1) pasty propellant rocket
膏体火箭
1.
In order to study effects of burning surface variation on interior ballistics adjustment precision of pasty propellant rocket motor,burning surface functions of straight round pipe nozzle and conical expand nozzle were derived respectively based on the working principle of pasty propellant rocket motor.
为研究燃面变化对膏体火箭发动机内弹道调节精度的影响,根据膏体火箭发动机的工作原理,分别推导了直圆管喷嘴和锥形扩张喷嘴型面下的膏体推进剂燃面方程,建立了膏体火箭发动机零维内弹道模型,分析了喷嘴型面对发动机内弹道性能的影响,并进行了直圆管喷嘴发动机试验。
2) liquid rocket
液体火箭
1.
Analysis of liquid rocket propellant evaporation characteristic in natural environment;
液体火箭推进剂在自然环境中蒸发特性
2.
The calculation of the intrinsic frequency of the liquid rocket propulsion system
液体火箭推进系统液路固有频率计算
3) Rocket case
火箭壳体
4) solid rocket
固体火箭
1.
In order to judge the stability of the surface crack in solid rocket motor (SRM) grains while the SRM was launched in different environmental temperature.
为了探讨环境温度对固体火箭发动机点火发射时药柱内表面裂纹稳定性的影响,以翼锥-过渡伞盘-圆柱组合药型的发动机为例,采用三维有限元方法,在发动机药柱的危险截面上沿危险方向预设裂纹,在裂纹尖端构建奇异三维裂纹元,计算在不同环境温度下点火发射时裂纹的应力强度因子。
2.
By analyzing and summarizing the flow characters of exhaust jet of solid rocket,we have developed a kind of equipment which can be used for measuring the multi-point pressure of high-speed exhaust jet and then we have practically tested the flow of under-expansion solid rocket motor.
在总结与分析了固体火箭燃气射流流动特性的基础上,研制开发了用于测量高速燃气射流的多点测压装置,并且使用该装置对欠膨胀固体火箭发动机的燃气射流流动进行实验测试。
3.
Considering the features of solid rocket motor jet, a kind of experimental equipment based on the pitot tube technology for measuring the multi-point pressures was developed.
结合固体火箭燃气射流的特点 ,开发了基于皮托管技术的多点压力参数实验测量装置 ,运用实验的方法 ,对燃气射流流场进行了研究 。
5) nose cone
火箭锥体
6) dry-fuel rocket,powder rocket,solid rocket,solid rocket unit
固体火箭<火>
补充资料：液体火箭
利用液体火箭发动机作动力装置的火箭，又称液体推进剂火箭。
说明：补充资料仅用于学习参考，请勿用于其它任何用途。
参考词条