ID 原文 译文
11034 方案II在垂直维采用rank自适应,水平维支持rank 1传输。 Scheme II in vertical dimension using rank adaptive, horizontal transmission support rank 1.
11035 在三维城市宏小区和三维城市微小区场景下,采用系统级仿真验证了两种方案的性能。 In three-dimensional urban macro community and 3 d scenario, small area of city by system level simulation verify the performance of the two plans.
11036 相较于水平维和垂直维都仅支持rank 1的传输方案,两种方案都取得了性能增益,同时方案I优于方案II。 Compared with horizontal and vertical dimensions are only supported rank 1 transmission scheme, two kinds of solutions are obtained the performance gain, plan I better than II at the same time.
11037 采用基于矩量法(method of moments,MoM)的面-线积分方程法分析了同轴线馈电的球面共形微带天线的输入阻抗。 Based on the method of moments (MoM) method of moments, the interface - the line integral equation method to analyze the coaxial feed input impedance of the spherical conformal microstrip antennas.
11038 面-线积分法在分析过程中具有未知量少,计算时间短的优势。 ‭Interface - the line integral method in the process of analysis has an unknown quantity is little, the advantages of short computing time.
11039 天线贴片电流和探针电流分别采用Rao-Wilton-Glisson(RWG)基函数与三角基函数来模拟。 ‭Patch antenna and the probe current respectively by Rao - became - Glisson, RWG basis function and triangular basis function to simulate.
11040 在线面连接处,提出一种新型的连接基函数以保证探针与贴片的电流连续性。 ‭Online surface joint, put forward a new kind of connection basis function to ensure the current continuity of probe and patch.
11041 激励源采用磁流环模型,并且结合球表面磁并矢格林函数求解激励源在天线表面产生的场。 ‭Incentive source USES the magnetic flow loop model, and combined with the ball surface magnetic excitation and the solution is green's function in the field of antenna surface.
11042 最后,通过实例验证了连接基函数的可行性,并分析了两副球面共形微带天线的输入阻抗,证明所提分析处理的正确性。 ‭Finally, an example proves the feasibility of the connection basis function, and analyzes the two pairs of spherical conformal microstrip antenna input impedance, prove the correctness of the proposed analytical processing. ‭
11043 研究了伸缩翼飞机变形飞行过程的动力学建模与鲁棒控制问题,以分析机翼变形对飞机性能的影响机理,并实现机翼变形时的平稳飞行。 Studied the expansion deformation of wing aircraft flight dynamics modeling and robust control problems, to analyze deformation mechanism of effect on the performance of aircraft wing, and realize smooth deformation when the wing of the flight.