查询词典 propellant

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。

A type of high-performance fuel-rich propellant for the unchoked ducted rocket has been developed. The burning rates of the fuel-rich propellant are greater then 2mm/s at 0.5MPa, the greatest one is up to 4. 05mm/s. The burning-rate exponent is greater than 0.5, the highest one reaches 0.58. The fuel-rich propellant grain can combust steadily in the gas generator at 0.226MPa. The uniaxial mechanical properties and the processability of the fuel-rich propellant are good.

研制了一类用于非壅塞固体火箭冲压发动机的高性能铝镁贫氧推进剂：0.5MPa下燃速高于2mm/s，最高者达4.05mm/s；燃速压强指数高于0.5，最高者达0.58；直连式实验时，在0.226MPa下燃烧稳定；具有良好的力学性能和工艺性能。

This paper, the experimental research on contribution of Al and RDX and high nitrogen content nitrocotton to a screw CMDB propellant, is carried out, a proper content about Al, RDX is selected in this propellant, and a problem of the propellant mechanical properties which use high nitrogen content nitrocotten is solved.

研究了Al粉、RDX及高氮量硝棉对螺压高能改性双基推进能量的贡献，配方选择了比较合适的Al粉、RDX含量，解决了采用高氮量硝棉的推进剂的力学性能问题。

In this paper migration theory and techniques related to the high-energy TEGN gun propellant are presented, and some methods determining the migration of RDX are analyzed and compared. As a result, chemical and thermal analyses are employed associatively to test the content of RDX in different position of TEGN gun propellant stored different period. The antimigration capability of TEGN gun propellant making use of two different granularity of RDX is also been studied.

本文以高能太根发射药及其相关技术为研究对象，分析研究了迁移理论以及目前国内外测定RDX迁移性能的方法，对这些方法的优缺点进行了比较，并采用化学分析法、热失重法、差式扫描量热法相结合的方法对各种不同储存时期高能太根发射药不同部位中RDX含量进行了测定，研究了使用两种不同粒度RDX制备的太根发射药的抗迁移性能。

The results show that the value of burning rate pressure exponent of propellant and its change law can bring about a great change of interior ballistic behavior, The new type high-energy propellant whose burning rate pressure exponent is decrescent as pressure increasing can obtain higher interior ballistic piezometric efficiency, and reduce the sensitivity of bore pressure and muzzle velocity on loaded conditions of propellant.

结果表明，发射药燃速压力指数的大小及其随压力的变化规律对内弹道性能有很大的影响，对于燃速压力指数随压力升高而减小的新型高能发射药，可获得较高的内弹道示压效率，降低膛压和弹丸初速对发射药装填条件的敏感性。

A new high energy deterred single base gun propellant was prepared by using high nitrogen content single base multiperforated gun propellant containing process solvent as main material,and HEDS propellant was produced by two steps,first absorbing nitroglycerine and second absorbing polymeric deterrent in water.

以高氮量单基发射药为原料，使用先吸收NG、后吸收聚酯钝感剂的两步法工艺，成功制备出高能钝感单基药。

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]。

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。

Results show that the propellant with α-HMX is easy to be ignited and its gas generation brisance and combustion rate is lower than that with β-HMX, and the burning rate pressure exponent of the propellant with α-HMX is 0.1 higher than that with β-HMX and mechanical properties of the propellant with α-HMX is worse.

结果表明：含α-HMX发射药点火容易，其气体生成猛度和燃烧速度比含β-HMX发射药的小，含α-HMX比含β-HMX发射药的燃速压力指数高0.1、力学性能差。

The review deals with the effects of solid propellant during production and application on the environments and the antipollution techniques by careful selection of propellant ingredients or development of clean propellants.

综述了固体推进剂及火箭发动机在生产和使用过程中产生的污染以及改进措施。

The role of the environment is very important.

的作用，环境是非常重要的。

At that time, the High Court of England and Wales Court of Queen's Bench president of William Murray, Lord Mansfield in June 22, 1772 ruling:"No matter then there is the inconvenience, but there must be a decision, I can not say that this case under the law in England are permitted or authorized; are so black should be released."

当时的英格兰及威尔士高等法院王座法庭院长William Murray， Lord Mansfield于1772年6月22日宣判：「无论有那麽不便，但总要有个决定，我不能说这件案在英格兰法律之下是准许或认可；所以黑人是应该被释放。