specific impulse

Rocket based combined cycle is a combination of the advantages of the rocket engine and intake engine, which features high thrust to weight ratio and high specific impulse and realizes the optimality of performances in the whole ballistic trajectory.

火箭基组合循环综合了火箭发动机和吸气式发动机的优点，具有高推重比、高比冲的特点，实现了整个弹道上性能的最优化。

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Synthetic method and stabilization of alpha-AlH_3 are reviewed. Introducing AlH_3 instead of aluminum powder in solid propellant. Theoretical specific impulse can be enhanced above 100N · s/ kg.

综述了三氢化铝晶体形态特征、α-AlH3的分子结构、合成方法及稳定化途径，在固体推进剂中用三氢化铝代替铝粉可使推进剂理论比冲可以增加100N·s/kg以上。

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The main performance parameters of a fixed geometry scramjet are observed, and the effective thrust coefficient, effective specific impulse and effective specific thrust are determined.

探讨了固定几何尺寸（不可调）的超燃冲压发动机有效推力系数、有效比冲和有效单位推力等主要性能参数变化的定量范围。

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A Hall thruster, with its high-efficiency and high specific impulse, is one of the most important electric propulsion devices widely used for spacecraft propulsion such as attitude control, orbital transfer and deep space exploration missions in the future.

霍尔推力器作为一种等离子体装置，以其高效率高比冲等特点成为国际电推进领域的研究热点，广泛应用在姿态控制，轨道转移及将来的深空探测任务。

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Arcjet is one of the highlight of electric propulsion investigation and application because of its high thrust density, high ratio of thrust and power, preferable specific impulse, better system successiveness and reliability.

作为电推进的一种方式，电弧加热发动机以较高的推力/功率比、推力密度、中高的比冲、良好的系统继承性和可靠性等特点，成为当前国际研究和应用的热点。

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Rotating acceleration has inevitable influence on the work process of Solid Rocket Motor: flow of combustion chamber and nozzle is changed; the pressure, mass flow rate and the specific impulse of Solid Rocket Motor are affected by the spinning.

旋转产生的加速度必然对固体火箭发动机的工作过程产生影响：使燃烧室和喷管中的燃气流动发生变化，对燃烧室工作压力质量流率及冲量产生影响。

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Theoretical specific impulse for two-phase flow in nozzle of rocket-ramjet engine& a simple estimation method

火箭冲压发动机喷管的两相流动理论比冲&一种简单估算方法

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The effect of operation pressure on the specific impulse of tactical missile solid motors is analyzed from several factors, such as characteristic velocity, thrust coefficient, impulse coefficients of the chamber and nozzle.

从固体发动机的特征速度、推力系数、燃烧室冲量系数和喷管冲量系数等因素出发，分析了发动机工作压强对战术固体火箭发动机比冲的影响。

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Curves of constant specific impulse are traced inside the triangle.

比冲为常数的曲线则画在三角形内部.

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In addition, it showed that thermal throat will increase engine thrust and decrease specific impulse.

另外还得到热力喉道取代几何喉道后对发动机性能的影响，它可以提高发动机的推力，却要降低比冲。

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Theoretical research on specific impulse performance and chamber length of hydroreactive metal fuel motor;

水反应金属燃料发动机系统构型研究需要以燃烧数值模拟作为研究基础。

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Calculation of the Specific Impulse Loss for Radiative Cooling Thrust Chamber

辐射冷却推力室的比冲损失计算

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It is a reliable measuring method of the specific impulse for the high-burning rate propellants.

为高燃速推进剂比冲测试提供了可靠的试验依据.

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Energic level of NEPE solid propellant was analyzed, the effect regularity of ingredients different ratio and content on the propellant formulas standard theoretical specific impulse ( ISS) was studied.

借助电子计算机计算与分析了NEPE固体推进剂的能量水平，研究和比较了组分的含量与不同配比对推进剂配方标准理论比冲I（ss）~°值的规律性影响。

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This paper analyzes the effects of burning rate catalysts on the theoretical specific impulse ( ISS) and the pressure exponents of NEPE high energy solid propellants.

分析了燃速催化剂对NEPE高能固体推进剂理论比冲和燃速压强指数的影响。

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Hydrogen peroxide/ azido-amine combination is hypergolic bipropellant with high density specific impulse.

过氧化氢/叠氮胺类不但密度比冲高，而且可实现自燃；

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The theoretical specific impulse formula for two-phase flow in nozzle of rocket-ramjet engine is derived on the basis of similarity to that used for rocket engine.

本文导出了类似于火箭发动机的火箭冲压发动机喷管的两相流动理论比冲公式；

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High speed, high specific impulse, long range, high maneuver, simple structure are ideal objects, which designers of missile propulsion aspire after for ever.

高速度、高比冲、远射程、高机动性、简单结构和低成本一直是导弹动力装置设计者孜孜以求的目标。

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The specific impulse of helium ( He) propellants is higher than that of Argon ( Ar).

氦气（He）的比冲远高于氩气（Ar）的比冲。

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And thrust deviation is less than 0.4%, the specific impulse deviation is less than 0.35%.

计算表明，理论预示推力与测试推力基本一致，平均推力偏差不大于0.4%，平均比冲偏差不大于0.35%。

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Research on the High Specific Impulse Bipropellant Liquid Apogee Engine

高比冲双组元液体远地点火箭发动机研究

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Smokeless propellants with HCO all show to give higher specific impulse ( theoretical) than those with HMX.

以HCO取代HMX作为无烟推进剂的高能添加剂，其理论比冲都高于HMX无烟推进剂。

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