Conceptual design of a bioregenerative life support system containing crops and silkworms

This article summarizes a conceptual design of a bioregenerative life support system for permanent lunar base or planetary exploration. The system consists of seven compartments – higher plants cultivation, animal rearing, human habitation, water recovery, waste treatment, atmosphere management, and storages. Fifteen kinds of crops, such as wheat, rice, soybean, lettuce, and mulberry, were selected as main life support contributors to provide the crew with air, water, and vegetable food. Silkworms fed by crop leaves were designated to produce partial animal nutrition for the crew. Various physical-chemical and biological methods were combined to reclaim wastewater and solid waste. Condensate collected from atmosphere was recycled into potable water through granular activated carbon adsorption, iodine sterilization, and trace element supplementation. All grey water was also purified though multifiltration and ultraviolet sterilization. Plant residue, human excrement, silkworm feces, etc. were decomposed into inorganic substances which were finally absorbed by higher plants. Some meat, ingredients, as well as nitrogen fertilizer were prestored and resupplied periodically. Meanwhile, the same amount and chemical composition of organic waste was dumped to maintain the steady state of the system. A nutritional balanced diet was developed by means of the linear programming method. It could provide 2721 kcal of energy, 375.5 g of carbohydrate, 99.47 g of protein, and 91.19 g of fat per capita per day. Silkworm powder covered 12.54% of total animal protein intakes. The balance of material flows between compartments was described by the system of stoichiometric equations. Basic life support requirements for crews including oxygen, food, potable and hygiene water summed up to 29.68 kg per capita per day. The coefficient of system material closure reached 99.40%.     

PARAMETRIC MODELING OF COMPONENT LIBRARY FOR LANDING GEAR BASED ON CATIA/CAA

The design of landing gear is complicated due to the numerous considered elements.And the initial elements related to each other can also be influenced by different factors.Landing gear design often involves a very large variety of configurations,especially in the conceptual design phase.However,traditional method costs more time to complete the whole procedure for suitable configurations of landing gears.Therefore,the parametric modeling of component library for landing gear based on computer aided three-dimensional interface application/component application architecutre(CATIA/CAA)is proposed.According to the analysis of the characteristics of landing gear components,a method is presented to extract the primary parameters of landing gear components so that a systematic classification can be established.Further,the related theories and methods,including receiving geometrical parameters of the components and updating the parametrical model,displaying the component parts,are also illustrated.Finally,the development technology for component library is explained.The proposed modeling method can improve the efficiency of the whole design cycle for landing gear.     

高负荷跨音压气机转子ATS-3气动设计

ATS-3的设计工作是在已有的设计较为成功的风扇压气机 ATS-2的基础上 ,进行细致的优化 ,主要是想提高失速裕度 ,也为高负荷、高压比跨声速压气机的设计提供更为直接、有用的设计数据。优化设计的重点是在根部应用可控扩散叶型的思想进行二维反问题优化、并对整体的安装角进行调整。其特性的数值模拟结果表明 ATS-3较 ATS-2有更大的失速域度 ,效率有所提高 ,但设计点的压比和流量略微有所降低     

发动机孔探图像三维测量与立体重建的实现

作为一种新兴的可视探测技术，孔探成像分析在现代发动机故障诊断中一直发挥着重要的作用。研制和开发基于孔探图像的三维测量与立体重建系统对提高故障诊断水平和预测准确度，降低工作中的人力物力投入，节约维护成本都有着重要的现实意义。本文以整体系统的构架为线索，阐述了系统的图像采集，摄像机标定，图像预处理，立体匹配，3D计算以及深度重建等功能模块的研制思路和基本算法，并给出部分研制结果。本系统的开发为基于也探图像的发动机故障监测与诊断系统的奠定了重要的基础。     

用纤内Bragg光栅进行动态应变测量的研究

描述了用纤内Bragg光栅进行动态应变测量研究的意义，原理和方法，提出了两种用纤内Bragg光栅动态应变测量时进行Bragg波长偏移量的解调方法；光干涉相位检测Bragg光栅反射波长偏移的解调方法和用DWDM密集波分复用器解调Bragg波长的方法，前者适用于高频宽带动态应变测量，后者适用于有限频率或中等频率响应的动态应变测量。     

Parylene真空涂覆新工艺研究

简述了Parylene真空沉积的机理,并对采用Parylene真空涂覆的涂层样件进行了全面的性能摸底试验。     

运输机总体参数和性能统计分析

 按照飞机设计的基本原理,通过对现有运输机总体参数和性能数据的统计分析,寻找现代运输机各个总体性能和性能参数之间存在的定量关系,得到了 1 6个经验公式和一些参数取值范围,为运输机概念设计提供了一些可用的数据。     

梯度热障涂层的设计

 采用电子束物理气相沉积方法 (EB PVD)制备了梯度热障涂层,其结构设计为NiCoCrAlY粘结层 /Al₂O₃ YSZ过渡层 /YSZ陶瓷层。YSZ陶瓷层的结构为柱状晶结构,Al₂O₃ YSZ梯度过渡层为梯度微孔结构。采用有限元方法对梯度热障涂层进行热应力分析,优化了Al₂O₃ YSZ梯度过渡层的组成。计算结果表明,梯度涂层的内应力显著降低,而且界面及其附近应力和应变变化较平缓。过渡层厚度的增加有利于降低涂层内应力和缓和涂层界面处的应力集中。     

大迎角下鸭翼涡与边条涡的干扰特性

 在风洞测力、水洞染色线和激光片光实验的基础上 ,对翼身组合体鸭翼边条翼布局大迎角涡系干扰机理进行了分析和探讨 ,揭示了该布局增升的机理。鸭翼涡位于机翼内侧 ,其与边条涡的相互诱导致使边条涡向外翼偏折 ,既改善了外翼的流态 ,又使机翼前缘涡量卷入边条涡 ,增强了边条涡的强度 ,从而延迟其破裂。两方面的共同作用 ,提高了主翼的涡升力 ,起到增升作用。     

SACMA和QMW试验方法对复合材料层合板低速冲击后压缩行为的影响

采用了 SACMA标准和一种小试样试验方法对复合材料层合板低速冲击后的压缩 (CAI)行为进行试验研究 ,从层合板的冲击损伤分布、冲击后压缩破坏过程 ,以及层合板的准静态横向压缩、开孔后压缩等多方面进行对比 ,结果表明 ,这两种试验方法存在很大差别 ,试验方法不同 ,层合板低速冲击后的压缩行为也不同 ;采用 SACMA标准所测得的低速冲击后压缩强度更能全面反映基体韧性的优劣。作为 CAI试验标准 ,小试样试验方法还有待改进