Onboard Radio-electronic Equipment Research Articles

Criteria for Evaluating the Processes of Designing Onboard Radio-Electronic Equipment of Space Vehicles

The authors of the article conducted an analysis of approaches, methods, and criteria for evaluating the design processes of onboard radio-electronic equipment. In particular, the key criteria influencing the enhancement of efficiency in designing onboard radio-electronic equipment processes were examined, along with ways to improve them when addressing business process reengineering tasks in design organizations. Based on the analysis conducted and the authors experience in the field of engineering business processes for designing onboard radio-electronic equipment for spacecraft, fourteen groups of quality assessment criteria for business processes were developed. The developed criteria were tested in evaluating the performance of reengineering business processes in the instrumentation department of the Information Satellite Systems named after M. F. Reshetnev Joint-Stock Company. However, due to the vast amount of material obtained during the research and design work conducted, the authors of the article have provided only examples of the development and coordination of the technical specification for the design of onboard radio-electronic equipment for spacecraft as indicative results. The results of the testing showed the effectiveness of the developed criteria for evaluating the design processes of onboard radio-electronic equipment for spacecraft, substantiating the potential for innovation implementation.

A synergetic approach to the development of the economic potential of the aviation complex enterprises

The potential of aviation enterprises makes it possible to increase the volume of development and production of aviation equipment, in particular: regional passenger and transport aircraft; aircraft engines and units; on-board radio-electronic equipment aimed at the use of satellite communication, navigation and observation systems; helicopters and general aviation aircraft, including unmanned ones; military goods and dual-use products. It is substantiated that the harmonization of the modern system of state regulation of the integration of the foreign trade sector of Ukraine into the EU should be carried out based on the fact that the parties have excellent reasons for forming an integration association. The consistent implementation of worldview and methodological procedures for maximizing the use of potential is, first of all, a tool for overcoming the low level of economic development, efforts through unification to create better conditions for the industrialization and development of aviation enterprises, the possibility of qualitative transformation of the foreign trade sector by attracting foreign investments and high technologies. This approach should contribute to the fundamental restructuring and diversification of export supplies, increase the opportunities to use positive development trends, and increase the level of international competitiveness of domestic economic entities. The results of the diagnostics of aviation enterprises made it possible to reveal the expediency of forming a new structure of interaction of enterprises and systematizing them into an aviation complex, which is considered as a set of organizations involved in the development, testing, production, sale, operation, modernization and repair of aviation equipment, which form several interconnected clusters.

METHOD OF CALCULATING THE UNSTATIONARY TEMPERATURE FIELD PARTS OF THE SPHERICAL FORM OF THE STRUCTURE FLIGHT APPARATUS OF UNMANNED AVIATION COMPLEXES

The design of unmanned aircraft vehicles during operation is exposed to significant temperature effects, which causes changes in the dielectric characteristics of radio technical elements and can lead to failures of on-board radio electronic equipment, as a result of which the task of determining the amount of temperature change in the compartments where the radio electronic equipment is located is performed. At the same time, some external elements of the aircraft vehicle can have complex structures with shapes close to spherical and different thicknesses in each cross-sectional structure.
 There is a need to develop a method for calculating the non-stationary temperature field with the purpose of finding out the real conditions in which all the elements of the aircraft structure work, which would help to determine how the temperature of the structure changes during any flight. At the same time, it is necessary to take into account the three dimensions of temperature gradients on spherical parts of structures of various shapes, namely nose part, rounded wing and others. In them, as a rule, each cross-section of the wall has its own thickness and, according to each cross-section, the temperature distribution along the thickness of the wall will correspond, that is, it is necessary to ensure the redistribution of temperature along the structural element, the calculation of which month. In addition, it is necessary to note that the wall of the aircraft can be multi-layered and the properties of its material can change along with the change in temperature. Considering the fact that it is impossible to take into account all the listed features by analytical methods, when choosing a calculation method, it will be advisable to stop at numerical methods.
 One of the most well-known numerical methods is the finite difference method with an implicit calculation scheme, which has an indisputable advantage for modeling - absolute stability with sufficient changes in time and coordinate steps. We will use the level of thermal conductivity in spherical coordinates in order to increase the accuracy of the calculation, for which solution, after finding out the boundary conditions, we will perform a one-dimensional calculation of the temperature by thickness in each mesh section of the structure, and also perform a calculation of the two-dimensional "heat flow" along the solid between the points, that are located on the same thickness, but have a temperature difference. Thus, when calculating the temperature field, the sphericity and multi-lay redness of the structural elements is taken into account, and the property of the material of the aircraft structure changes depending on the temperature.

