含运动副间隙舵机执行机构的动态特性研究

为了研究运动副间隙对空间4R机构动态特性的影响,间隙处的接触碰撞模型和摩擦的建立分别采用非线性弹簧阻尼模型和修正的库伦摩擦模型。在Solidworks中建立空间4R机构模型,导入ADAMS中进行动力学仿真分析。对比含间隙和不含间隙时系统动力学仿真结果的异同,分析间隙大小和最佳间隙量对空间4R机构动态特性的影响,为机构的设计提供了重要的参考依据,有利于工程实际应用。     

关于进一步加强学院科研工作的思考

通过到八所军队院校的科研工作调研,总结了他们科研管理的成功经验,简要分析了我院科研工作存在的问题,对进一步加强学院科研工作进行了理性思考,提出了科研工作机制创新的设想。     

扑翼UUV前肢驱动机构设计

通过对海龟前肢运动特点的分析和研究,对扑翼进行受力分析,充分利用惯性与流体力的作用,基于Unigraphics软件,实现前肢扑翼驱动机构的虚拟样机设计,简述此机构的周期运动过程,通过计算与仿真得出其粗略的推进力曲线及驱动电机参数,验证了机构的合理性。     

陶瓷基复合装甲防12.7mm穿甲燃烧弹的靶试研究（Ⅱ）

基于对材料特性和防弹机理的认识,设计了由（SiC＋Si）陶瓷、616装甲钢和高强PE材料构成的陶瓷基复合靶板,靶板防护面密度为118 kg/m2,尺寸为500 mm×500 mm×25 mm。利用现役12.7 mm穿甲燃烧弹考核靶板在6发弹打击下的防护能力,检验靶板设计思路。结果表明：靶板结构是可行的,可防住V25为818 m/s的现役12.7 mm穿甲燃烧弹。     

某型火炮制退机节制环磨损故障分析与处理

制退机的性能好坏直接关系到火炮作战效能的发挥。针对目前装备保障方式大多停留在维修层面而理论研究不够深入的实际,对节制环磨损故障的机理进行分析。以某型火炮短节制杆式制退复进机为对象,利用MATLAB数值计算平台,编程仿真节制环磨损故障对后坐的影响。同时探讨了故障后对火炮的处理方案。研究表明,节制环磨损对后坐诸元都将产生不同影响,针对影响的程度可制定相应的故障处理方案。仿真模拟和方案探讨对装备保障工作具有参考意义。     

基于SWOT分析的军队审计容错免责机制完善路径研究

军队审计容错免责机制是在审计权限范围内对符合容错免责情形的事由减轻或免于问责并及时纠正的稳定工作机制,是审计问责态势下应对“为官不为”问题的合理路径。本文基于SWOT法分析认为,当前审计环境下建立军队审计容错免责机制的优势在于独立的经济监督地位、专业的经济监督力量和广泛的经济监督对象,劣势在于单一的认定主体、缺失的法律规范和匮乏的免责素质,机遇在于利好政策的出台、国家审计的实践经验和军队审计的职能定位,威胁在于制度规范笼统、审计风险扩大和资源矛盾加剧。在此基础上,本研究基于W-T（劣势-威胁）的战略选择,提出完善军队审计容错免责机制的现实路径,即：明确机制定位,科学界定边界;完善制度规范,形成法律依据;完备容错清单,转变审计模式;优化容错环境,降低容错风险。     

Fracture mechanism of a cylindrical shell cut by circumferential detonation collision

The failure mechanism of a cylindrical shell cut into fragments by circumferential detonation collision was experimentally and numerically investigated. A self-designed detonation wave regulator was used to control the detonation and cut the shell. It was found that the self-designed regulator controlled the fragment shape. The macrostructure and micro-characteristics of fragments revealed that shear fracture was a prior mechanism, the shell fractured not only at the position of detonation collision, but the crack also penetrated the shell at the first contact position of the Chapmen-Jouguet (C-J) wave. The effects of groove number and outer layer thickness on the fracture behavior were tested by simulations. When the thickness of the outer layer was 5–18 mm, it has little effect on fragmentation of the shell, and shells all fractured at similar positions. The increase of the groove number reduced the fracture possibility of the first contact position of the C-J wave. When the groove number reached 7 with a 10 mm outer layer (1/4 model), the fracture only occurred at the position of detonation collision and the fragment width rebounded.     

Hypersonic impact flash characteristics of a long-rod projectile collision with a thin plate target

Impact flash occurs when objects collide at supersonic speeds and can be used for real-time damage assessment when weapons rely on kinetic energy to destroy targets.However,the mechanism of impact flash remains unclear.A series of impact flash experiments of flat-head long-rod projectiles impacting thin target plates were performed with a two-stage light gas gun.The impact flash spectra for 6061 aluminum at 1.3-3.2 km/s collision speeds were recorded with a high-speed camera,a photoelectric sensor,and a time-resolved spectrometer.The intensity of the impact flash exhibited a pulse charac-teristic with time.The intensity(I)increased with impact velocity(V0)according to I∝Vn0,where n = 4.41 for V0 ＞ 2 km/s.However,for V0 ＜ 2 km/s,n = 2.21,and the intense flash duration is an order of magnitude less than that of higher V0.When V0 ＞ 2 km/s,a continuous spectrum(thermal radiation background)was observed and increased in intensity with V0.However,for V0 ＜ 2 km/s,only atomic line spectra were detected.There was no aluminum spectral lines for V0 ＜ 2 km/s,which indicated that it had not been vaporized.The initial intense flash was emission from excited and ionized ambient gases near the impact surface,and had little relationship with shock temperature rise,indicating a new mechanism of impact flash.     

基于有限元-刚体混合模型的运载火箭缓释放特性分析

以一种新提出的新型强制式牵制释放系统为例,建立了分析运载火箭缓释放过程中缓释特性的有限元—刚体混合模型。采用刚体模型计算运载火箭的运动,利用有限元方法计算缓释销的弹塑性大变形接触过程,缓释机构和运载火箭的界面满足力和位移的协调条件。该混合模型采用增量方法进行求解,其可用来分析缓释机构的不同材料、几何形状、尺寸以及摩擦条件对运载火箭的完全释放时间、释放时刻速度以及缓释机构消耗功等参数的影响。     

外槽轮机构分度精度分析与设计

分析了外槽轮机构主要零部件的设计精度对槽轮分度精度的影响 ,结果表明主动件长度和滚子与轮槽之间的间隙对分度精度影响最大。用概率与数理统计的方法导出了精度设计公式并给出一个计算实例