推进剂相关的网络解释 [注：此内容来源于网络，仅供参考]

liquid, propellant：液体推进剂

liquid phase 液相 | liquid propellant 液体推进剂 | liquid propellant rocket 液体推进剂火箭

liquid propellant rocket：液体推进剂火箭

liquid propellant 液体推进剂 | liquid propellant rocket 液体推进剂火箭 | liquid propellant rocket engine 液体火箭发动机

liquid propellant sustainer：液体推进剂主发动机

liquid propellant starter | 液体推进剂启动机 | liquid propellant sustainer | 液体推进剂主发动机 | liquid propellant unit | 液体火箭发动机

liquid propellant rocket engine：液体推进剂火箭发动机

liquid propellant rocket | 液体推进剂火箭 | liquid propellant rocket engine | 液体推进剂火箭发动机 | liquid propellant starter | 液体推进剂启动机

liquid missile propellant; liquid propellant：液态导弹推进剂

Guide for Countries Preparing National Biodiversity Strategies and Action Plans, draft;... | liquid missile propellant; liquid propellant;液态导弹推进剂; ; | Military Industrialization Corporation;军事...

propellant：推进剂

"除虫剂喷雾器"(insecticide fogger) 指经设计以在室内范围内以浓雾或淡雾形式在单"造型"(styling) 指塑造、形塑或调控头发以暂时改变发型;"推进剂"(propellant) 指为以下用途全部或部分使用的液化或压缩气体,

Propellant Supply：推进剂供应

22.Programming System 程序设计系统 | 23.Propellant Supply 推进剂供应 | 24.Proton Synchrotron 质子同步加速器

Propellant Supply：推进剂的输送

propellant structure 推进剂结构 | propellant supply 推进剂的输送 | propellant terminal 推进剂仓库

Propellant Supply：推进剂供给

Programming System 程序设计系统; | Propellant Supply 推进剂供给; | Proton Synchrotron 质子同步加速器;

liquid propellent rocket：液体推进剂火箭

液体推进剂 liquid propellant | 液体推进剂火箭 liquid propellent rocket | 受液器 liquid receiver