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。
Applications of integral solid propellant rocket ramjets arc researched.
研究了整体式固体火箭冲压发动机的应用性能。
Two minutes later, after consuming 1.4 million pounds of solid propellant, the rocket burned out.
经过两分钟，火箭烧尽140万磅固体推进剂后，最终熄灭了。
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。
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。
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。
Stress analysis of solid propellant motor when temperature varys 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。
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。
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。
The solid propellant is a high energy polymer filled with particles, which behavior of failure is evident different from metal.
固体推进剂是一种颗粒填充高能聚合物，其破坏时所表现出的一些行为和金属的破坏相比，有明显不同之处。
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。
To find out the performance characteristic of aerospike nozzle, the simulated tests were a aerospike engine unit using solid propellant.
为了了解塞式喷管性能，采用固体推进剂对塞式喷管单元发动机进行了模拟实验。
It will burn a mixture of solid propellant (HTPB, or hydroxyl-terminated polybutadiene) and liquid oxidiser (high-test peroxide, HTP) for 20 seconds.
它将点燃固体推进燃料(HTPB，或称羟基封端聚丁二烯)和液体氧化剂(高挥发性过氧化物，HTP)的混合物持续20秒。
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。
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。
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。
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。
As control force source, the solid propellant gas generator was used to exert lateral force for the end control and the turn of vertical launching of missiles.
利用固体燃气发生器作为控制力源对导弹进行侧向力控制、导弹的末端控制和垂直发射导弹的转弯具有重要的作用。
Based on the experimental study, volume creep compliance, volume relaxation modulus and their main curves and initial void content of solid propellant are given.
通过实验研究，给出了固体推进剂的体积蠕变柔量、体积松弛模量和材料的初始气孔率。
Based on the experimental study, volume creep compliance, volume relaxation modulus and their main curves and initial void content of solid propellant are given.
通过实验研究，给出了固体推进剂的体积蠕变柔量、体积松弛模量和材料的初始气孔率。
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