火箭研究

On the basis of the study on the shaping law to process the cowled integral impeller with ECCEM, the data depict the blade surface of the cowled integral impeller were processed, so that the tool-cathode was devised and its path in the process was obtained. Then the shape of the tool-cathode and its path were adjust according to the simulation of the computer.

由于带冠整体叶轮是整体叶轮结构设计的发展方向之一，特别在火箭发动机中，论文在研究展成电解加工带冠整体叶轮成型规律的基础上，分析处理带冠整体叶轮的型面数据，计算加工轨迹，设计工具阴极，并依据计算机仿真对加工轨迹和工具阴极的形状进行修正。

To predict influence of the rocket acceleration force and vibration on electron cyclotron resonance thruster when it is being launched to space, a finite element model of 10 cm C/C composite material grid was established with finite element analysis software. Some of its dynamic characteristics, vibration response characteristics and models was analyzed.

为了研究电子回旋共振推力器在搭载火箭升空过程中，过载和振动环境对栅极带来的影响，采用有限元分析软件建立了10 cm C/C复合材料栅极的有限元分析模型，计算分析了不同C/C复合材料栅极的力学性能、频率响应和振动模态。

On the background of the new rocket depth charge multifunction fuze, the signal processing circuit of ultrasonic detection receiver is studied. The aim of this dissertation is to improve the performance of the receiver.

本文以火箭深弹新型多作用体制引信为应用背景，主要就引信声近炸模块主动超声波探测接收机信号处理电路进行了研究，目的是提高接收机对回波的处理能力，从而提高引信探测目标能力和近炸精度。

The basic theories of the solid rocket motor, the method of grid generation, discrete equations and coupled two-phase flow flied are introduced in detail.

论文以某小型实验发动机为研究对象，介绍了固体火箭发动机的基本理论、网格生成方法、方程的离散方法和两相耦合算法等内容。

This paper mainly presents the fluxion rules of burned gas during the course of rocket shell launching.

本文主要研究火箭弹发射过程中火箭燃气在火箭筒内的流动规律。

Propulsion Subsystem Technology (requires Research 5, Science 5, Engineering 5, Graviton Physics 4) plus Rocket Science 1

导航子系统技术：需要研究概论5，科学原理5，工程学5，引力物理学4+火箭科学1

The effort of spray characteristic on rocket engine combustion stability for hypergolic propellant was studied.

用数值方法研究了一甲基肼/四氧化二氮自燃推进剂喷雾液滴直径对火箭发动机燃烧稳定性的影响。

This paper develops a theoretical model of the heat radiation effect and the shock wave characteristics for liquid hypergolic rocket bipropellant explosion,as well as the explosion experimental method.

建立了自燃液体火箭推进剂爆炸热辐射效应和冲击波特性理论模型，介绍了实验研究的方法，给出了N2O4／UDMH液体推进剂爆炸产生的火球直径、火球温度、火球辐射热流、爆炸冲击波超压值等参数计算与实验观测结果，结果表明计算结果与实验观测结果吻合。

Tripropellant injector element is one of the most important components in tripropellant engine, which is studied with emphasis.

三组元喷嘴是三组元液体火箭发动机的重要部件，也是三组元发动机研究的重点之一。

Results of the research can be applied to health monitoring of liquid propellant rocket engine in ground test.

本论文的研究成果已经可以用于液体火箭发动机地面试车的故障检测。

The split between the two groups can hardly be papered over.

这两个团体间的分歧难以掩饰。

This approach not only encourages a greater number of responses, but minimizes the likelihood of stale groupthink.

这种做法不仅鼓励了更多的反应，而且减少跟风的可能性。