Russian sources said that much more experimental work and funding would be required to prove that solid propellant could be safely used for a manned landing.
俄罗斯的消息人士称，这将需要更多的试验工作以及资金来证明固体推进剂可以被安全地用于载人着陆。
China has undertaken to research and develop composite solid propellant rocket motors since 1958.
中国从1958年开始复合固体推进剂火箭发动机的探索和研制工作。
Among those methods to improve the burning rate of solid propellant, the nanometer-sized catalyst has been considered as one kind of most prospective methods.
在提高固体推进剂燃速的众多方法中，采用纳米催化剂被认为是最有前途的方法之一。
The solid propellant booster weighs an additional 210kg.
附加的固体火箭助推器重量210千克。
A conception of adjustable solid propellant rocket motor was proposed.
本文提出了一种推力可调的固体火箭发动机的设想方案。
A new method of the solid propellant rocket nozzle design is presented.
本文介绍一种设计固体火箭喷管的新方法。
Composite solid propellant slurry is a viscous fluid with high percentage of solid particles.
复合固体推进剂药浆是固体粒子含量很高的粘性流体。
Fitting of relaxation modulus master curve for solid propellant and W. L. F. equation parameters.
推进剂松弛模量主曲线及W.L.F。方程参数的拟合处理。
The 300mm diameter solid propellant rocket motor employs a composite propellant end burning grain.
直径300毫米的固体推进剂火箭发动机采用了复合推进剂端燃药柱。
Stress analysis of solid propellant motor when temperature varies in storage is presented in this paper.
分析了固体火箭发动机药柱在长期贮存过程中，由于温度载荷谱的变化所引起的力学响应。
Nanometer metal powders also have catalytic effects on the thermal decomposition of AP/HTPB solid propellant.
纳米金属粉对AP/HTPB推进剂的热分解同样具有一定的催化效果。
A laser method was used for measuring transient burning rate delay of solid propellant in oscillatory combustion.
应用激光方法测量压力振荡过程中的固体推进剂瞬态燃速。
This paper discusses operating principles and technology challenges of the integral solid propellant rocket ramjet.
研讨了整体式固体冲压火箭发动机的工作原理及技术难点；
The ablation mechanism and the performance of carbon-phenolic material of solid propellant rocket nozzles are studied.
本文研究了碳-酚醛材料在固体火箭发动机喷管中的烧蚀机理及性能。
A theoretical model describing the process of the crack combustion and propagation in solid propellant was formulated.
建立了描述固体推进剂裂纹燃烧与扩展过程的数学模型。
Overload acceleration is one of those important factors which influence the performance of solid propellant rocket motor.
过载加速度是影响固体火箭发动机性能的重要因素之一。
The one dimensional two phase flow model of solid propellant electrothermal chemical gun (SPETCG) is established in the paper.
该文建立了固体工质电热化学炮(SPETCG)内弹道一维两相流模型。
In this paper, one-dimensional two-phase constant lag flow in combustion chamber of solid propellant rocket motors is described.
本文论述了固体火箭发动机燃烧室一维两相常滞后流动。
The primary combustion of deficient oxygen solid propellant is non equilibrium because of its own physical and chemical processes.
贫氧推进剂一次燃烧的物理和化学动力学因素决定了其一次燃烧为非平衡燃烧。
The homogeneity of certified reference material is studied by acoustic emission method for composite solid propellant burning rate.
采用声发射燃速测试方法研究了复合固体推进剂方坯燃速的均匀性。
Interface bond quality of solid propellant rocket motor can be tested by Lamb waves, but the modes of Lamb waves need to be selected.
用兰姆波可对固体火箭发动机进行胶接质量的检测，但需要对其模式进行选择。
The fuzzy mathematic model for synthesis sensitivity evaluation of solid propellant was established by means of fuzzy mathematic method.
利用模糊数学方法，建立了固体推进剂综合感度评价的模糊数学模型，并用于NEPE推进剂的综合感度评价。
The broad-band USED CARS measurements of temperature and N2 concentration in the combustion of solid propellant at atmospheric pressure are reported.
报道了采用单次脉冲非稳腔空间增强探测相干反斯托克斯喇曼散射（USEDCARS）技术诊断常压下固体燃剂瞬态燃烧场温度和氮气浓度。
According to the entire design requirements and restraints of a certain solid propellant rocket motor, design method of nozzle contour is put forward.
根据某型号固体火箭发动机总体设计要求及限制条件，给出了喷管型面设计方法。
Based on modified Arrhenius formula, an integral method and a two-step regression method for storage life prediction of solid propellant are presented.
在修正的阿伦尼斯公式基础上，提出固体推进剂贮存寿命的整体预测方法和两步回归预测方法。
It is considered that solid propellant with nanometer metal oxide catalysts has the better combustion properties compared with non-nanometer catalysts.
认为固体推进剂用纳米金属氧化物作催化剂，可获得优于非纳米催化剂的燃烧性能。
The plume temperature is an important parameter, for solid propellant rocket engines and it is useful for determining the combustion process of the engine.
推进剂的羽焰温度是固体推进剂火箭发动机的重要参数，对于研究发动机内的燃烧过程具有重要价值。
The plume temperature is an important parameter, for solid propellant rocket engines and it is useful for determining the combustion process of the engine.
推进剂的羽焰温度是固体推进剂火箭发动机的重要参数，对于研究发动机内的燃烧过程具有重要价值。
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