On-board Electronic Equipment Research Articles

Increasing the period of active use of on-board electronic equipment of spacecraft

For electronic equipment of space systems, and primarily memory devices, the task of protection from the effects of ionizing cosmic radiation and other external factors that distort stored and processed information is relevant. This paper proposes a holographic coding method that allows you to restore information in the event of a large number of errors. The method is based on recording into memory, instead of the original digital hologram data, a virtual digital object corresponding to a data block. The divisibility property of a hologram is used, which makes it possible to reconstruct a recorded data block from its fragment. The achieved level of noise immunity is determined by the size of the hologram. For an 8-bit data block, recording a 256-bit hologram provides information recovery if 75 % of the recorded hologram is lost. The developed decoder corrects a package of dependent (grouping) errors that distort all bits of the hologram. The number of random independent errors that the decoder corrects can be up to 40 % of the recorded information. The information storage system, resistant to ionizing radiation, is a memory array of increased capacity, taking into account the selected redundancy factor, and a memory controller that performs holographic encoding when recording information and decoding with automatic error correction when reading information. The operating algorithm of the controller itself can be implemented in the form of a programmable logic integrated circuit, or stored in a read-only memory device that is not affected by ionizing radiation.

Оценка и анализ поглощённой дозы в гетероструктуре AlGaN/GaN при воздействии ионизирующих потоков радиационных полей Земли в условиях эксплуатации наноспутника

Research of influence of ionizing radiation in the energy range of protons (from 0.1 to 400 MeV) and electrons (from 0.04 to 7 MeV) on circular sun-synchronous orbit on the radiation resistance of the AlGaN/GaN heterostructure as part of the nanosatellite on-board electronic equipment under operating conditions is carried out using physical and mathematical modeling in the stack model approximation. All calculations are based on data from the energy spectra of protons and electrons in sun-synchronous orbit provided Spenvis information system (European Space Agency). The results of calculation of integral fluxes and absorbed doses in aluminum and heterostructure were obtained. An evaluation and analysis of the radiation resistance of the heterostructure under the influence of low- and high-energy ionizing particles and their ability to function throughout the year was carried out.

Problematic issues of application of methods of accelerated radiation testing of ECB

In this paper, an analysis of existing domestic and foreign regulatory documents regulating the conduct of radiation tests of EEE-part to determine resistance to dose effects is carried out. Ionizing radiation from outer space is one of the most important operational factors affecting the performance of on-board equipment, as a result, determining the duration of the active existence. This largely determines the relevance of the topic of radiation effects in electronic equipment materials, radiation-induced degradation of semiconductor devices and integrated circuits, and determining the reliability and radiation resistance of on-board equipment under the influence of the ionizing radiation from outer space. Conducting radiation tests of EEE-part (total dose effects) is an integral part of the process of ensuring radiation resistance of on-board electronic equipment and the spacecraft as a whole. The paper identifies and shows the existing risks of the developer of the on-board equipment and the spacecraft as a whole while ensuring the radiation resistance of the equipment and the guaranteed fulfillment of the target task of the spacecraft during the entire period of active lifetime.

EVALUATION OF THE RESULTS OF TESTING THE HARDWARE COMPARTMENT OF SUBORBITAL ROCKETS FOR RELIABILITY

Nowadays, the issue of creating modern models of rocketry is becoming more and more popular due to the constant development of technologies and competition in the domestic market. This paper describes the results of the behavior of on-board electronic equipment during launches of ultra light suborbital rockets of the «Meteo» series manufactured by the Rocketry agency project. When designing the hardware compartment
 and further improving it in subsequent rocket models, the first place is occupied by its level of reliability, which should in turn take into account the economic part for the development and manufacture of further products. Such improvements included the use of new materials, increased strength and resistance to negative impacts, improved thermal management and elimination of structural defects. Tests have shown that to overcome higher altitudes, such as the Karman Line, more fuel is used and the mass and size characteristics of the rockets change, which leads to increased complexity of their control and navigation. One of the key challenges is the lack of an effective control system. Without a proper control system, a missile's flight becomes unpredictable and dangerous for the area where it is flying. One way to solve this problem is to develop and test a proper control system for the missile on a special test bed that will allow testing and debugging the control system in a controlled environment that ensures its functioning in real-world conditions without the risk of sending an untested missile into the air.