DESIGN AND TECHNOLOGY SYSTEM FOR DEVELOPMENT AND OPERATION OF ULTRALIGHT SUBORBITAL ROCKET COMPLEXES

Abstract. Vehicles are called suborbital if they either move along a ballistic trajectory with a flight velocity sufficient to reach altitudes of up to 100 km or more, but insufficient for becoming an orbiter, or fly to altitudes of 100 km or more strictly vertically, but do not become artificial satellites of the planet, even if they reach sufficient velocity at some point. In both the first and second cases, this will be considered a space flight if its height exceeds 100 km (the Kármán line). Despite the active development of the suborbital rocket science in the world as a means of solving many scientific and technical problems in the space and defense industries, scientific research and engineering education, the development of suborbital rocket science in Ukraine has so far remained, at best, at the level of achievements of the 1960s and 1970s and has been supported by numerous amateurs. This article presents the results of the creation and development of a design and technological system for the development and operation of ultralight suborbital rocket systems as the basis for the creation of new models of domestic space rocket systems, rocket and missile weapons systems, the development of innovative technologies in the field of rocket science in general, practical training of highly qualified specialists for the space industry. This paper presents structural and layout diagrams of the developed suborbital rockets, design and technological solutions for the creation of on-board radio-electronic equipment and rocket engines, design modeling, bench and flight tests. The presented design and technological system is already used today at Oles Honchar Dnipro National University for comprehensive practical training of specialists in the field of creation and operation of rocket technology and missile and rocket weapons.

Разработка устройства защиты от сверхкоротких импульсов для цепей электропитания бортовой радиоэлектронной аппаратуры

Correct and uninterrupted operation of on-board radio-electronic equipment (REE) operating in extreme space conditions is an important requirement in spacecraft (SC) development and operation, since its violation can cause irreparable damage. Ensuring interference immunity of power supply bus (PSB) of on-board REE of SC. When designing the PSB, the task of ensuring the integrity of the power supply was solved by developing a protection device against conductive interference, including protection against ultra-short pulses (USP). The duration of such interference is in the nanosecond and subnanosecond range. Due to their wide range, such interference overcomes traditional means of protection. To protect against USP, devices called modal filters (MF) have been proposed. MFs are designed to be integrated into PSBs and provide effective protection against USP. Meanwhile, in order to obtain a complex protection effect of a spacecraft against radiated and conductive large-amplitude USP, a joint use of MF and an electromagnetic interference (EMI) filter on elements with concentrated parameters is proposed. For the first time, recommendations on step-by-step development of an PSB protection device against USP, which is a hybrid consisting of MF and EMI-filter, are presented. Experimental studies have shown that such a hybrid attenuates common and differential interference in the frequency range up to 5 GHz by 5.81 and 11.9 times, respectively. In addition, the device is small and lightweight, which is important for space applications.

Estimation and analysis of the influence of ionizing radiation on the operation of nanosatellite onboard radio electronic equipment

The paper presents the results of a calculation aimed to study the influence of ionizing, bremsstrahlung radiation on the operation of a nanosatellite obtained during the implementation of the project 0777-2020-0018 in 2020. A comparative analysis of the results of calculating the specific ionization and radiation energy losses of protons (from 0.1 to 400 MeV) and electrons (from 0.04 to 7 MeV), as well as their path lengths in aluminum according to the formulas of various authors and the database of materials of the National Institute of Standards and Technologies is presented. Based on the analysis results, the annual dose in the aluminum structure of the SamSat ION nanosatellite in a circular sun-synchronous orbit (SSO) is calculated. All calculations are based on the data of the energy spectra of protons and electrons of the SSO given in the Information system Spenvis of the European Space Agency. The results of calculating the integral fluxes in aluminum under the action of protons and electrons of a circular SSO for different thicknesses are obtained, and the fraction of passed particles is shown in the approximation of a single-layer stack. The radiation resistance of the electronic elements ISL70321SEH, ISL73321SEH and Virtex-4QV, Virtex-5QV included in the SamSat ION avionics and its ability to operate during a year was assessed.

METHOD FOR CONTROL OF TECHNICAL STATE OF ONBOARD RADIOELECTRONIC EQUIPMENT OF SPACECRAFTS BASED ON INTERACTION OF ELEMENTS OF DISTRIBUTED TECHNICAL DIAGNOSIS SYSTEM

The article deals with the issues of technical diagnostics of on-board radioelectronic equipment of spacecrafts. A mathematical formulation of the problem is carried out in order to minimize the time of technical diagnostics. A method has been developed for monitoring the technical state of onboard radioelectronic equipment based on the interaction of elements of a distributed technical diagnostics system, which includes identification of onboard radioelectronic equipment and training a neural network, searching for the location and causes of a malfunction using a mathematical model and making decisions by controlling the onboard radioelectronic equipment of spacecrafts. When searching for the location and causes of a malfunction, an interesting approach is based on a neural network classification of malfunctions. Practical recommendations for technical diagnostics of onboard radioelectronic equipment of spacecrafts are presented, in particular, a scheme for constructing a promising onboard distributed system of technical diagnostics when interacting with onboard systems of a typical spacecraft.

