计及分离的机翼低速气动特性的一种近似计算方法

本文介绍一种计算带分离的大中层弦比、小后掠角机翼低速气动特性的近似方法。根据给定机翼的平面形状和几何迎角,按线化升力面理论算出升力和力矩沿展向分布的第一次近似值。再逆向应用升力面理论估算下洗流场,从而近似地得到各个削面的有效迎角。然后根据有效迎角及雷诺数,从翼型实验数据得到相应的升力和力矩分布的第二次近似值。如此反复迭代直至收敛为止。     

Long term dynamics and optimal control of nano-satellite deorbit using a short electrodynamic tether

This paper studies the long term dynamics and optimal control of a nano-satellite deorbit by a short electrodynamic tether. The long term deorbit process is discretized into intervals and within each interval a two-phase optimal control law is proposed to achieve libration stability and fast deorbit simultaneously. The first-phase formulates an open-loop fast-deorbit control trajectory by a simplified model that assumes the slow-varying orbital elements of electrodynamic tethered system as constant and ignores perturbation forces other than the electrodynamic force. The second phase tracks the optimal trajectory derived in the first phase by a finite receding horizon control method while considering a full dynamic model of electrodynamic tether system. Both optimal control problems are solved by direct collocation method base on the Hermite–Simpson discretization schemes with coincident nodes. The resulting piecewise nonlinear programing problems in the sequential intervals reduces the problem size and improve the computational efficiency, which enable an on-orbit control application. Numerical results for deorbit control of a short electrodynamic tethered nano-satellite system in both equatorial and highly inclined orbits demonstrate the efficiency of the proposed control method. An optimal balance between the libration stability and a fast deorbit of satellite with minimum control efforts is achieved.     

卫星结构用PVC泡沫芯与铝蜂窝芯夹层板的比较

以卫星隔板为例,从原材料、工艺方法、力学性能、重量、生产周期及制造成本等方面比较了PVC泡沫芯夹层板和传统的铝蜂窝芯夹层板,总结出PVC泡沫芯夹层板的优势与劣势。最后,展望了PVC泡沫夹层结构在航天领域的应用前景。     

卫星信号缺失情况下GPS/SINS组合导航系统研究

针对GPS/SINS组合导航在复杂环境中出现的卫星信号不全情况,在分析SINS误差模型的基础上建立了组合导航的松组合和紧组合模型,采用无迹卡尔曼滤波对两种组合模式进行仿真实验.仿真结果显示,在卫星信号正常情况下,紧组合的导航精度高于松组合;在卫星信号缺失时,松组合转变为单纯的惯性导航,导航误差随时间积累,紧组合虽然误差增大,但在一定时间内仍能提供精确导航信息,提高了GPS/SINS组合导航适应复杂环境的能力.     

进口圆度仪智能化改造

以Talyrond73型圆度仪为例，介绍了圆度仪智能化改造的基本原理，圆度测量软件的主要功能以及回度误差评定方法的优化，探讨了保证检测精度的若干措施，并给出了检定结果。     

基于MDT的夹具CAD系统

简要介绍了基于MDT(Mechanica1 Desktop)的夹具CAD系统的功能、运行环境和应用范围.     

航天飞机热结构的辩证反思

挑战者号航天飞机失事的直接原因,是1986年1月28日肯尼迪航天中心的低温天气,使固体火箭助推器的氟橡胶密封圈失去弹性导致泄漏,挑战者号航天飞机发射升空73秒发生爆炸。哥伦比亚号航天飞机失事的直接原因,是升空过程中外贮箱脱落的绝热用聚氨酯泡     

近区场强仪自动校准测试的研究

介绍了近区场强仪的校准原理和方法，着重介绍了近区场强仪的自动校准测试系统和软件的研究。     

美国军用喷气燃料发展综述

以JP和RJ系列燃料为主线,系统地回顾了美国军用喷气燃料发展的历史与成就,着重论述了高密度燃料和吸热碳氢燃料两大军用燃料领域的关键技术,归纳了美国在这两大技术方面的研究历程和最新进展,对喷气燃料的发展前景和可能的研究方向作了展望。     

Development of a CELSS Experimental Facility

A CELSS Experimental Facility was developed two years ago. It contains a volume of about 40.0 m³ and a cultivating area of about 8.4 m²; its interior atmospheric parameters such as temperature, relative humidity, oxygen concentration, carbon dioxide concentration, total pressure, lighting intensity, photoperiod, water content in the growing-matrix, CO₂-added accumulative amount, O₂-released accumulative amount and ethylene concentration are all controlled and logged automatically and effectively; its growing system consists of two rows of racks along its left-and-right sides separately, each side holds two upper-and-lower layers, and the vertical distance of each growing bed can be adjusted automatically and independently; lighting sources consist of both red (95%) and blue (5%) light-emitting diodes (LED), and the average lighting intensity of each lamp bank at 20-cm distance position under it, reaches to 255.0 μmol m⁻² s⁻¹. After that, demonstrating tests were carried out and were finally followed by growing lettuce in the facility. The results showed that all subsystems operated well and all parameters were controlled automatically and efficiently. The lettuce plants in the system could grow much well. Successful development of this system laid a necessary foundation for future larger-scale studies on CELSS integration technique.