Structural design and mechanical analysis for space-borne electronic equipment

With the development of a new generation of radar performance requirements, the chip integration and module assembly density of onboard electronic equipment have been greatly improved. The integration of the system is becoming more complex. This paper designs a kind of electronic equipment with a superposition structure. Separate functional modules are strung together by a screw. Each module unit has the same sectional size. The conventional cabinet form structure is abandoned. The main contradiction of volume, weight, and reliability is solved well. The mechanical properties of electronic equipment are analyzed by the finite element method, and the structure of the fixed lug is optimized. The result shows that the electronic equipment meets the requirements of structural safety margin. The structural design is safe and reliable.

An Aeromagnetic Compensation Method for Suppressing the Magnetic Interference Generated by Electric Current with Vector Magnetometer.

In aeromagnetic detection, the magnetic interference conducted by electric currents in onboard electronic (OBE) equipment is gradually being taken seriously with the development of aeromagnetic compensation technology. Here, we propose a compensation method based on the synthetically total magnetic field (STMF) measured by an onboard fluxgate vector magnetometer. In this method, a compensation model is firstly built to suppress the electric current magnetic interference (ECMI) which is jointly measured by a scalar magnetometer and a fluxgate vector magnetometer. The singular spectrum analysis (SSA) method is introduced to accurately extract the characteristic signal of the ECMI from the compensated STMF. In addition, in order to better suppress the geomagnetic gradient interference, the International Geomagnetic Reference Field (IGRF) model is introduced to modify the existing geomagnetic gradient compensation model. Based on these, a novel compensation model including the traditional aeromagnetic compensation model, modified geomagnetic gradient model, and ECMI compensation model is proposed. The results in the field experiment show that this model has better compensation performance than the TLG model, which is extended from the T–L compensation model.

Typical vibration isolation systems and shock absorbers in on-board electronic equipment designs

The article discusses basic principles of designing shock absorbers and vibration isolation systems for electronic equipment of rockets. The rationale for the use of dry friction elements (cable shock absorbers) in shock absorbers is given. The designs of miniature shock absorbers are given.

VIBRATION PROTECTION OF ON-BOARD ELECTRONIC EQUIPMENT FROM EXTERNAL INFLUENCES

The article is devoted to the problems of protection of on-board electronic equipment (BEA) from vibration effects. To ensure BEA protection, it is necessary to know the characteristics and conditions of external influences and, in accordance with this, choose a method to reduce their influence on the BEA performance. The article discusses the most common ways to reduce the impact of mechanical external influences, and also provides analytical calculations of the printed circuit board and their correlation with the results of mathematical modeling. The developed technique for modeling vibration effects on the printed circuit assembly allows you to more effectively evaluate the physical characteristics of the product, thereby avoiding design errors and inaccuracies.

Mathematical Modeling and Optimization Heat Pipe Systems

The results of optimization of the supporting structure of a block of onboard electronic equipment with a built-in single flat heat pipe in the supporting structure with an integrated heat pipe system are presented, using the example of solving a model problem with a single heat source. The comparison was carried out at an equal temperature, occupied volume and for a certain maximum temperature of electrical radio products. The results of computational modeling are presented, demonstrating a comparison of the characteristics of a single flat heat pipe with a system of sequentially located flat heat pipes. Ultimately, the studies carried out have determined the limiting values of the removed thermal power of a single heat pipe, two-level and three-level heat pipe systems with different heat carriers. The versatility of the mathematical model, supplemented by the optimization method, has been confirmed

On-board electronic telecommunication equipment with laser illumination in integrated search systems of underwater vehicles

The intensive development of autonomous underwater robotic complexes is very important for the development of the World Ocean. One of the main problems of using underwater robotic complexes is an increase searching efficiency of underwater devices based on the integration of the capabilities of onboard radio-electronic systems of obtaining information in various physical fields. Analyzing the physical basis of the search, including the consideration of the environment of its conduct, objects, as well as detection tools, it can be noted that the result of the search operations of the same objects in the same water areas for various underwater robotic complexes depends on what means of detection they are equipped. The presence of a certain set of the technical means will specify the development of the optimal sequence of actions of the search algorithm. The creation of such algorithms in relation to the task of increasing the search potential of underwater robotics will determine the direction of the research that ensures the formation of an optimal system of underwater search. Efficient use of search resources substantiates the conclusion that radio-electronic means of submersibles forming the system of underwater search, include the number of devices functionally interconnected for its effective conduct. The specified combination is aimed at the formation of the so-called integrated search system, which provides an exchange of information between different channels of searching devices about all objects detected. The article provides proposals for the creation of integrated search systems taking into account practical experiments and experience in designing underwater vehicles capable to implement the optimal system of underwater search using laser technologies.

