含硼富燃推进剂燃烧机理研究。
The combustion mechanism of boron-based fuel-rich propellant was studied.
本文提出了铅化合物催化双基推进剂燃烧的反应历程。
This paper has advanced the mechanism of reaction that lead compounds catalyze the combustion of double-base propellants.
本文介绍一种求解复合推进剂燃烧产物平衡成分的简化计算方法。
This paper gives a simplified calculation method which solves equilibrium composition of the combustion products of composite propellants.
研究了不同工艺对含ACP无烟改性双基推进剂燃烧性能的影响。
The effect of different technology including casting and extrution on the combustion performance of smokeless modified double-base propellant with ACP was studied.
结果表明，该模型能正确地预测许多因素对推进剂燃烧速率的影响。
It is shown that effects of many factors on combustion rate of propellant can be properly predicted by use of this model.
液体推进剂燃烧过程是相当复杂的，很难对其进行严谨的分析描述。
Liquid propellant combustion processes are quite complicated and defy precise analytical description.
综述了国内外对含硼贫氧推进剂燃烧特性及其改进技术的研究成果。
The characteristics of the boron based fuel rich propellant and its modification techniques are reviewed.
实验发现了双基推进剂燃烧表面上方高温反应中心的存在和变化规律。
The high temperature reaction centre above the burning surface of the double base propellants and its variety regulation are found.
残渣影响微粒尺寸测量，而推进剂燃烧特性将直接影响着微粒尺寸分布。
Soot affects the measurement results and the combustion characteristics also has a influence the particulate size distribution.
实验结果表明，这种化合物具有改善推进剂燃烧性能和力学性能的双重作用。
The results have shown that the compound can improve both propellant mechanical properties and combustion characteristics.
使用少量燃烧催化剂是调节火炸药，特别是固体推进剂燃烧性能的最佳途径。
Using less combustion catalyst is the best method that is used to adjust the combustion property of propellants and explosives, especially solid propellants. In this Ph.
运用几种表面分析方法研究了硝胺改性双基推进剂燃烧前后的表面物化结构。
Surface analysis methods were used to investigate the physical and chemical structure of the burning surface of RDX-CMDB propellant before and after combustion.
并测量了推进剂的爆热和燃速，比较了AP包覆硼粒子对推进剂燃烧性能的影响。
The difference of the burning peculiarity between propellants whose boron was coated with and without AP was compared by measuring the explosive heat and burning rate of the propellants.
建立了一个描述微孔推进剂燃烧的模型，并得到了推进剂稳定燃烧时的控制方程组。
The combustion model of micro-void propellant is presented in this paper. The control equations for stable burning of propellant are set up.
通过微热电偶测温和火焰单幅照相技术测试了含硼富燃料推进剂燃烧波温度分布及燃烧火焰结构；
The combustion wave temperature profiles and flame structures of fuel-rich propellant containing boron are measured by using W-Re micro-thermal couple and flame photo technique.
在固体推进剂bdp燃烧模型基础上，引入膏体推进剂燃烧热效应这一新参数将模型推广于膏体推进剂和固体推进剂药浆燃烧研究。
In this paper, a new parameter named slurry combustion effect was induced for applying solid propellant BDP model for prediction of pasty propellant and slurry propellant steady combustion behavior.
压力-时间痕量从kdx- 002静力试验的河童的DX火箭发动机将被用来估计推进剂燃烧率，与结果相比，钢绞线燃烧器的数据 。
The pressure-time trace from the KDX-002 static test of the Kappa-DX rocket motor will be used to estimate the propellant burn rate, with the results compared to Strand Burner data .
研究了过渡金属氧化物（TMO ）及其复配物对非壅塞固体火箭冲压发动机铝镁贫氧推进剂燃烧特性的影响。研究发现，氧化铁对提高铝镁贫氧推进剂燃速的作用显著。
The effects of TMOs and their mixtures on the burning rate and the pressure exponent of the aluminum magnesium fuel rich propellant for unchoked ducted rocket are investigated.
典型的任务：测试新的推进剂的燃烧率。
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.
推进剂的燃烧特性及喷管堵盖打开压强对点火升压过程有较大影响。
Propellant property and nozzle closure opening pressure have an important effect on the ignition transient.
降低硝酸铵的热分解温度，促进AN的热分解是解决硝酸铵推进剂点火和燃烧困难的途径之一。
One way to resolve ignition and combustion difficulties for AN-based propellant is to lower AN decomposition temperature, and to accelerate the thermal decomposition of AN.
膏体推进剂的点火和燃烧特性是发动机设计的重要参数。
The ignition and combustion characteristics of pasty propellant are important parameters for the motor design.
本文给出了用该程序对采用液氧、丙烷作为推进剂的分级燃烧循环进行计算的结果。
The stage combustion cycle using the liquid oxygen and methane as propellant is calculated with the program, and the calculation results are also given.
给出了推力室内从推进剂雾化、蒸发、燃烧到传热一整套合理的数学模型。
And a reasonable mathematic model about the spray, evaporation, combustion and heat transfer of the propellant in engine is given.
数值仿真模型中考虑了自燃推进剂雾化机理、高压分解燃烧和预混反应流湍流燃烧等。
The atomization mechanism of hypergolic rocket propellant and decomposition combustion at high pressure and turbulence burning of premixed reactant flow field are considered .
为了有效地进行燃烧，推进剂必须雾化。
For proper combustion it is necessary to atomize the propellants.
试车使用的推进剂具有易挥发、易爆炸、易燃烧等特点，使得试验过程具有很多不安全因素，危险性大。
During the test, so much volatile and burnable propellant is used that the process is dangerous and influenced by many factors.
利用先进的双钨铼微热电偶技术，研究了GAP／AN 推进剂的燃烧波温度分布。
Combustion wave temperature distribution of GAP/AN propellant was studied by means of advanced double W Re microthermocouple technique.
分析了在硝胺改性双基推进剂中炭黑对其燃烧性能的影响。
The effect of carbon black on burning properties of modified nitramine double base propellant was detailed in this paper.
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