火箭推进剂皮肤防护装备研究现状及发展趋势

对皮肤防护装备的应用和发展进行了综述，分析了塑料、橡胶与火箭推进剂的相容性，以及目前国内火箭推进剂皮肤防护装备存在的缺陷，并对推进剂专用皮肤防护装备的发展趋势进行了探讨。     

主动引射高模试车台水喷雾冷却器等效热力系统模型的研究

水喷雾冷却器在主动引射高空模拟试车台中具有重要作用,其出口处温度的有效控制是保障试车正常运行的关键。针对某型号火箭发动机常压试验的喷雾冷却器,建立了等效热力系统模型,并在Simulink平台上建立了相应的动态仿真模型,计算结果与试车测试结果对比证明所建等效热力系统模型正确,从而为实现其出口处温度的有效控制提供依据。     

固体火箭发动机可靠性评定的影子理论及应用

首次提出可靠性评定的影子问题,证明了影子定理,并用影子定理对固体火箭发动机的结构可靠性进行了评定,表明其具有应用价值。     

喷管后段内壁铣槽加工工艺

归纳了喷管后段内壁在铣槽加工中容易出现的问题,从技术上进行了分析,结合机床特点,介绍了采取的一系列措施,重点阐述了解决问题的方法和注意事项。解决了长期困扰在生产中的难题,大副降低了加工中的误差幅度。     

长征系列运载火箭航天发射总次数突破两位数

长征系列火箭为中国航天运载火箭的统称。文章讨论了该系列火箭的组成和航天发射情况。     

推进剂制造过程中组分快速分析方法概述

以复合固体推进剂为主，概述了制造过程中多种实时分析和相对快速分析方法，包括色谱法、极谱法、红外光谱法、Ｘ－射线萤光光谱法。详细比较了ＨＰＬＣ和流动注射分析（ＦＩＡ）之间的差异，提出了ＦＩＡ的优点及其在推进剂中应用的潜力。     

Evaluation of pressure oscillations by a laboratory motor

Aeroacoustic pressure oscillation is one of the important challenges in segmented solid rocket motors with high slenderness ratio. The reason for these oscillations can be searched in vortex shedding due to grain burning surfaces, holes and slots. In this paper, a novel sub-scaled motor was used for evaluation of aeroacoustic pressure oscillations. First, the related parameters to scale down using Buckingham’s Pi-theorem were determined and then the sub-scaled motor was designed and manufactured. After this, Strouhal number in various grain forms and vortex shedding prediction criteria have been discussed. Then, one-dimensional linear and non-linear solution approaches have been presented. To understand the motor internal flow and vortex shedding formation, steady state computational fluid dynamic performed for seven regression steps and finally, two static tests have been performed. Results show that various definitions for Strouhal number are useful only for primarily glance on vortex shedding and pressure oscillations and so CFD solution and the test program are inevitable for a correct understanding of the ballistic operational condition of the motor. Experimental results demonstrated the existence of such oscillations with frequencies nearly equal to axial modes. It seems that non-linear parameters have small effects on aeroacoustic pressure oscillation and therefore the linear solution is acceptable to obtain approximate data. Of course, it should be emphasized that linear solution represents oscillations on overall motor action time, whereas the output of non-linear solution depends on thermochemistry properties of solid propellant and combustion products. Therefore, with a non-linear solution, oscillations maybe occur in some intervals of action time. FFT (Fast Fourier Transformation) results demonstrated that although both first and second acoustic modes have been excited, the position of longitudinal oscillation has an important role on which one is dominant.     

甲烷喷射温度对燃烧稳定性影响规律研究

对液氧/甲烷火箭发动机燃烧稳定性进行了数值仿真研究,比较分析了甲烷喷射温度对其燃烧稳定性的影响规律.结果表明：在222 K,224 K,226 K,228 K,230 K和234 K时,发动机燃烧稳定性较好.     

瞬态时域数据合成冲击响应谱算法研究

某液体火箭发动机的部件采用振动台进行模拟冲击环境试验,冲击控制谱的冲击时域波形由软件采用基本波形合成,基本波形有正弦波、合成小波、Chirp波形,而国内常用正弦波合成冲击谱进行冲击环境试验。给出了瞬态冲击数据合成法的算法过程,提取某液体火箭发动机试车过程中的冲击时域数据来合成冲击控制谱的冲击时域波形,计算结果表明算法有效,所合成的冲击时域数据能够满足冲击响应谱的精度要求。     

液氧/甲烷燃气发生器试验研究

为了研究液氧/甲烷的点火和燃烧特性,进行了液氧/甲烷燃气发生器热试验研究。介绍了液氧/甲烷燃气发生器热试验的试验装置、试验方案和试验情况,分析了试验结果。试验结果表明燃气发生器设计方案和点火方案可行,点火品质较好,能够在较宽的工作条件下稳定工作,燃烧组织合理,燃烧品质良好,温度均匀性较好,积碳轻微。