Experimental study of a high current electromagnetic interference filter for the spacecraft power bus

Secondary power supplies, including on-board electronic equipment, extend the range of operating frequencies in order to increase the efficiency of the converters. This leads to the deterioration of electromagnetic environment. We propose a protective device for the spacecraft power bus based on lumped elements, which is characterized by high reliability, radiation resistance, and low mass-dimensional parameters. This device suppresses common and differential conducted interference in high-current power circuits. The results of the circuit simulation and field experiments in the frequency domain are presented. The obtained results are analysed, and the practical recommendations are given regarding the design of noise-suppressing devices based on elements with lumped parameters.

The Experience of Digital Transformation of Business Processes of Applied Experimental Research by Using the Multitenancy of the Resources

As part of the digital transformation of various areas of human activity, the urgent task is to transform existing business processes (BP) in order to increase their variability according to the needs of the customer, to increase productivity, quality and competitiveness of products. The introduction of end-to-end digital technologies allows for this. The article examines the experience of transforming the BP of experimental research in solving a number of applied tasks in the field of electronic instrumentation, which is obtained as a result of the introduction of operation technology for test, research and laboratory equipment based on the concept of multitenancy. Developed on the basis of the experience of the authors, a number of industrial samples and prototype multiuser distributed measurement-control systems implementing this concept have allowed to transform the following processes: end-to-end BP of tests on-board electronic equipment of spacecraft (communications, relay, navigation, geodesy, remote sensing, etc.); BP of forming the operational load of the spacecraft's on-board relay complex; BP of conducting experimental laboratory research in the industry training system. The effectiveness of modernized BP was evaluated on the basis of their formalized models and a set of qualitative indicators. The key resulting effects of transformation: improving the quality of BP by improving the informativeness of individual business functions and the efficiency of the use of high-tech experimental equipment; reducing the number of gaps in BP by reducing the number of business roles involved in their implementation; reducing the duration of BP by significantly reducing material and time costs and improving the productivity of individual business functions; transition to a service model "Laboratory As Service" for access to high-tech equipment while performing experimental laboratory studies based on digital educational environments.

A generalized simplified modeling method for electromagnetic coupling effects of uncertainty strapping cable harness

<sec>The cable harness provides a main gateway for electromagnetic interference(EMI) in electromechanical system. The unreasonable electromagnetic compatibility (EMC) design of cable harness will produce EMI to other on-board electronic equipment, bringing great safety risks to the system. Theoretical research and engineering practice indicate that most of the electromechanical systems cannot satisfy EMC standards, which can be attributed to the EMI generated by cables. As for the eletromagnetic(EM) illumination analysis, reliably and efficiently generating a full numerical model of cable harness is becoming more prominent for the EMC designers. Therefore, it is necessary to develop a more effective method to solve the modeling problem of cable harness. </sec><sec>In the practical application, the cable harness has the characteristics of spatial layout, and its characteristics such as “large number of core wires”, “arbitrary curvature of space” and “randomness of wiring” bring challenges to the modeling of EM coupling to cable harness. The numerical simulation of the whole cable harness model requires severe conditions for computational resource and even makes the EM coupling analysis impossible. Thus, considering the uncertainty of wire position, this paper proposes a generalized simplified modeling method for the EM coupling effect of uncertainty strapping cable harness. Firstly, the Gaussian distribution and spline interpolation are used to determine the location of the core conductors in the random bundling. Then, the distribution parameters of the cable harness at different positions are established by using the transposition relationship between the subsegments of the wires. Finally, the effectiveness of the proposed method is verified by numerical examples of the arc-shaped and sine-shaped harness. </sec><sec>In conclusion, this paper proposes a generalized simplification technique to model the EM illumination on cable harness with uncertainty wiring factors. By grouping the conductors together, the required computation time is markedly reduced and the complexity of modeling the completely cable harness is significantly simplified within a good accuracy. The proposed method provides a way of solving the modeling problem caused by “uncertainty strapping” of the complex wiring harnesses in electromechanical systems.</sec>

