The company's decision to rely exclusively on solid-propellant engines for landing of a capsule with six cosmonauts onboard attracted particular criticism.
这家公司为了搭载有6名宇航员的航天舱的着陆而单独依靠固体推进剂发动机的决定，引发了严厉的批评。
A variety of mechanical surfaces have been employed for deflecting the exhaust jets of solid-propellant rockets.
人们已经用过各种类型的机械控制面来偏转固体推进剂火箭的排气流。
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。
Solid rocket propellant is a kind of high filled granular composite with viscoelastic behavior so that the experimental researches on its fracture are very difficult.
固体火箭推进剂是一种粘弹性高聚物，同时又是颗粒基复合材料。其断裂实验难度较大。
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。
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。
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。
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。
This thesis is focused on the hydrosilylation of ferrocenylsilanes, expecting to solve the problem of migration of ferrocene derivatives as combustion catalyst in solid propellant.
本文以研究二茂铁硅烷的硅氢化反应作为重点，以期通过硅氢化反应来解决二茂铁衍生物作为燃速催化剂在固体推进剂中的迁移问题。
This paper expatiates upon the principle and application of Acoustic Emission (AE), and it is known that AE technique is applicable to HTPB composite solid propellant dynamic damage process.
阐述了声发射(AE)原理及应用，指出AE技术适用于研究HTPB复合固体推进剂动态损伤过程。
The liner is a polymeric elastomer coating between propellant and insulation layer or case. The liner-forming is a special step in production of solid rocket motor.
衬层是推进剂与绝热层或壳体之间的高分子弹性体涂层，衬层成型是固体火箭发动机生产中的一种特种工序。
Solid propellant engine systems are basically less flexible in operation than liquid or hybrid propellant systems.
固体推进剂发动机系统的可调性基本上比液体或混合型的要差。
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 method to measure the burning rate coefficient and pressure index of a solid propellant with only one strand is discussed and analyzed, and the measured and processed results are given.
分析讨论了用一根药条测量固体推进剂燃速系数和压力指数的方法，并给出了测量和处理结果。
The paper gives the performance characteristic of a new type modified double base solid propellant, and it is compared with the traditional double base propellant.
论文研究了一种新型改性双基固体推进剂的性能特点，并与传统的双基推进剂进行了比较。
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。
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 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 results showed that the main influencing factor to the interior ballistics of solid motor with high energy propellant is the slow descending of burning rate.
结果表明，燃速缓慢下降是影响高能推进剂发动机内弹道性能变化的主要因素。
A new high energetic bonder intermediate azidodeoxycellulose for solid propellant was synthesized from the raw material cotton linters under homogeneous conditions.
以棉纤维为原料，在均相反应状态下合成了一种新型推进剂用含能黏合剂—叠氮纤维素。
The status and tendency of attitude control motors for satellites is briefly described. A new concept solid propellant controllable motor for attitude control based on photochemistry is recommended.
简要介绍了目前卫星姿控发动机的应用现状及发展趋势，提出了一种以光化学分解为基础的工作过程可控的固体姿控发动机新概念。
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。
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。
As mentioned above, three parameter VFD model can characterize the viscoelasticity of solid propellant. Applied it to SRM dynamic analysis, time and frequency domain response can be calculated.
综上所述，三参数VFD模型能够很好的反映推进剂的粘弹特性，将它用于固体发动机动力学分析，可以得到药柱在时域和频域内的动态响应。
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。
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。
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