An efficient and modular modeling for launch dynamics of tubed rockets on a moving launcher

This paper develops a modular modeling and efficient formulation of launch dynamics with marching fire (LDMF) using a mixed formulation of the transfer matrix method for multibody systems (MSTMM) and Newton-Euler formulation. Taking a ground-borne multiple launch rocket systems (MLRS), the focus is on the launching subsystem comprising the rocket, flexible tube, and tube tail. The launching subsystem is treated as a coupled rigid-flexible multibody system, where the rocket and tube tail are treated as rigid bodies while the flexible tube as a beam with large motion. Firstly, the tube and tube tail can be elegantly handled by the MSTMM, a computationally efficient order-N formulation. Then, the equation of motion of the in-bore rocket with relative kinematics w.r.t. the tube using the Newton-Euler method is derived. Finally, the rocket, tube, and tube tail dynamics are coupled, yielding the equation of motion of the launching subsystem that can be regarded as a building block and further integrated with other subsystems. The deduced dynamics equation of the launching subsystem is not limited to ground-borne MLRS but also fits for tanks, self-propelled artilleries, and other air-borne and naval-borne weapons undergoing large motion. Numerical simulation results of LDMF are given and partially verified by the experiment.     

Recent advances in catalytic combustion of AP-based composite solid propellants

Composite solid propellants (CSPs) have widely been used as main energy source for propelling the rockets in both space and military applications. Internal ballistic parameters of rockets like characteristic exhaust velocity, specific impulse, thrust, burning rate etc., are measured to assess and control the performance of rocket motors. The burn rate of solid propellants has been considered as most vital parameter for design of solid rocket motors to meet specific mission requirements. The burning rate of solid propellants can be tailored by using different constituents, extent of oxidizer loading and its particle size and more commonly by incorporating suitable combustion catalysts. Various metal oxides (MOs), complexes, metal powders and metal alloys have shown positive catalytic behaviour during the com-bustion of CSPs. These are usually solid-state catalysts that play multiple roles in combustion of CSPs such as reduction in activation energy, enhancement of rate of reaction, modification of sequences in reaction-phase, influence on condensed-phase combustion and participation in combustion process in gas-phase reactions. The application of nanoscale catalysts in CSPs has increased considerably in recent past due to their superior catalytic properties as compared to their bulk-sized counterparts. A large surface-to-volume ratio and quantum size effect of nanocatalysts are considered to be plausible reasons for improving the combustion characteristics of propellants. Several efforts have been made to produce nanoscale combustion catalysts for advanced propellant formulations to improve their energetics. The work done so far is largely scattered. In this review, an effort has been made to introduce various combustion catalysts having at least a metallic entity. Recent developments of nanoscale combustion catalysts with their specific merits are discussed. The combustion chemistry of a typical CSP is briefly discussed for providing a better understanding on role of combustion catalysts in burning rate enhancement. Available information on different types of combustion nanocatalysts is also presented with critical comments.     

武装直升机火箭武器对地攻击方式效能评估

根据某型武装直升机机载火箭武器的四种对地攻击方式,建立了该型直升机实战中将遭遇的作战条件的战场模型。采用层次分析法,建立了确定各作战条件模块加权系数的判断矩阵并计算了加权系数;结合各种对地攻击方式和该型直升机火箭武器系统的特点,确定了各攻击方式下各模块的效能系数。在加权系数和效能系数的基础上,计算了各作战条件下四种对地攻击方式各自的作战效能,得出一个当前作战条件下的最佳攻击方式提供给飞行员。为飞行员实施对地攻击提供了科学依据     

三组元液体火箭发动机实现单级入轨的优化分析

建立了三组元液体火箭发动机性能计算模型、单级入轨可重复使用运载器质量模型和弹道模型,以起飞质量为目标函数,优化得到了实现单级入轨的发动机基本参数。结果显示:三组元发动机性能比氢氧发动机高10%。本研究是三组元发动机系统设计和分析的基础。     

火箭发动机控制活门动态特性模拟与测试

根据电动活门的工作原理和采样定律，通过活门等效器ＤＸＱ－１的设计，介绍了火箭发动机控制活门动态特性模拟与测试，分析了电路参数选取和设计的基本依据，并给出了有关的理论分析结果。     

液体火箭发动机故障诊断的命题逻辑方法

为对液体火箭发动机诊断知识的表达和组织提供一种简洁有效和易于处理的方式 ,通过以命题逻辑公式和子句的形式对系统观测信息和定性特征加以描述建立定性诊断模型 ,同时诊断问题基于归结原理和假言推理规则的演绎推理方法求解。基于试车数据的诊断结果表明方法具有较强的诊断能力。     

伞盘结构对大长径比发动机药柱结构完整性的影响

为了提高大长径比发动机药柱结构完整性水平,基于三维黏弹性有限元法,计算某大长径比固体发动机在温度和内压荷载联合作用下的结构响应;研究伞盘结构及其位置对药柱最大Von Mises应变的影响规律;讨论当伞盘位于药柱中部时,伞盘最大Von Mises应变随伞盘宽度、深度以及顶部圆弧半径比的变化规律。结果表明,伞盘位于药柱中部时可以有效地降低大长径比药柱的最大Von Mises应变,增加伞盘宽度、深度或选取合适的半径比均可降低伞盘结构的最大Von Mises应变。所得结论可为固体发动机设计提供参考。     

火箭子母弹抛撒过程测试

子弹撒布特性是火箭子母弹的一项重要技术指标,描述了火箭子母弹地面抛撒过程的测试方案和扩散过程的计算方法,给出了某火箭子母弹的测试结果。     

织女一号气象火箭设计中的若干技术

织女一号气象火箭是一种小型无控固体火箭,由于采用了若干先进的技术,使其总体性能达到了国际先进水平。本文介绍了其总体性能,重点介绍了总体方案设计中采用的包括最优推力程序等若干先进技术。     

变推力液体火箭发动机脉宽采样数字控制

本文对变推力液体火箭发动机的脉宽采样数字控制系统进行了理论分析和实验研究。文中提出了此类控制系统的时宽输入模型,讨论了系统的稳定边界和无波纹响应条件,指出了影响动静态响应的关键因素及其与一般比例反馈控制的区别,并分析了发动机试车时动态特性随工况大幅变化的原因。