propellant combustion的例句大全

nano-catalysts have been widely studied because of its significant catalytic effect on solid propellant combustion.

在固体推进剂的燃烧过程中，纳米催化剂可发挥良好的燃烧速度改善和燃烧稳定性提高的作用，因而被广泛研究和应用。

互联网摘选

A Study of Pressure Wave in Long Closed Bomb by Propellant Combustion

火药在长密闭管中燃烧的压力波研究

互联网摘选

The combustion gasbag projector structure is one of firing ways with extensive application foreground for shrapnel, it involves that the processes of propellant combustion, gasbag charge, and pullet dispersion.

子母弹燃气囊子弹抛撒系统是一种具有广泛应用前景的抛撒技术，它包括了抛撒药燃烧、燃气囊充气和各子弹运动的变化过程。

互联网摘选

A Study on Catalysis Mechanism of PNTO in GAP Propellant Combustion

PNTO在GAP推进剂燃烧中的催化特性

互联网摘选

Combustion Research on Superfine Aluminium Powder In Ap/ HTPB Propellant

超细铝粉在Ap/HTPB推进剂中的燃烧研究

互联网摘选

This paper presents the development of the liquid propellant rocket engine technology from the viewpoint of combustion chamber pressure, thrust level and power cycle.

本文从燃烧室压力、系统工作循环方式以及最大推力三个方面叙述了世界各国液体火箭发动机的技术水平。

互联网摘选

Temperature distribution of combustion flame of double base propellant, composite propellant and NEPE propellant ( taking HNIW or HMX as oxidizer) were measured by using relative light intensity method.

采用相对光强度法测定了双基推进剂、复合推进剂及NEPE（氧化剂为HNIW或HMX）推进剂的燃烧火焰温度分布。

互联网摘选

An experimental study on the ignition and combustion characteristics of pasty propellant

膏体推进剂点火和燃烧特性的实验研究

互联网摘选

The combustion rate of propellant at any pressure can be obtained by one test of closed burner method, and closed burner method will be an effective tool to study new style propellant working under high pressure.

密闭燃烧器法一次测试可测出全部压强下推进剂燃速，可成为高压高燃推进剂研制的有效工具。

互联网摘选

Effect of structure pattern of pasty propellant ramjet motors on combustion efficiency

膏体冲压发动机构型对燃烧效率的影响研究

互联网摘选

Numerical Simulation and Experimental Study of Pasty Propellant and Solid Propellant Slurry Steady Combustion Behavior

膏体推进剂和固体推进剂药浆稳态燃烧研究

互联网摘选

A Study of Combustion Laws of Propellant's External Coating Layer

火药包覆层外层燃烧规律的研究

互联网摘选

The effect of initial propellant temperature on rocket engine combustion stability for hypergolic propellant ( MMH/ NTO) is studied. A physics model for initial propellant temperature effecting evaporation rate has been developed in this paper.

对自燃推进剂（MMH/NTO）初始温度对火箭发动机燃烧稳定性的影响进行了研究，从推进剂初始温度对蒸发速率的影响规律出发，发展了初始温度大小影响蒸发速率的物理模型。

互联网摘选

Application of XPS and Sims to the study of combustion theory of solid propellant

表面分析技术（XPS及SIMS）在固体推进剂燃烧理论研究中的应用

互联网摘选

Effects of Injection Structure on Combustion Stability in Liquid Propellant Gun

液体炮中喷射结构对燃烧稳定性的影响

互联网摘选

The Experimental Study on the Thermal Aging Combustion Property of the Composite Modified Double Base Propellant and its Life Time Calculation

改性双基推进剂热老化燃烧性能试验研究与寿命预估

互联网摘选

The self-radiation spectrum of the combustion flame of a solid propellant was measured using a multi-wavelength pyrometer.

采用多波长高温计测量了某种固体推进剂燃烧火焰的自辐射光谱，并进行了数据处理。

互联网摘选

Study of Liquid Propellant Ignition and Combustion in High Energy Gas Fracturing

高能气体压裂用液体药点火与燃烧研究

互联网摘选

A numerical analysis model of tangential combustion instability in liquid propellant engine

液体火箭发动机切向不稳定燃烧数值分析模型

互联网摘选

Based on the solid propellant burning rate formula, a new method for the combustion time determination during the data treatment in solid rocket motor firing test was studied with a method of numerical integration and interpolation.

以固体推进剂燃速公式为基础，采用计算力学中的数值积分及插值法，并利用计算机技术，研究了用燃烧室药柱的实际肉厚，确定固体火箭发动机试验曲线中燃烧时间的新方法。

互联网摘选