质子号运载火箭及其运营

质子号运载火箭是苏联专为航天发射任务设计的大型运载火箭。通过配备Block DM和微风M上面级适应不同要求的发射任务。文章对目前活跃在商业发射市场中的质子号运载火箭进行了介绍。     

Holographic subsurface radar for diagnostics of cryogenic fuel tank thermal insulation of space vehicles

Analysis of critical conditions on the reusable spacecrafts Columbia (USA), and Buran (Russia) related to defects in insulation and heat-protection coatings have been performed. It is shown that the existing methods of non-destructive testing, including ultrasonics, failed to prevent the disaster of the Space Shuttle Columbia and serious incidents involving the spacecraft Buran during its only flight. A new method for using the holographic subsurface radar RASCAN-5/15000 which reveals the internal defects of the coating was proposed, and experiments on models of thermal insulation coatings were performed. The experimental results were displayed in the form of radar images on which defects in the heat insulation provided a good contrast. The article reflects preliminary study and further efforts are needed to improve resolution of the technology.     

无负载工况液氧加注流量调试方法研究

针对某新建动力系统试验台液氧加注需求,设计阻力孔板流量调试方案。采用理论计算的方法确定孔板直径,并对加装孔板后的管路流场进行数值模拟,验证了设计的合理性。采用经验证的孔板进行流量调试,得到与各流量输出值相匹配的系统运行工况,将调试得到工况运用于实际的动力系统试验并对结果进行对比分析。结果表明,动力系统试验中液氧加注实际工况与流量调试所确定的工况吻合性好,采用孔板的流量调试方法合理可行。     

Performance analysis of no-vent fill process for liquid hydrogen tank in terrestrial and on-orbit environments

Two finite difference computer models, aiming at the process predictions of no-vent fill in normal gravity and microgravity environments respectively, are developed to investigate the filling performance in a liquid hydrogen (LH₂) tank. In the normal gravity case model, the tank/fluid system is divided into five control volume including ullage, bulk liquid, gas–liquid interface, ullage-adjacent wall, and liquid-adjacent wall. In the microgravity case model, vapor–liquid thermal equilibrium state is maintained throughout the process, and only two nodes representing fluid and wall regions are applied. To capture the liquid–wall heat transfer accurately, a series of heat transfer mechanisms are considered and modeled successively, including film boiling, transition boiling, nucleate boiling and liquid natural convection. The two models are validated by comparing their prediction with experimental data, which shows good agreement. Then the two models are used to investigate the performance of no-vent fill in different conditions and several conclusions are obtained. It shows that in the normal gravity environment the no-vent fill experiences a continuous pressure rise during the whole process and the maximum pressure occurs at the end of the operation, while the maximum pressure of the microgravity case occurs at the beginning stage of the process. Moreover, it seems that increasing inlet mass flux has an apparent influence on the pressure evolution of no-vent fill process in normal gravity but a little influence in microgravity. The larger initial wall temperature brings about more significant liquid evaporation during the filling operation, and then causes higher pressure evolution, no matter the filling process occurs under normal gravity or microgravity conditions. Reducing inlet liquid temperature can improve the filling performance in normal gravity, but cannot significantly reduce the maximum pressure in microgravity. The presented work benefits the understanding of the no-vent fill performance and may guide the design of on-orbit no-vent fill system.     

发射箱车载倾斜发射过程下沉量影响因素研究

为研究车载倾斜发射装置在导弹发射过程中发射箱下沉量的主要影响因素,通过改进的Craig-Bampton方法将车架、回转台、发射架等柔性体融合在车载导弹发射系统多体动力学模型中,建立导弹发射系统刚柔耦合动力学模型,研究车架变形、回转台变形、发射架变形、燃气流冲击、风载荷作用以及起竖油缸变形等因素对发射装置动态响应的影响,获得不同因素对发射箱下沉量的影响因子,为开展系统的优化设计,减小发射过程中发射箱的下沉量及导弹初始扰动提供了理论依据。     

俄罗斯运载火箭的历史、现状和发展方向

介绍了俄罗斯运载火箭的特点、生产及发射情况，对其部分特性与其它国家的运载火箭进行了比较。简单总结了俄罗斯运载火箭从改装战略导弹到有针对性研制的发展历程，列举了有代表性的在用型号和未来的研制方向。     

A theoretical study for the design of a new ballistic range

The ballistic range has long been employed in a variety of engineering fields such as high-velocity impact engineering, projectile aerodynamics, creation of new materials, etc, since it can create an extremely high-pressure state in very short time. Of many different types of ballistic ranges developed to date, two-stage light gas gun is being employed most extensively. In the present study, a theoretical work has been made to develop a new type of ballistic range which can easily simulate a flying projectile. The present ballistic range consists of high-pressure tube, piston, pump tube, shock tube and launch tube. The effect of adding a shock tube in between the pump tube and launch tube is investigated. This improvement is identified as the reduction in pressures in the high pressure tube and pump tube while maintaining the projectile velocity. Equations of motions of piston and projectile are solved using Runge-Kutta methods. Dependence of projectile velocity on various design factors such as high pressure tube pressure, piston mass, projectile mass, area ratio of pump tube to launch tube and type of driver gas in the pump tube are also analyzed. Effect of various gas combinations is also investigated. Calculations show that projectile velocities of the order 8 km/sec could be achieved with the present ballistic range.     

Pro／ENGINEER在航天器结构设计中的应用

提出将柱体或锥体部段的仪器电缆安装设计图样以展开形式绘 表示解决了Ｐｒｏ／ＥＮＧＩＮＥＥＲ在航天型号产品设计中的应用问题，并对应用该设计方法在仪器安装设计中可能产生相互干涉的误差进行了分析。     

浅析牵制释放发射技术

分析了国外火箭牵制释放发射装置的设计特点和设计要求，对其结构进行了综合研讨，在此基础上归纳了国外牵制释放发射机构的8点设计要求。提出了一种运载火箭强制牵制释放机构的设计思想和设计条件。     

适应伺服机构卡死故障的控制指令重分配技术研究

提出一种能够适应运载火箭伺服机构卡死故障的控制指令重分配技术。在传统运载火箭控制系统设计过程中,伺服机构指令是在不考虑伺服机构故障时设计确定的,一旦伺服机构发生卡死故障将可能导致箭体姿态失稳。为了提高运载火箭的安全性和可靠性,根据某伺服机构卡死角度,通过控制指令在多个冗余伺服机构之间的重分配,在伺服机构卡死情况下仍能保证姿态稳定。仿真结果表明,即使某个伺服机构卡死也能保证姿态稳定,而且不需要重新设计控制参数。