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21.
为了解决结构型吸波材料的分析和设计中所遇到的反射系数计算问题,从电磁场理论出发,导出了电磁波以任意角入射时多层雷达吸波材料(RAM)涂层的反射系数公式,此法简单易行,为结构型吸波材料的计算机辅助分析和设计提供了基础,同时给出了计算曲线的例子,通过实例计算分析了电磁波的入射角,极化状态等对反射特性和隐身效果的影响。 相似文献
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The primary objective of the Laser Interferometer Space Antenna (LISA) mission is to detect and observe gravitational waves from massive black holes and galactic binaries in the frequency range 10−4 to 10−1 Hz. This low-frequency range is inaccessible to ground-based interferometers because of the unshieldable background of local gravitational noise and because ground-based interferometers are limited in length to a few km. LISA is an ESA cornerstone mission and recently had a system study (Ref. 1) carried out by a consortium led by Astrium, which confirmed the basic configuration for the payload with only minor changes, and provided detailed concepts for the spacecraft and mission design. The study confirmed the need for a drag-free technology demonstration mission to develop the inertial sensors for LISA, before embarking on the build of the flight sensors. With a technology demonstration flight in 2005, it would be possible to carry out LISA as a joint ESA-NASA mission with a launch by 2010 subject to the funding programmatics. The baseline for LISA is three disc-like spacecraft each of which consist of a science module which carries the laser interferometer payload (two in each science module) and a propulsion module containing an ion drive and the hydrazine thrusters of the AOCS. The propulsion module is used for the transfer from earth escape trajectory provided by the Delta II launch to the operational orbit. Once there the propulsion module is jettisoned to reduce disturbances on the payload. Detailed analysis of thermal and gravitational disturbances, a model of the drag-free control and of the interferometer operation confirm that the strain sensitivity of the interferometer will be achieved. 相似文献
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研究了过渡流域三维热化学非平衡流动DSMC方法实现的过程.以四面体非结构网格为基本单元,提出一种新型的高效搜索算法,该算法不仅可以快速跟踪模拟分子在网格之间的迁移,而且可以准确判别分子与物面是否相互作用,避免了原有算法中分子表面反射的非确定论判据.设计了适合三维DSMC方法的动态局部时间步长技术,节约了计算时间.将碰撞距离的思想引入到非结构网格上来,有效地消除了网格尺度小于三分之一平均自由程的限制.利用Foaran90的动态分配内存技术编制了适用于任意外形的通用计算程序.最后对全尺寸航天飞机高超声速绕流进行了数值试验,计算结果验证了该算法的可行性及高效性. 相似文献
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针对固体火箭发动机药柱存在裂纹的情况,对运动激波在狭缝中绕射传播的非定常流场进行了计算,得到了清晰的流场变化图谱,从流场图中可分辨出激波在狭缝中的传播过程。对不同深宽比的狭缝进行研究,发现流场结构存在明显差别,在深宽比较小时狭缝内压力波振荡较小,当深宽比超过一定值时狭缝内的压力波产生剧烈振荡。研究结果表明,该方法可很好地描述激波在狭缝中的传播过程。 相似文献
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基于RBF网络的惯导系统初始对准 总被引:18,自引:2,他引:18
建立了惯导系统(INS)初始对准的线性和非线性误差模型。分析了径向基函数(RBF)网络的结构和工作原理。研究了RBF网代替初始对准中的卡尔曼滤波器的实现方法。通过仿真表明,用神经网络进行初始对准,既可获得与卡尔曼滤波相同的对准精度,又提高了系统的实时性。 相似文献
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Major X-33 flight hardware has been delivered, and assembly of the vehicle is well underway in anticipation of its flight test program commencing in the summer of 1999. Attention has now turned to the operational VentureStarTM, the first single-stage-to-orbit (SSTO) reusable launch vehicle. Activities are grouped under two broad categories: (1) vehicle development and (2) market/business planning, each of which is discussed. The mission concept is presented for direct payload delivery to the International Space Station and to low Earth orbit, as well as payload delivery with an upper stage to Geosynchronous Transfer Orbit (GTO) and other high energy orbits. System requirements include flight segment and ground segment. Vehicle system sizing and design status is provided including the application of X-33 traceability and lessons learned. Technology applications to the VentureStarTM are described including the structure, propellant tanks, thermal protection system, aerodynamics, subsystems, payload bay and propulsion. Developing a market driven low cost launch services system for the 21st Century requires traditional and non-traditional ways of being able to forecast the evolution of the potential market. The challenge is balancing both the technical and financial assumptions of the market. This involves the need to provide a capability to meet market segments that in some cases are very speculative, while at the same time providing the financial community with a credible revenue stream. Furthermore, the market derived requirements need to be assessed so as not to impose unnecessary requirements on the vehicle design that add unreasonable cost to the development of the system, yet provides the right capabilities for new markets that could be triggered by dramatically lower space transportation prices. 相似文献