1) Spinning solid propellant rocket
自旋固体火箭
1.
The paper deduced the Fluid dynamics model of Spinning solid propellant rockets,and validated the Fluid dynamics model by analyzing the examples,the result accord with the actual status.
推导了一种自旋固体火箭的流体动力学模型,并通过实例对模型进行了验证计算,计算结果与实际情况基本吻合。
2) 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 。
3) swirling solid rocket motor
旋转固体火箭发动机
1.
Some results of numerical simulation on the internal ballistics of a swirling solid rocket motor are summarized, including predictions of the burning rate sensitivity of aluminized HTPB propellants and the internal ballistics of motors in an accelerated field.
系统地总结了旋转固体火箭发动机内弹道数值模拟方面的某些成果，其中包括含铝丁羟推进剂燃速敏感性预示和星孔形及“锥—柱”形装药发动机内弹道预示，得出了一些有益结论，可供发动机设计和装药配方设计参考。
4) dry-fuel rocket,powder rocket,solid rocket,solid rocket unit
固体火箭<火>
5) antispin rocket
反自旋火箭
6) solid rocket propellant
固体火箭推进剂
1.
By studying and summing up the failure physical models in common use,this paper advanced a cumulative damage-reaction theory life model to the storage and usage of solid rocket propellant,and,by calculating examples,demonstrated this model clearly.
通过对常用失效物理模型的分析和总结,提出了固体火箭推进剂贮存使用寿命的累积损伤-反应论模型,并通过算例阐释了这一模型。
2.
By using real time holographic interferometry,the solid rocket propellant combustion process were investigated and recorded by a video camera with a shooting speed of 25 frames per second and the maximum electronic shutter speed of 1/2000 second.
本文采用实时全息法与摄像机相结合的方法来研究固体火箭推进剂的燃烧过程，记录速度为２５帧／秒，曝光快门速度最高可达１／２０００秒。
3.
Anti-stick coatings for stripping of solid rocket propellant, which could be cured at room temperature had been successfully developed.
开发一种用于固体火箭推进剂脱模的可常温固化溶剂型防粘涂料,该涂料是以常温固化型氟树脂为基体,加入改性微粉及其他各种助剂,配制而成的悬浮液。
补充资料：自旋-自旋弛豫
自旋-自旋弛豫
磁共振成像术语。又称T2弛豫或横向弛豫(transverse relaxation)，指垂直于外磁场B0方向的磁化矢量的指数性衰减过程。磁共振成像时，对置于外磁场B0中的自旋系统施加90°射频脉冲，则自旋系统被激励，其净磁化矢量指向与外磁场B0垂直；射频脉冲终止后，被激励的质子与邻近的原子核之间发生相互作用，逐渐失去相位，净磁化矢量指向恢复与外磁场平行，该过程称自旋-自旋弛豫。自旋-自旋弛豫过程无能量交换。
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