火箭发动机

Lastly, two-phase flow flied is studied under spinning (60n/s and 100n/s) condition, integral calculation of the two-phase flow is completed in the spinning SRM combustion chamber and nozzle, and the behavior and varieties of parameters of different diametric particles are studied in spinning internal flow flied thoroughly. The analysis of result and discussion are presented by comparison to two-phase flow flied of no-spinning case.

最后重点研究旋转情况下(25n/s和60n/s)固体火箭发动机两相流场，进行旋转固体火箭发动机燃烧室—喷管一体化两相流场数值模拟，分析了发动机内不同颗粒的运动及参数变化规律，并与不旋转两相流场对比进行结果分析和讨论。

Solid rocket engine ; Hybrid propellent rocket engine ; Performance analysis

固体火箭发动机；固液混合火箭发动机；性能分析

The evolution course of Chinese solid rocket propulsion technology for space missions since 1950s is presented.

叙述了 2 0世纪 5 0年代以来中国航天固体火箭推进技术的发展历程，介绍了 9种最具代表性的固体火箭发动机的技术特征、研制过程、地面试验和飞行情况，这些发动机分别应用于中国的探空火箭、运载火箭上面级和应用卫星变轨系统。

The high frequency combustion instability in liquid rocket engine LRE is analyti cally studied by usin g CFD methods.The comprehensive model and governing equations for numerical simu lation of high frequency combustion instability are presented.The PISO and MacCo rmack algorithms are compared in this study.Both methods can successfully handle combustion instability analysis.

应用CFD方法对液体火箭发动机中的高频燃烧不稳定性进行了分析研究，建立了液体火箭发动机不稳定燃烧数值模拟的综合模型和控制方程，比较了PISO和Ma cCormack两种算法，得出了两种算法均能成功应用于不稳定燃烧分析的结论。

Through malfunction of the tests of 810 Research Institute, the combustion performance of the hybrid motor and model about regression rate have been studied in the dissertation. The main aspects are as follows: The performance of the HNO3+N2O4 -HTPB hybrid rocket motor were all discussed.

本文结合航天科技集团公司810研究所正在研制的AK-20L/HTPB+Al组合固液火箭发动机，开展了固液火箭发动机混合燃烧特性的数值模拟工作，在此基础上给出固体燃料退移速率预示模型及预示结果。

To improve the stability of Arcjet discharge plasma in low current and high voltage mode, research on the demand of output characteristics of Arcjet Power Conditioning Unit was conducted. In this paper, based on PWM invertors and current mode control, using MOSFET as the main power device, an Arcjet Power Conditioning Unit was developed. Through adding a closed loop feedback circuit of output voltage, it can make the output characteristics of PCU be positive resistance to ensure the stability of Arcjet discharge plasma. The experiment indicates that this PCU can make Arcjet engine work at high voltage mode (100 V, 10 A) and ensure the stability of arcjet discharge plasma. Finally, it provides the experimental data of Arcjet when working.

为了解决小电流、高电压下电弧火箭等离子体的稳定性问题，研究了电弧火箭发动机对电源调理单元的输出特性要求，基于逆变电源脉宽调制技术与峰值电流型控制原理，以MOSFET为主功率器件，研制了一台电弧火箭电源调理单元，给出了Arcjet工作时的实验数据，通过增加PCU输出电压的闭环反馈电路，可以使PCU的输出外特性呈现正阻性，保证电弧的稳定燃烧，实验结果表明，该电源调理单元能使电弧火箭发动机达到高电压工作模式(100V， 10A)，保持电弧工作的稳定性。

In order to design optimum nozzle for air-air missile solid rocket motor, the mass model of solid rocket motor, the nozzle specifice impulse model of solid rocket motor and the objective function are established. Five different type of nozzles are choosen lor calculation: Conical, parabolidal,two different arcs,quadiatic polynominal and cubic polynominal.

以两种空-空导弹固体火箭发动机喷管作为算例，为此，建立固体火箭发动机的质量模型，喷管的质量比冲模型和目标函数模型，选择五种喷管扩散段内型面：锥形喷管，抛物线喷管，双圆弧喷管，二次多项式喷管和三次多项式喷管，进行优化设计，利用优化理论，成功地完成了五个设计变量的优化问题。

High speed rotation solid propellant rocket motor recording apparatus which we designed is going to resolve pressure testing of rocket motor in high speed rotation.

本文设计的高速旋转固体火箭发动机内置动态参数记录仪，着重解决火箭发动机在高速旋转状态下压力测试问题。

Key technologies of developing variable thrust rocket engine are analyzed.

火箭发动机的关键技术，最后提出适合我国国情的变推力液体火箭发动机技术的发展设想。

By processing the measured data of the multiwavelength pyrometer at two different time, the true temperatures and spectral emissivities at two different time can be simultaneously calculated.

实验结果表明，其真温计算值与火箭发动机设计者提供的理论值之差在± 2 0K以内，说明该方法是解决固体火箭发动机羽焰温度测量的可行性方法

But we don't care about Battlegrounds.

但我们并不在乎沙场中的显露。

Ah! don't mention it, the butcher's shop is a horror.

啊！不用提了。提到肉，真是糟透了。