测量与理论分析了复合推进剂的黏性与力学性能。
Composite propellant viscosity and mechanical properties were measured and analyzed theoretically.
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.
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。
The 300mm diameter solid propellant rocket motor employs a composite propellant end burning grain.
通过常温湿度试验，研究了HTPB复合推进剂力学性能随试验时间的变化规律。
The change rule of mechanical property of HTPB composite propellant with test time was studied by humidity test.
结果表明，这种方法可以有效地改善硝酸铵的晶体结构和吸湿特性，为硝酸铵在复合推进剂中的应用提供了实验和理论依据。
The results show that modification technology can effectively improve an's crystal structure and hygroscopicity, the experimental and theoretical foundation are also provided for an used in the...
结果表明，在细观结构下，复合推进剂中的应力分布是不均匀的，推进剂一般首先在极区产生脱粘，颗粒的大小对推进剂的力学性能有较大影响。
The results show that the stresses are inhomogeneous in the composite propellant and debonding cracks are usually generated in the pole of propellant. The particle size has great effect on them…
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。
The homogeneity of certified reference material is studied by acoustic emission method for composite solid propellant burning rate.
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。
China has undertaken to research and develop composite solid propellant rocket motors since 1958.
重点指出固化剂和氧化剂的微胶囊化包覆、复合粒子的制备等对提高推进剂的性能有重要作用。
The important effects of microencapsulated coating of the curing agent and oxidizer and preparation of composite particles to improve the properties of solid propellants are also showed.
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。
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.
复合固体推进剂药浆是固体粒子含量很高的粘性流体。
Composite solid propellant slurry is a viscous fluid with high percentage of solid particles.
根据一个有效的非线性粘弹模型，导出复合固体推进剂微分形式本构方程和应变速率关系式。
Based on an effective nonlinear viscoelastic model, the differential constitutive equation and strain-rate equation of solid composite propellants are induced.
两种相分离可以同时发生，但其对复合固体推进剂性能的影响不同。
The phase separation between the binder and plasticizer may seriously decrease the properties of the propellants.
针对火箭推进剂作业的特点，研制了一种以复合氟橡胶为主体材料的防护手套，可用于红烟硝酸作业人员的皮肤防护。
According to the trait of rocket propellant a kind of protective gloves made of composite fluorine rubber is developed which can be used to protect the skin of red fuming nitric acid worker.
结论利用生物激波管冲击和染毒柜染毒相结合的形式可以模拟复制现场液体火箭推进剂爆炸致冲毒复合伤的动物模型。
It was stable, economical, practical and easy to repeat. Conclusions Injury caused by the explosion of liquid propellant can be simulated by using the blast wave tube and the intoxication tank.
研究了AP／HTPB复合固体推进剂热分解性能对贮存老化期间增长断裂能初始变化率的影响。
The effect of AP/HTPB Composite propellant thermal decomposition characteristics on initial change rate of fracture property during aging has been studied in this paper.
相对于纯硼粉的推进剂，硼复合粒子的推进剂的表观分解热最高提高了12.6%。
In comparison with propellant with pure boron powder, the apparent decomposition heat of propellant with boron composition increases 12.6%.
目的复制冲击波和液体火箭推进剂中毒致冲毒复合伤的动物模型。
Objective To establish model of the blast-toxicosis combined injury caused by the explosion of the liquid propellant.
研究了HMX含量对HTPB复合固体推进剂微波衰减的影响。
The effect of the HMX content on the microwave attenuation of HTPB propellant has been studied.
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。
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.
采用靶线法对推进剂的燃速和压力指数分别进行了测定和计算，根据燃速和压力指数的变化，最终考察各种复合粉末对推进剂燃烧性能的催化作用。
The burning rate was measured with target line method and the pressure index was calculated. The catalytic effect of different catalysts for propellant on combustion performance were explored.
采用靶线法对推进剂的燃速和压力指数分别进行了测定和计算，根据燃速和压力指数的变化，最终考察各种复合粉末对推进剂燃烧性能的催化作用。
The burning rate was measured with target line method and the pressure index was calculated. The catalytic effect of different catalysts for propellant on combustion performance were explored.
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