Радиацияның әсерінен ғарыш аппаратының борттық электроникасының есте сақтау элементтерінің бірліктік істен шығуларын сұлбалық модельдеу

The main purpose of the work is the circuit simulation of failures of on-board electronic equipment of spacecraft (SC) for various purposes under specified conditions and the parameters of the transistors of the memory element during the passage of a single cosmic ray particle (CR). Actuality of the problem. It is known that during the operation of spacecraft for various purposes, as a result of the impact of cosmic rays (CR), on-board electronic systems fail, which leads to abnormal situations, and in some cases to the loss of satellites, for example, KazSat -1 and Phobos-Grunt. Therefore, this paper uses the method of circuit modeling, which is a highly efficient and relatively low-cost method that allows us to evaluate the circuit parameters of the transistors of the memory element during the passage of a single cosmic ray particle. In this paper, we present the results of circuit failure modeling (SEU and SEL) under radiation exposure to storage devices (memory), which was carried out on the CMOS structure, which is the dominant one in the manufacture of ICS.

A new approach to the development of perspective compact frequency multipliers of the subterahertz and terahertz bands for on-board electronic equipment

Currently, the increasing interest of researchers is attracted by the theoretical and practical problems of mastering the sub-terahertz and terahertz frequency range. Electronic devices operating in these ranges find effective applications in various fields of science and technology: aerospace equipment, security systems, spectroscopy, medicine, biology and many others. The purpose of this work is to focus on a frequency multiplication device that allows using basic sources of relatively low frequency generation to enter the terahertz frequency range. The results of recent years obtained both on the basis of solid-state effects and with the help of vacuum electronics, in particular, magnetron-type devices, which are characterized by compactness, high resistance to radiation loads, mechanical influences, which is important for on-board equipment, are considered. It is known that at high frequencies, vacuum devices require super-precision manufacturing of decelerating systems. This is essentially the main difficulty. The article proposes a new approach based on the hypothesis of P.L. Kapitsa, which allows to significantly simplify the anode structure of a magnetron multiplier with an acceptable level of output parameters. The achievements of recent years in the field of creating sub-terahertz and terahertz frequency multipliers, mainly for on-board equipment of mobile platforms, taking into account the requirements of aerospace systems, first of all, are noted.

An automatic test complex for unmanned aerial vehicle engines

One of the most important components of an aircraft ground testing infrastructure is hardware and software test benches with complete or partial imitation of the aircraft in complex, on-board electronic equipment and controls. The development and debugging of such complexes is a complicated problem. The solution for this problem is presented in in the form of the automatic test complex for unmanned aerial vehicle engines and propulsion devices mounted on the Gough–Stewart platform manipulator. The complex is based on the modular measuring platform and also includes a set of various sensitive elements for forces, vibration, speed, torque, video and sound registration. The article also describes the procedure for one of the functional assessment stages of the U AV engine test complex, notably, the assessment of the tensometric measurement accuracy. Further development of the complex associated with the software implementation of atmosphere, wind turbulence models and modules for preliminary formation of test scenarios-UAV flight paths.

Development of multivariate equivalent cyclic tests of HALT-based aviation radio equipment for assessing reliability

The article studies forced test models for determining reliability of on-board electronic equipment due to the combined effects of broadband random vibration and cyclical changes in temperature. The model of multivariate equivalent cyclic tests based on HALT (High accelerated life / limited test) procedures is described.

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.

The hardware and software implementation of the adaptive platform for an onboard spacecraft control system

In this paper the authors discuss hardware and software implementation solutions for an adaptable platform used in onboard spacecraft electronic equipment complexes. The proposed solutions ensure the reduction of time required for designing and manufacturing the spacecraft, increase of the export potential of communication and other services by enabling the adaptation of the onboard equipment to new protocols and technologies in the fields of communication, data processing, and control in the process of the spacecraft’s operation in orbit and expanding its hardware and software unification.

Electromagnetic Interference Generated in a Spacecraft During Static Charge Accumulation

An approximate assessment of the electrical fields generated on charging the spacecraft is performed. The interference generated by the protecting device intended for neutralizing a noncompensated electrical charge on the spacecraft body is assessed. The assessment shows that the electrical fields can lead to failures in operations of the onboard electronic equipment.