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In this paper, a standard cell radiation pattern is selected to accelerate the synthesis of a large-scale arrays pattern. The radiation patterns distortion of each cell in array is transformed to the additive perturbation in the array manifold matrix of the antenna array, and the weighted total least squares method is developed to solve this matrix problem. The examples of several antenna arrays are presented to verify the method. Benefiting from the direct solution of matrix with the standard cell's radiation pattern, the method is low in computation cost and fast in speed. [ABSTRACT FROM AUTHOR]

In this paper, a novel miniaturized circularly polarized (CP) antenna is proposed for the use in B3 band of Compass Navigation Satellite System (CNSS). The primary radiator is a hexagon patch with four bending strips. A shorting pin is loaded with each strip to miniaturize the dimension of the proposed antenna, which achieves a small electrical size of 0.11λ × 0.11λ × 0.068λ (λ being the wave-length in free space at 1.268 GHz). In order to improve the bandwidth, Y-shaped coupled patches and bending-strips, which act as reactive loading, are coupled to an octagon patch. Four coupled bending-stubs with same turning directions of bending-strips are sequentially placed at the edge of the octagon patch to enhance CP performance. Finally, a prototype of the antenna is implemented and measured. The experimental results reveal that the proposed antenna achieves impedance bandwidth (IBW) of 19.6% (1.175-1.430 GHz) for ∣S11 ∣ ≤ -10 dB and 3-dB axial-ratio bandwidths (ARBW) of 27.5% (1.000-1.320 GHz). The radiation efficiency is more than 75%, and the gain keeps above 1.98 dBic over the B3 band. Thus, the proposed antenna can be a good candidate for the applications of CNSS. [ABSTRACT FROM AUTHOR]

Due to the influence of aerodynamic forces, the wing will be subjected to vibration and deformation. This will result in a severe performance degradation of the wing conformal antenna. To solve this problem, a new gain-phase error compensation method based on the deformation fitting of wing conformal antenna is proposed. In this proposed method, the array deformed shape curve is fitted through the gain error of the array, thus the position of each element can be calculated. Finally, by using the position of the elements to calibrate the gain-phase error, the corrected directions of arrival (DOA) estimation angle is obtained. Simulation results show that the proposed method can well reproduce the shape of the array, and effectively compensate the position error caused by the vibration of the wing conformal antenna. [ABSTRACT FROM AUTHOR]