固体火箭发动机柔性接头弹性件力学性能研究

针对固体火箭发动机柔性接头中的橡胶材料，研究了在进行这种橡胶结构有限元计算中橡胶材料的力学行为的表征。进行了单轴拉伸与简单剪切材料力学性能试验，根据不同材料模型对试验曲线进行了拟合，并用MSC／Marc软件模拟了超弹性材料的单轴拉伸与简单剪切变形过程。结果表明：采用单轴拉伸试验数据预测材料剪切性能会造成明显误差，而简单剪切试验得到的模型可以比较准确描述材料的拉伸和剪切变形，针对柔性接头这种以剪切变形为主的结构，应选取剪切试验数据；当应变大于150％时，不同材料模型与试验数据的选用范围对计算结果具有明显影响。

Thermal fatigue on pistons induced by shaped high power laser. Part I: Experimental study of transient temperature field and temperature oscillation

Thermal fatigue behavior is one of the foremost considerations in the design and operation of diesel engines. It is found that thermal fatigue is closely related to the temperature field and temperature fluctuation in the structure. In this paper, spatially shaped high power laser was introduced to simulate thermal loadings on the piston. The incident Gaussian beam was transformed into concentric multi-circular beam of specific intensity distribution with the help of diffractive optical element (DOE), and the transient temperature fields in the piston similar to those under working conditions could be achieved by setting up appropriate loading cycles. Simulation tests for typical thermal loading conditions, i.e., thermal high cycle fatigue (HCF) and thermal shock (or thermal low cycle fatigue, LCF) were carried out. Several important parameters that affect the transient temperature fields and/or temperature oscillations, including controlling mode, intensity distribution of shaped laser, laser power, temporal profile of laser pulse, heating time and cooling time in one thermal cycle, etc., were investigated and discussed. The results show that as a novel method, the shaped high power laser can simulate thermal loadings on pistons efficiently, and it is helpful in the study of thermal fatigue behavior in pistons. (C) 2007 Elsevier Ltd. All rights reserved.

The scientific project of the small satellite of china

The efforts involved in developing a small satellite for scientific purposes in China in recent years are introduced in the present paper. The project is arranged on a case to case principle depending upon requirements and financial support. The space technology of a satellite and rockets, which have been developed over a relatively longer period in China, have been transferred to the scientific research of small satellites for improvement of the quality requirements. The surplus payloads of the rocket and satellite are used as the payloads of the small satellite and scientific experiments at a low cost. As an example, the project of balloon satellites for atmospheric research was successfully completed in 1991. The experience of the project management is of great benefit for further organization and arrangement of other projects. Opportunities exist for surplus payloads to be used in the future, and a small satellite for magnetospheric research will be launched in 1993.

火箭增程乘波外形导弹弹道特性研究

基于椭圆锥相交流场，采用非轴对称设计方法生成了一种带火箭增程的乘波外形高超声速导弹，并在给定攻角条件下对乘波外形导弹的弹道进行了仿真。仿真结果表明：导弹的飞行轨迹为波浪形；在满足热防护的条件下，给定乘波外形和初始滑翔速度的导弹存在一个较优的初始滑翔高度；导弹自带增程火箭的点火时间越早，其飞行距离越远。

模拟火箭引射混合特性的实验研究

专门设计了可用于研究箭基组合循环发动机（RBCC）在起动阶段（Ma= 0）所使用的引射火箭性能的实验装置。作为初步试验，研究了不同工况的引射热喷流（一次流）和被引射空气（二次流）之间混合的演 变、发展过程，找出不同来流条析下影响引射性能的主要参数，为最终探明引射火箭的最佳工作条件打下基础，同时根据试验结果提出了促进一、二次流混合的可行方案，便 于下一步深入研究。

应用于固体火箭发动机喷管出口羽流温度测量的光学辐射高温计

利用辐射光谱测量温度的原理,设计并制造了一种新型的非接触式光学辐射高温计.详细介绍该温度计的基本原理和标定方法,并将该温度计应用于火箭发动机喷管出口羽流的温度测量中,初步的实验结果和数值模拟结果相一致.

Dinámica de las Redes Virtuales de Fabricación Global en la Industria Aeronáutica

[ES] Las redes virtuales de fabricación global (RVFGs) están formadas por empresas independientes las cuales establecen entre sí relaciones de tipo horizontal y vertical, pudiendo incluso ser competidores, donde no es necesario mantener internamente grandes recursos fabriles sino gestionar y compartir eficientemente los recursos de la red.

火箭剩余推进剂排放过程的分析与模拟

为了减少空间碎片的产生，星箭分离后，需要在轨排放火箭末级贮箱内的剩余推进剂．分析表明，排放条件下的推进剂射流进入太空后，立即失稳破碎为大量液滴；液滴在高真空环境下扩散，它们的表面不断有气体分子蒸发，逐渐在箭体周围形成了一个由液滴和蒸气分子组成的羽流场．采取Lagrange方法追踪该流场中每个液滴的运动轨迹以及表面蒸发冷凝过程，利用直接模拟Monte Carlo方法计算蒸气分子的运动和碰撞，然后通过微观量的统计平均获得感兴趣的宏观流场、箭体表面的压力和剪应力分布等．为了检验稀薄蒸气算法、模型和程序，模拟了真空水射流周围水蒸气羽流场，获得的径向Pitot压力分布与Fuchs和Legge的实验数据的符合．在此基础上，分别模拟了CZ-4B火箭末级剩余燃料偏二甲肼在不同排放方式下的三维稀薄蒸气与液滴羽流场．计算表明：原排放方式的扰动力矩相当大，超出了火箭姿控范围，新排放方式的扰动力矩很小，处于火箭姿控范围之内．这些预测得到了飞行遥测数据的支持．