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推进剂
propellant
Study on Primary Combustion of Boron-based Fuel-rich Propellant 含硼富燃推进剂一次燃烧研究 短句来源 A REVIEW CONCERNED TO RESEARCH AND APPLICATION OF HTPB PROPELLANT 丁羟推进剂的应用与性能研究评述 短句来源 Microwave Attenuation of the Exhaust Plume for Double-Base Propellant Rockets 双基推进剂火箭排气羽流的微波衰减 短句来源 PISA in Application to Improving the Properties of Polybutadiene System Propellant PISA在聚丁二烯系固体推进剂中的应用 短句来源 COMPOSITE SOLID PROPELLANT TOWARD HIGH ENERGY 复合固体推进剂的高能化 短句来源 更多 propellants
Researches on Combustion and Processes of High Boron Content Boron-Based Fuel-Rich Solid Propellants 高含硼富燃固体推进剂工艺和燃烧性能研究 短句来源 The Flame Temperature Distribution Measurement of Solid Propellants 固体推进剂火焰温度分布测量 短句来源 A STUDY OF EFFECTS OF STORAGE TEMPERATURE ON AGEING CHARACTERISTICS OF HTPB PROPELLANTS 贮存温度对丁羟推进剂老化性能影响的研究 短句来源 BLACK POWDER AND MODERN CHEMICAL PROPELLANTS 黑火药与现代化学推进剂 短句来源 PROPELLANTS FOR GAS GENERATORS 燃气发生器推进剂 短句来源 更多 propellent
Study of the Smokeless Propellent with Small Microwave Attenuation 对微波衰减小的无烟推进剂的研究 短句来源 A Review of Ap Composite Solid Propellent Steady Combustion Models Ap复合固体推进剂稳态燃烧模型综述 短句来源 MICROMECHANICS ANALYSIS ON THE VISCOELASTICS CONSTITUTIVE LAW OF COMPOSITE SOILD PROPELLENT (Ⅰ)REINFORCEMENT EFFECT OF BALL PARTICULATES 复合推进剂线粘弹本构方程的细观力学分析(Ⅰ)球形颗粒增强效应分析 短句来源 Micromechanics analysis on the viscoelastics constitutive law of composite solid propellent (Ⅱ)reinforce effects of non spherical particles 复合推进剂线粘弹本构方程的细观力学分析(Ⅱ)非球颗粒增强效应分析 短句来源 Study on micro-cracking damage constitutive model of HTPB composite solid propellent 复合推进剂微裂纹损伤本构模型研究 短句来源 更多 rocket propellant
THEORETICAL AND EXPERIMENTAL STUDIES FOR LIQUID ROCKET PROPELLANT EXPLOSION 液体推进剂爆炸理论与实验研究 短句来源 The Quantitative Safety Analysis of Conventional Liquid Rocket Propellant Operation 常规液体推进剂作业安全性研究 短句来源 Application of Electrochemical Gas Sensor on Detection of Liquid Rocket Propellant 控制电位电解型气体传感器在液体推进剂检测中的应用 短句来源 Based on CT experimental results of HTPB composite solid rocket propellant and under the assumption of single type of microcrack,the concentration degree and area of internal defects are quantitatively analyzed,the mathematic model and measurement method of damage are established. 本文通过HTPB复合固体推进剂断面层的计算机层析识别（Computerized Tomography 简称CT） 实验结果分析，并在微裂纹类型单一的假设条件下定量分析了材料内部微裂纹分布的密集程度和微裂纹面积的大小，建立了HTPB 复合固体推进剂损伤的CT 数学识别模型和方法。 短句来源 The Evaluation of HEDM Used as Solid Rocket Propellant (I): The Computational Investigation of Some Cyclic Nitramines HEDM作为固体推进剂组分的评价(Ⅰ):几种环状硝胺的计算研究 短句来源 更多 
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Analysis and operational results show that the control system can meet all technical requirements for high energy composite solid propellant manufacturing.
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Comprehensive Substantiation of the Structure and Parameters of a Power-Propellant System for a Spacecraft
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The conceptual and methodological principles, as well as some results of the comprehensive substantiation of a technical approach at early stages of design of power-propellant systems (PPS), are presented.
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The time of turn is minimized, as well as the functional having a meaning of the propellant consumption.
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The estimations of the propellant consumption for a realization of the programmed turn are made.
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An experimental method for determination of critical conditions of condensation of metal propellants of electric jet engines (EJEs) on the surfaces of materials of spacecraft thermoregulating covers is presented.
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Mechanism of combustion of fire-extinguishing propellants based on potassium nitrate
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A study is made of one-dimensional nonstationary problems of the combustion and detonation of aerosuspensions of unitary fuels or propellants, which contain the oxidant as well as the combustible material (gunpowder, high explosives).
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The temperature of attainable superheating of rocket propellants is also calculated by the theory of homogeneous nucleation.
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It is demonstrated that the employed kinetic model of thermochemical processes provides an adequate description of the available experimental data on the rate of combustion of AP- and PBR-based solid propellants.
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It is verified that the constitutive model with damage proposed can more accurately estimate the stress response of a class of viscoelastic particle-reinforced composite, such as solid propellent, than the constitutive model without damage.
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The rheological behaviour of plastic propellent in rocket motor situations is simulated in an experimental technique.
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In this a differential gas pressure is applied across a plug of propellent in a rigid tube so as to deform it in an approximately telescopic shear fashion.
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The rheological properties of plastic propellent have been examined by means of a technique in which gas pressures are used to stress a plug of propellent pressed into a rigid tube.
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The application of these superposed results to predict propellent behaviour is discussed.
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The detection of defects and the characterization of solid rocket propellant were thus possible.
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We have considered the electrodynamic effects on small Al2O3 spherules dumped into the Earth's magnetosphere in large quantities during solid rocket propellant burns.
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TG studies of a composite solid rocket propellant based on HTPB-binder
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The reasons for substantially nonstationary modes of operation of this system are considered, and a simplified model that approximates the phenomena of nonstationary combustion of a solid rocket propellant is proposed.
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The paper presents estimates of the dynamic characteristics of unsteady combustion of a solid rocket propellant in a combustion chamber with in pressure is varied automatically by a specified program.
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