旋风号火箭的设计和今后发展

旋风号运载火箭是独联体国家现在使用的一种重要的轻型火箭。它是以洲际弹道火道为基础设计的。重点介绍了该火箭的结构及其演变、设计思想、性能、发射系统以及今后的发展。     

CZ-2C火箭常规二级推进剂钝化过程分析

CZ-2C火箭发射SSO轨道卫星在星箭分离后其二级箭体轨道寿命很长,成为空间垃圾。为适应空间碎片减缓工作的需求,应该对二级箭体内剩余推进剂进行排放处理。针对优选排放方案,分析排放过程的工作情况和参数,并参照遥测数据对分析结果进行验证。     

液体火箭发动机研制情况的一些回顾

４０年来，我国液体火箭发动机的研制工作取得了很大成绩。文中对发动机的一些研制情况作了回顾，对ＹＦ－７３和ＹＦ－７５氢氧发动机的设计特点、飞行结果作了简单叙述。对今后工作也提出了看法。     

有关H－Ⅱ运载火箭的动力学课题研究

重点介绍有关Ｈ—Ⅱ运载火箭（以下简称Ｈ—Ⅱ）的一些动力学课题的研究状况。其中，重要的动力学课题有全箭振动、ＰＯＧＯ、防液体晃动、分离动力学试验、动力学环境试验等。针对这些动力学课题，日本有关部门已研究多年，既作了充分的地面试验，又进行了有效的工程应用研究，最终保证了Ｈ—Ⅱ的首次飞行成功。     

Improved Quality Output through Computer‐Based Training: An Automotive Assembly Field Study

In this article, two field experiments, conducted in an automotive assembly plant, evaluate how computer‐based training of operational sequences and related quality information can support the assembly performance of the operators. The experiments were performed during the launch of a new vehicle. A comparison was made of learning progress and quality performance between a reference group of operators that only had regular training and a test group for which some of the regular training was replaced with individual computer‐based training. Both quantitative measures of the quality output and questionnaires and observations were used to evaluate the effects of computer‐based training. The results show a clear positive difference in learning progress and improvements in quality output for the test group compared with the reference group. This combined with positive attitudes expressed by the operators and their team leaders shows that this type of training is an effective way to train operators during launches of new vehicles in automotive production.     

运载火箭载荷主动减缓控制律的设计与仿真

该文的研究内容包括两个方面,一方面讨论了高空风的抑制方法,设计了加速度反馈的载荷主动减缓控制律；另一方面,文中建立了运载火箭姿态控制系统仿真模型,研究在MATLAB环境下对一类复杂的时变系统仿真的问题。利用MAT LAB模型对载荷主动减缓控制律进行仿真,结果表明,此控制律能有效地抑制高空风,尤其是减小切变风引起的气流攻角。     

运载火箭一级发动机自动归零技术研究

基于现役某型号运载火箭一级伺服回路的控制方案和原理,提出一种在发射场一级发动机挂齿后进行自动归零的方法.经发射场试验实际验证:一级发动机喷管在实施自动归零措施后可快速回零且不发生偏离,自动归零方案可行有效.     

防空多管火箭武器跟踪发射模型研究

立足于火箭武器发展的需求,研究了防空多管火箭炮的跟踪运动对火箭弹离轨参数的影响,给出了跟踪发射时火箭弹运动参数的计算方法,确定了火箭弹脱离定向器瞬时的运动参数,获得了空间弹道计算的初始条件,同时研究了两种特殊跟踪运动下火箭弹的离轨参数,为火箭弹飞行性能优化和发射装置的设计提供了参考。     

基于ADAMS的多管火箭炮动力学仿真分析

基于虚拟样机技术，研究多管火箭炮武器系统加装缓冲装置发射时期的动力学特性。根据火箭炮系统的几何模型简化出适合动力学仿真的物理模型，在ADAMS软件平台下建立系统仿真样机，编制仿真发射程序，对比有无缓冲装置条件下火箭炮系统的俯仰轴和方位轴所受冲击扰动力矩和底座的受力的情况，为多管火箭炮系统的设计和试验提供参考数据，有效缩短火箭炮系统开发周期，节省研制经费。     

A neutronics analysis of long-life, sectored compact reactor concepts for lunar surface power

Neutronics analysis is performed of low temperature (≤900 K) Sectored Compact Reactor (SCoRe-N_x) concepts for operational lives >20 years. They are cooled with circulating liquid Nak-78. The reactor vessel and the UN fuel pins cladding are made of stainless steel. The power systems with the SCoRe-N_x concepts have no moving parts and employ SiGe thermoelectric elements for converting the reactor’s thermal power to electricity at a load voltage >300 VDC. Separate SiGe elements power the electromagnetic pumps that circulate the liquid NaK-78 in the reactor and 6 pairs of primary and secondary loops. Analysis confirmed that the submerged bare reactors in wet sand and flooded with seawater, in the unlikely event of a postulated launch abort accident, are sufficiently subcritical. Results show that the SCoRe-N₅-S concept is capable of operating for 62 full power years at 200 kW_th, while requiring 75% of the control drums to shutdown the reactor at BOL. With only 50% of the control drums required at BOL to shutdown the reactor, its operational life decreases to 39 full power years.