Shock-induced chemical processes and ‘molecular rocket reaction’ in metallocenes and their cyclodextrin inclusion compounds

Shock-induced yield enhancement has been observed in implantation of recoil atoms into metallocene and its-cyclodextrin (CD) inclusion compounds, as in the case of metal-diketonate compounds previously studied. The enhancement, however, occurs at much lower energy compared with that in metal-diketonates. In acetylruthenocene and benzoylruthenocene--CD inclusion compounds, various aspects of molecular rocket reaction have been discussed.This article was processed by the author using Springer-Verlag T_EX PJour2g macro package version 1.     

火箭橇加载试验技术研究

根据空气动力学和火箭发动机的相关理论,针对600 m长无缝滑车轨道,对搭载50 kg有效载荷、速度为45 m/s和搭载100 kg有效载荷、速度为200 m/s的两种双轨滑车进行了理论估算和试验验证。试验中,滑车的速度测试采用磁感应法、激光法和高速摄影法三种方法。试验结果表明,三种测试方法获得的滑车速度值一致,测试结果与理论计算值符合得较好。     

导弹发射装置滑轨表面MoS2干膜防护高温高速两相燃气流应用研究

选用多种MoS2干膜润滑材料，对滑轨式武器发射系统的高能有烟发动机两相燃气流高温烧蚀、熔融残渣的高速热冲蚀以及粘渣-烧蚀耦合破坏作用进行有效的润滑和防护试验，分析了烧粘现象和残渣组成，采用发动机试车台模拟试验及国军标环境条件试验评估了多种MoS2干膜润滑材料的防护特性．结果表明：国产MoS2干膜防护涂层兼有一定的润滑及防腐蚀功能，能显著改善滑轨表面的润滑性能和抑制高温高速燃气流的烧粘-腐蚀破坏作用；滑轨表面烧粘-腐蚀程度与发动机推进剂的铝粉性质及含量(残渣量)直接相关，各种防护涂层的主要破坏形式为烧蚀、热冲蚀以及粘渣破坏，由于残渣含腐蚀物，有必要在烧粘后及时清洗并施行二次防护，其中热固型MoS2干膜的防护性能优于常温固化型MoS2干膜，但由于燃气严重的热冲蚀，还需采用常温快速固化的MoS2干膜进行现场修补．     

Effect of propellant morphology on acoustics in a planar rocket motor

This paper reports the results of numerical simulations of the acoustics in a two-dimensional (plane) motor using a high-order accurate, low-dissipation numerical solver. For verification we compare solutions to Culick’s (AIAA J 4(8):1462–1464, 1966) asymptotic solution for constant injection, and to recent results of Hegab and Kassoy (AIAA J 44(4):812–826, 2006) for a space- and time-dependent mass injection. We present results when the injection boundary condition is described by propellant morphology and by white noise. Morphology strongly affects the amplitude of the longitudinal acoustic modes, and in this connection white noise is not a suitable surrogate.      

Aluminum combustion in a solid rocket motor environment

A model for prediction of particle radius and oxide cap size/shape versus time for an aluminum particle tracking a stream-tube through a solid rocket motor port has been developed. Following preliminary calculations leading to a postulated flame structure, a quasi-steady model to predict instantaneous consumption of aluminum and generation of condensed oxide (both as a cap on the aluminum particle and as smoke) as a function of instantaneous particle size, ambient conditions, and cumulative amount of oxide in the cap was developed. Finally, this model was imbedded into a framework tracking evolution of particle size, oxide cap size, and ambient conditions, which change as the particle travels along a stream-tube consuming oxidizer and releasing heat. Qualitative agreement was found between predictions and limited observations.     

A phase sensitive modulated thermography of debondings in the insulator of SRMs

Solid rocket motors (SRMs) have been widely applied in missiles, space rockets and shuttles. However, because of some technological and environmental reasons, debonding or poor bonding usually appears in the insulator of SRMs. To evaluate the bonding state between the insulator and the shell during manufacturing, a phase sensitive modulated thermography (MT) is proposed. In order to optimize the operating condition, the influences of the modulation frequency, insulator thickness and debonding lateral size on defect signals are studied through experimentation and 3D numerical simulation. Finite element analysis (FEA) using ANSYS software is applied to simulate the thermal process of the structures precisely. The results show that phase sensitive MT is an effective approach to detect the debondings in the adhesion interfaces. The phase difference at the modulation frequency can be expressed as a quintic polynomial of the modulation frequency in the usual operating frequency range, and the best modulation frequency and detectable frequency band can be determined by the polynomial; when the insulator thickness increases, the best modulation frequency and the maximum phase difference decrease; when the debonding lateral size increases, the maximum phase difference increases while the best modulation frequency remains unchanged. The results provide a guideline for the MT of debondings in SRMs.     

导弹动爆对模拟船舱毁伤效果试验研究

 设计了基于火箭橇的导弹动爆试验,介绍了模拟船舱的结构尺寸、测试点的布设情况及测试仪器性能。通过获取的断线、光、压力、加速度信号得出如下结论：测试方法有效;冲击波在舱室内传播不均匀,导弹运动方向反射冲击波很大,反方向较小,两者比例可达3.5∶1,舱室的角隅部位冲击波压力高于壁面正反射压力;导弹穿甲时舱壁的冲击振动高达10 000 g,且穿甲舱壁的冲击远大于其它舱壁,被破片击中会加大舱壁的振动幅值。     

关于水火箭水平射程的实验探究

介绍了自制水火箭及其发射装置的制作过程,探究了影响水火箭的水平射程的因素.在猜想假设、实验探究的基础上得出结论.     

考虑Stefan影响的单颗粒硼着火过程研究

针对含硼推进剂固体火箭冲压发动机内单颗粒硼的着火过程展开了系统研究. 考虑硼颗粒周围气相流动以及硼颗粒与周围环境间的传热传质过程, 建立了考虑Stefan流作用的一维硼颗粒着火模型, 研究了硼颗粒实现着火和未能实现着火两种典型情形下硼颗粒及周围气相的参数变化规律, 对两种情形下Stefan流的变化规律及其成因展开了详细分析. 研究表明, 在硼颗粒实现着火的过程中, 液态B₂O₃的蒸发及硼的 氧化均能在硼颗粒的反应自加热作用下急剧加速, 硼颗粒表面附近的氧气和气相B₂O₃分布变化剧烈; 在未能实现着火的过程中, 液态B₂O₃的蒸发和氧气消耗的质量流率相对较小, 并逐渐趋于稳定, 硼颗粒表面附近的氧气和气相B₂O₃分布相对变化很小.在两种典型情形下, 硼颗粒外表面的Stefan流都会经历先由周围空间流向颗粒表面, 而后变为由颗粒表面流向周围空间的过程. 关键词： 固体火箭冲压发动机 硼颗粒 着火过程 Stefan流     

铝的发展、应用和新机遇

从铝元素的发现开始，逐步介绍性质优异的铝元素在工业制造以及人们日常生活等方面不可取代的应用，同时探讨了铝及其化合物的生物毒性。随着纳米技术蓬勃发展，金属铝纳米结构作为极具潜力商业化的、可持续的局域表面等离子体材料受到人们广泛关注。总结近几年铝纳米粒子的合成方法，以及在局域表面等离子体打印、表面增强拉曼检测等方面的应用。