微重力环境下硅基纳米器件碰撞滑动接触问题研究

随着纳米技术的发展,微机电系统被广泛应用于微纳卫星、皮卫星以及各种高精密仪器. 单晶硅广泛应用于微机电系统,考虑微重力环境空间机构无规则碰撞的运动特性,建立刚性金刚石压头与弹性硅基体之间碰撞滑动接触的分子动力学模型,对比研究压头不同振动频率和振幅对平均摩擦力的影响. 结果表明:压头振动频率低于基体固有频率时,平均摩擦力无明显变化,而高于固有频率时,平均摩擦力随振动频率增大呈现先减小后不变的趋势;振幅的增大导致压头和基体的碰撞更加剧烈,剧烈的碰撞导致基体表面更多原子晶格结构破坏,失效原子数增多,降低了平均摩擦力;在基体表面引入纹理,发现纹理表面能够有效降低平均摩擦力.      

Numerical simulation of control ablation by transpiration cooling

A transient, one-dimensional numerical model is developed to describe the processes of transpiration cooling and ablation of the porous matrix used for the cooling. This model is based on the assumption of local thermal equilibrium. The problem of moving boundary due to ablation of the porous matrix is treated by the front-fixing method. This paper discusses the results of numerical simulations under different conditions and control parameters of ablation process. It was found that cooling effects and ablation processes are influenced by the coolant mass flow rate, the intensity of the heat flux, and the initial temperature at the start of transpiration cooling. In additional to the above three parameters, the Stefan number and the Biot number can also influence the transient cooling process, control ablative thickness of the porous plate by the reduction of ablative speed and duration, respectively.     

运载火箭结构动特性分析工具的设计与实现

运载火箭的结构模型复杂,只有通过开发专用的仿真分析软件,才能高效、便捷的对其开展动力学特性分析。为保证工具建设的实用性,该软件基于航天领域应用广泛的Patran/Nastran软件进行二次开发。针对仿真分析流程,设计实现了运载火箭结构动特性分析工具,涵盖了建模与计算模块、结果后处理模块、模态筛选模块与模型修正模块,并提炼了其中的关键技术。经工程实践表明,工具可提升设计效率,且计算结果准确、通用性与扩展性强,在工程中具备良好的应用价值。     

Synthesis and characterization of a novel arylacetylene oligomer containing POSS units in main chains

A novel arylacetylene oligomer containing octamethyl POSS units in main chains was prepared from difluoride octamethyl POSS (diexo-(CH₃)₈Si₈O₁₁F₂) and diethynylbenzene (DEB) by Grignard reaction and characterized by FT-IR, NMR, WAXD, GPC, DSC, and TGA. The curing reaction kinetic of the oligomer was studied by Kissinger and Ozawa methods and the kinetic parameters were obtained. The cured polymer had good thermal and thermal-oxidative properties. TGA analyses demonstrated that the thermal decomposition temperature (T_d5) of the cured polymer in nitrogen and air were 503 and 479 °C, respectively.     

复杂系统的舱体屏蔽效能的评价方法

舱体屏蔽效能的试验评价是验证车载复杂系统抗电磁脉冲加固性能的重要环节。为了定量估计试验设计和结果评定所引入的不确定度,以高空电磁脉冲为背景,分别从频域/时域测试方法选择、测试频点设置、合格曲线设计和超差点的处理等几个要素,研究了舱体电磁脉冲屏蔽效能的验证评价方法。针对车载复杂系统典型舱体屏蔽效能较低的特点,针对不同屏蔽效能提出了一簇合格曲线,并基于二阶谐振系统模型,定量估计了频点设置准则、合格曲线、超差点处理准则所引入的不确定度,为舱体屏蔽效能的试验设计与数据分析提供了方法与支撑,同时定量分析也可作为不确定度估计的基础。     

星敏感器技术研究现状及发展趋势

本文综述了星敏感器技术的研究现状和未来发展趋势。首先,总结了国内外星载星敏感器的发展历程。接着,根据星敏感器工作原理,分析讨论了星点质心定位算法、星图识别算法和姿态解算算法等星敏感器关键技术的发展现状。通过讨论星点质心定位精度对星敏感器测量精度影响,分析了星点质心定位算法以及对应误差补偿的研究现状;基于星座特征、字符模式和智能行为,介绍了星图识别算法并进行了对比分析;根据确定姿态解算算法和动态姿态解算算法分析了姿态解算算法的研究现状。最后,对星敏感器的未来发展进行了展望,讨论了航空机载星敏感器、微小型星敏感器和甚高精度星敏感器的发展趋势以及未来重点研究内容。     

Influence of turbulence model parameter settings on conjugate heat transfer simulation

Rationality of the parameter settings in turbulence model is an important factor affecting the accuracy of conjugate heat transfer (CHT) prediction. On the basis of a developed CHT methodology and the experimental data of Mark// cooling turbine blade, influences of the turbulence model parameter settings and the selection of turbulence models on CHT simulation are investigated. Results and comparisons with experimental data indicate that the inlet setting of the $\tilde{v}$ in Spalart–Allmaras model has nearly no influence on flow and heat transfer in blade surface. The inlet turbulence length scale l _T in the low-Reynolds number Chien k-ε turbulence model and the blade surface roughness in shear stress transport (SST) k-ω SST model have relatively obvious effects on the blade surface temperature which increases with the increase of them. Both of the laminar Prandtl number and turbulent Prandtl number have slight influences on the prediction, and they only need to be constant in CHT simulation. The k-ω SST model has the best accuracy in the turbine blade CHT simulation compared with the other two models.     

双圆柱气囊缓冲性能分析

基于有限元法和控制体积法,建立了双圆柱气囊缓冲系统的有限元模型。以着陆速度为6.7m/s,高为2m,直径为1m的圆柱形气囊为例,利用LS-DYNA软件计算气囊缓冲过程中空投设备的速度和加速度,并对影响气囊缓冲性能的织物弹性模量、排气孔开口面积以及气囊初始内压进行了分析。结果表明:(1)当气囊织物的弹性模量E≤0.5GPa时,增大弹性模量可以显著提高气囊的缓冲性能;当气囊织物的弹性模量E0.5GPa时,增大弹性模量对气囊缓冲性能的影响很小。(2)在不超过排气阀门值的范围内,增大气囊的初始内压可以有效地提高气囊的缓冲性能。     

Oldroyd-B黏弹性液滴碰撞过程的数值模拟

复杂的流变特性使凝胶推进剂的雾化过程存在一定困难,这制约了它的发展.聚合物胶凝剂的加入使凝胶推进剂具有黏弹性,从而在雾化时会产生黏弹性液滴,因此为了进一步认识凝胶推进剂的雾化机理、提高凝胶推进剂的雾化性能,对黏弹性液滴的碰撞行为进行数值模拟研究.针对凝胶推进剂雾化过程中出现的液滴撞击现象,考虑流体具有的黏弹性效应,采用...     

利用卡尔曼滤波和参数自调整控制器提高飞行仿真转台性能

为了提高惯性器件仿真的真实性,飞行仿真转台被广泛应用于半实物仿真系统.但是飞行仿真转台的响应误差、响应滞后、非线性等特性影响了整个半实物仿真系统的性能.采用卡尔曼滤波器对转台的状态进行估计,并设计了带有前馈的闭环控制器,减小了飞行仿真转台的低频相位滞后.通过对转动轴上的转动惯量进行辨识,控制器的参数可以自动调整来减小负载惯量变化对系统的影响,同时控制器对系统的力矩扰动进行了补偿.经过试验验证,转台小信号运行时的失真度残小为原来的1/5,动态仿真性能也有显著提高.