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Journal Antennas №10 for 2016 г.
Article in number:
Simulation of the antenna system elements and AESA control system for the next generation radar. Experimental and simulation data comparison
Keywords:
active electrically steerable array
numerical simulation
radiator
control system algorithm
temperature instability
phase correction
amplitude correction
Authors:
P. L. Batov - Head of Special Design Bureau, Public JSC «Scientific-production association «Almaz» (Moscow). E-mail: skb.spo@gskb.ru
E. N. Gurkin - Head of Department, Public JSC «Scientific-production association «Almaz» (Moscow)
O. L. Dobrozhanskaya - Deputy Head of Special Design Bureau, Public JSC «Scientific-production association «Almaz» (Moscow)
N. V. Drozhina - Head of Department, Public JSC «Scientific-production association «Almaz» (Moscow)
A. E. Kozlova - Engineer, Public JSC «Scientific-production association «Almaz» (Moscow)
A. O. Manichev - PhD, Head of Department, Public JSC «Scientific-production association «Almaz» (Moscow), Scientific-technical center «Altair» (Moscow)
D. L. Borisevich - Deputy Head of Paseshifters Department, JSC «ZRTO» (St. Petersburg)
Abstract:
To provide required antenna performance during active electrically steerable array antenna (AESA) development one should design radiating antenna element and control system, which will be able to form necessary amplitude and phase distribution taking into account constructive and circuitry features of AESA equipment. So, at the first step of antenna system design the radiation pattern has been calculated when constructive elements of antenna array are taken into account. As a result an optimum geometry of radiating elements - placement has been selected. Throughout this work questions of radiator design and control system mathematic model creation are also considered in offered paper.
The control system model is intended for operational development and verification of real AESA amplitude and phase calculating software. This model takes into consideration active elements operational features, related with temperature and operating frequency deviations.
The experimental check of proposed algorithms has been carried out on the fragment of AESA. Experimental and simulation results are presented.
Pages: 44-50
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