The experience of JSC “Russian Space Systems” in the development of on-board equipment for command radio links of spacecraft for various purposes with a given level of radiation resistance under conditions of long-term exposure to ionizing radiation of outer space for the period from 2003 to 2021 is summarized. The main stages of work to ensure the resistance of onboard equipment to integral dose effects and the effects of single events are considered. Methodological and software resources have been developed that allow correct prediction of local dose loads of ionizing radiation from outer space in the on-board equipment of command radio links, taking into account the effect of “dose amplification” of secondary bremsstrahlung. The methodological issues of ensuring the terms of the active existence of the onboard equipment are considered, using the cold redundancy of critical devices and components. The use of cold redundancy makes it possible to increase the duration of active existence relative to resistance to integral dose effects by about 1.5 times. The effectiveness of the developed methodological and software resources for confirming the radiation resistance of the onboard equipment of command radio links is proved by successful operation of about 100 spacecraft for various purposes in the 2005–2021 period.
The paper presents an approach to the synthesis of a transceiving feed for axisymmetric double reflector antennas based on the aperture separation of C- and Ka-band signals of coaxial and circular waveguides with a maximum separation of the extreme bands of 10 : 1. The development and selection of a coaxial feed design for constructing a feed system of the transceiving reflector antenna was carried out. Optimal parameters of the coaxial feed were determined and experimentally proved to provide a feed angle level of the subreflector of 30◦ and a VSWR of 1.25 for the C- and Ka-band outputs in the receiving channels and 1.15 and 1.3 for the C- and Ka-band transmission channels, respectively, with the bandwidth of Сreception — 21 %, Сtransmission — 18.2 %, Каreception — 8.6 %, Каtransmission — 7.8 %. The results of practical implementation are presented.
Creating an integrated system of orientation and navigation of small spacecraft based on precision sensors of inertial and external information is an urgent task for the space industry. The object of research is a micromechanical gyroscope (MMG) with a gimbal suspension of a sensitive element. The problem of increasing the accuracy of the MMG by building a new mathematical model of the sensor accurate enough to take into account the influence of technological errors of manufacturing and nonlinear nonstationary effects associated with finite oscillations of a sensitive element and slow change in system parameters. To build a digital model of the micromechanical inertial information sensor, parametric design systems have been applied enabling a full cycle of design documentation creation and calculations. The parametric calculations of the structural scheme were used to analyze the stress-strain state of mechanical elements under various external influences including extreme overloads. The obtained mathematical model was supplemented by analytical methods of nonlinear mechanics, which allow taking into account the influence of finite vibrations of structural elements on the dynamics and accuracy of measurements of angular motion of the gyroscope base. The results of bench experimental tests of sensors carried out to check the adequacy of the developed numerical mathematical model are discussed.
In the article, arrays of two and three microstrip emitters of elliptical polarization are studied by the methods of electrodynamic analysis. Formulas are obtained for determining the corrections to the amplitudes and phases of the array elements, which ensure the presence of dips in the resulting radiation pattern. The dependence of the width of the dip near zero of the radiation pattern on the number of elements in the array, its pitch, and design has been studied. It is shown that at a fixed dip depth exceeding minus 100 dB, its width slightly depends on the array type and dip orientation in the upper or lower hemisphere of the diagram. At the same time, at different depths of the dip, its width can vary significantly and depends on the accuracy of compliance with the amplitude-phase relationships that provide zeros of the radiation pattern.
This article presents a brief description of the life of one of our legendary contemporaries, who sat at the control panel of the device that communicated between two great people who initiated the era of cosmonautics, S. P. Korolyov and Yu. A. Gagarin, during the first manned flight into space. L. I. Gusev was the liaison between the General Designer and the first cosmonaut of the Earth during this epoch-making event. Today it is already obvious to everyone that without its complexes of radio engineering, telemetric and trajectory measurements, it would be impossible to explore outer space. Enterprises and organizations led by L. I. Gusev, took an active part in all key events in the Russian space industry — from the launch of the First artificial Earth satellite to the development, creation and operation of modern space complexes and systems in all areas of space activity.