Algorithm for conducting autonomous tests of radio electronic means

Due to the increasing complexity of radio electronic equipment, the problem of its reliability becomes much more acute. At the same time, the task of evaluating on-board equipment at the design and production stages becomes very urgent. An important issue is also the reliable determination of numerical values of its reliability indicators. Ground-based experimental testing of samples of on-board radio-electronic facilities, devices, assemblies and units facilitates the solution of this problem. Inthe course of this testing, various tests conducted. It been shown that the timeliest information about the quality and reliability of the equipment can be obtained from autonomous tests. In the article, the choice of an autonomous test facility has made. Amicroprocessor-based temperature controller chosen as an autonomous test object. The expert evaluation method used to select the object. Analysis of specifications carried out. The scope of autonomous tests was determined. An algorithm for autonomous testing of on-board radio electronic equipment of spacecraft was developed. It has properties of discreteness, determinacy, limb and mass. The development of the autonomous test algorithm takes more account of the specifics of the technology used to manufacture the product under test and the test sequence. One of the options for mathematical modelling of the process of selecting test equipment for autonomous tests been considered.

Knowledge representation model for intelligent power supply control system of special purpose control machines

The problem of automating the process of reconfiguring the power supply system of onboard radio-electronic equipment in special-purpose control machines in different operation modes is considered. It covers power supply from different power sources, both while parked and when moving by developing and introducing the intellectual management to the structure of an electric power supply system. The analysis of the existing devices used to provide mobile objects with electrical energy of a direct current is carried out. Their advantages and drawbacks are highlighted. The conclusion is drawn on the necessity of new product development – the P910 power supply control panel with an integrated intellectual power supply management system. The model of representation of knowledge of the intellectual management system offered by authors is based on the classic productional model specified regarding the mechanism of forming and creating the database and rule base structures. The process of synthesizing managing influences that are based on analysis of information that describes a system status of control machines’ power supply is formalized. The operation algorithm of the intellectual power supply management system is developed and the chart illustrating its work is provided. The 1887BE7T domestic microcontroller is offered for the implementation of the model.

Development of technology to ensure minimal thermal resistance between mating surfaces while simulating outer space conditions

The transition to the leaky design of the instrument compartment of the spacecraft inevitably leads to additional thermal loads on the components of the onboard electronic equipment due to a change in the heat transfer scheme. The thermal mode of operation of the onboard radio-electronic equipment of the spacecraft is one of the important factors for ensuring the long term active existence of the spacecraft. Ensuring the long term of active existence of spacecraft is the most important scientific, engineering and economic task, the solution of which requires a deep systematic approach at all stages of the creation and operation of onboard electronic equipment of the spacecraft. The strategic objective for ensuring the long term of the spacecraft’s active existence is the implementation at all stages of the life cycle of onboard radio-electronic equipment of the highest achievable reliability indicators through the using of modern design and technological solutions, as well as effective methods for its design and production. This article presents the results of experimental work to reduce heat transfer resistance between onboard electronic equipment and the spacecraft’s thermal control system. As a result of the work, the main data were obtained on improving the heat sink efficiency of the energy-converting equipment of the spacecraft, the effectiveness of measures to ensure heat removal of the onboard radio-electronic equipment of the spacecraft was confirmed.

Evaluation of the limit properties of a solid body system

This article discusses the design of modern wheel-transport vehicles, in which the problem of reducing the level of vibrations and shocks arises, since the quality and performance, reliability and durability of the operation of machines, devices and equipment depend mainly on the resulting fluctuations during their operation. Also, solutions of problems concerning the limiting properties of solid-state systems for cases of harmonic and shock effects are discussed. The design model of many technical objects is a solid body, which is onboard radio electronic equipment (REA). For the selected model of a solid body, a system is designed for the vibration isolation of a block, at s points of which there are electrical radio-sensitive elements that can withstand a given limiting vibration acceleration. The synthesized vibration-proof system is implemented with the help of linear passive elastic-damping suspensions and active elements, which represent an ideal servo-mechanism.

ШЛЯХИ СТВОРЕННЯ ІНТЕГРОВАНОГО РАДІОЛОКАЦІЙНО-ПЕРЕШКОДОВОГО КОМПЛЕКСУ НА ЛІТАКАХ-ВИНИЩУВАЧАХ ЗБРОЙНИХ СИЛ УКРАЇНИ

Today, one of the possible ways to solve the problems of increasing the effectiveness of the use of fighter aircraft is the deep integration of equipment installed on board the fighter. In the article, the authors reveal views on the possible ways of integrating onboard radio-electronic equipment (on-board radar, radiation warning station, on-board station of active interference of individual protection) fighter planes of Ukrainian Air Force into a single integrated radar-jamming complex.Considering the integrated radar-jamming complex as a complex system that consists of a targeted set of interrelated elements against the background of the external environment or some higher level system. The main feature of creating such a system during its design will be a functional-structural approach. At the same time, integrity and complexity should remain one of the most important principles for constructing an integrated radar-jamming complex. Based on the principles and tasks that the integrated radar-jamming complex will be able to solve, its structural scheme will be built and the devices and facilities that should be part of it will be determined.

Проектирование радиационной защиты комплекса научной аппаратуры космического аппарата дистанционного зондирования Земли

In the course of operation spacecrafts are exposed to ionizing radiation from outer space. The electronic component base (ECB) used in creating onboard radio-electronic equipment of universal space platforms does not always correspond to the external operating conditions in terms of radiation resistance for some spacecraft orbits due to a number of technical and/or economic reasons. One method to increase the radiation resistance of onboard equipment is to install additional mass protection in the form of screens on the whole equipment or local screens on individual critical radio and electronic components. The article describes the design of additional radiation protection of the geostationary spacecraft scientific equipment complex for adaptation to the radiation conditions of operation in orbits of the “Molniya” type. The solution of the problem involves several preliminary steps, namely: determining the radiation conditions for the spacecraft operation in the target orbit, estimating the local absorbed doses at the locations of the onboard equipment, estimating absorbed doses directly in the electronic component base of the equipment and analyzing the radiation resistance. Designing the radiation complex of scientific equipment was based on the values of the radiation resistance of the equipment and its components, as well as the calculated values of the local absorbed doses in the components

An Adaptive Control of the Board Oscillations of Onboard Radio-electronic Equipment in the Resonant Mode

In the article the features of dynamic plate bending, as a basis of printed board assemblies of onboard radio-electronic equipment, with its resonance oscillations and various fixing conditions, are analyzed. Application features of the bending mode for solving the problem of radio elements placing on the plate field are considered. Methods for obtaining the eigenmodes of the plate by mathematical and experimental methods are described. An idea of adaptive control of oscillations of the plate in the resonant mode is proposed.

Schematic Method of Estimation and Increase of Radiation Hardness of the Onboard Radio-electronic Equipment for Space Applications

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The dynamics of phase changes in a heat storage of thermal control system for onboard radio-electronic equipment

The paper considers a heat storage (HS) based on the materials with a “solid-liquid” phase change for a thermal control system for on-board radio electronic equipment (REE) with periodic and short time action. To intensify the heat transfer in the HS design, ribs made of hyper heat-conducting plates are used. The dynamics of temperature fields and phase transformations in the HS volume is studied on the basis of numerical modeling. The results of calculations have shown that the use of ribs in the form of hyper heat-conducting plates allows significantly reducing the amplitude of temperature fluctuations at the seat of the REE unit.

Architecture of a platform for hardware-in-the-loop simulation of flying vehicle control systems

A hardware-software platform is presented, which is designed for the development and hardware-in-the-loop simulation of flying vehicle control systems. This platform ensures the construction of the mathematical model of the plant, development of algorithms and software for onboard radioelectronic equipment and ground control station, and visualization of the three-dimensional model of the vehicle and external environment of the cockpit in the simulator training mode.

Технологии информационной поддержки жизненного цикла бортовой радиоэлектронной аппаратуры ракетно-космической техники

Технологии информационной поддержки жизненного цикла бортовой радиоэлектронной аппаратуры ракетно-космической техники

ZHGUT_V2 SOFTWARE DESIGN SUITE FOR DESIGN OF WIRED INSTALLATION IN ALTIUM DESIGNER – SOLIDWORKS SYSTEM

This article is dedicated to automation of the design of wired installation of on-board radio electronic equipment for space vehicles. In this paper, we present a software suite that makes it possible to retrieve from the EDA-system a list of wiredwire circuits, to perform its automated processing and generate data for monitoring the electrical bundles of the REE, data for creating a 3D model of electrical wiring in CAD, connections table in accordance with GOST 2.413–72. The software suite makes it possible to reduce the number of errors and the overall time for REE design.