The effect of collapsing layers in flat panels made of a hybrid material on the stability under compression and shear is analyzed. The hybrid material is formed from carbon fiber and fiberglass blocks. The blocks form a symmetrical structure of layers relative to the neutral surface. The eigenvalue problem is solved in displacements by approximating the deflection function with "beam" functions depending on the support conditions on the panel contour. The minimum eigenvalues are determined – stability coefficients and critical compression and shear forces. The panel is loaded with a contour force in fractions of the critical force, the problem of postcritical deformation is solved by approximating the deflection as a product of an unknown amplitude and the minimum eigenform. Using the layer loading coefficients, the load-bearing capacity of the panel is estimated by the moment of failure of the most loaded layer/layers of different structures using the Tsai-Wu strength criterion. The ultimate force is established at which the loading coefficient in the most loaded layer is. This damaged layer is replaced by a fictitious layer with mechanical properties of the binder. The analysis of layer-by-layer destruction of hybrid panels is limited to five loading stages. As a result of the research, critical compressive and shear forces were found, allowing us to evaluate the effect of layer-by-layer destruction of the hybrid material on these values, and an effective reinforcement option for the hybrid package was determined.
The article summarizes more than forty-year period of progress of technology of development of the onboard software of the satellites created by JSC «Academician M. F. Reshetnev» Information Satellite Systems» (now JSC «RESHETNEV»), and provides an overview of the key aspects that make this technology effective: satellite software is developed as a set of satellite system software, considered as software built into these systems; satellite system software operates in a single hardware and software environment and is developed on single tools using a single technology; the system for supporting design, system testing and software maintenance is built on the basis of the satellite software information model and the system of development object archives; the environment for development, autonomous testing and verification of software for software systems is built on the basis of a cross-programming system in the Modula-2 language, containing interpreters for on-board computer commands; portability of functional software to a new computing platform is ensured by the constancy of software interfaces and special methods for adapting the unified on-board OS to new computing platforms; quality management, based on the quality of software components, the quality of software configuration management and the quality of software verification and confirmation as a whole; three-level management of objects and works; the use of software models of satellites both for the purposes of system testing of satellite software and for its maintenance during operation.
The deployment of U.S. weapons in space reduces the flight time of weapons to important strategic ground and space objects, which in turn significantly limits the ability to counter threats and retaliate with domestic strategic nuclear and non-nuclear forces. This factor increases the importance of the task of optimal control of the guided aircraft's movement towards a maneuvering space object to improve the accuracy of guidance. This article explores the synthesis of optimal control of the guided aircraft's movement towards a maneuvering space object. The purpose of the synthesis is to ensure the acceptable conditions for capturing a space object by a television homing head by fulfilling the conditions of quasi-collinearity of the velocity vectors of the aircraft and the space object at the end of long-range homing. The experimental results of the study confirm the achievement of the goal. To determine the transition area of the guided aircraft to homing.
In order to increase the accuracy of predicting time information in synchronization systems (this accuracy, in turn, depends on the mathematical model describing the departure of the time scale and on the accuracy of estimates of its parameters), it is proposed to process time information using a two-step algorithm. In the first step, in order to find the trend in the class of linearly or parabolically varying functions, the maximum likelihood method is used, which can be implemented taking into account the posterior probability. In the second step, after highlighting the trend of the time scale departure, it is proposed to predict the observation noise using the least squares method (which can be supplemented with L2 regularization), where it is proposed to use trigonometric functions as basic ones. The optimal choice of the period of the first harmonic and the multiplicity of the considered harmonics in the decomposition of the observation noise is carried out using its approximate canonical decomposition by trigonometric functions with random coefficients. These parameters, as well as the variances of random decomposition coefficients, are in accordance with the spectral density of the power of the observation noise estimated at the observation interval and with a given accuracy of reproducing its variance. The advantage of the approximate canonical decomposition of observation noise in comparison with the strict orthogonal Karhunen-Loev decomposition is shown. The paper substantiates the optimal choice of observation and forecasting intervals.
Currently, antenna parameter measurement methods can be divided into two main groups: far-range and near-range methods. Long-range methods do not require expensive and complex equipment, but their implementation often requires an antenna range hundreds and thousands of meters long. In addition, the task of shielding the measuring path from the influence of signal reflections from various objects becomes almost impossible. Near-field methods, on the contrary, are devoid of this disadvantage, but require the use of complex automated measurement and computing systems. The method of measuring antenna characteristics in the Fresnel zone makes it possible to organize an antenna range of significantly shorter length than in the methods of the far zone. This article is devoted to the use of this method in relation to a conical horn antenna at a frequency of 13 gigaherz (GHz). The effect of correction of phase direction pattern is shown for different values of the size of the direction pattern recovery area, as well as for different configurations of the antenna position on the control unit. The direction pattern recovery results was analyzed for each control unit configuration. Based on the analysis of the results of the direction pattern restoration results, a conclusion was made about the relationship between the need to correct the phase direction pattern and the distance from the center of the antenna aperture to the intersection of the axes of rotation of the control unit.
The use of composite materials, especially in space technology, is becoming increasingly relevant due to their unique properties, which make it possible to function effectively in extreme conditions and maintain specified characteristics. The article presents a study of polymer composite materials based on aramid fibers and their applications in the rocket and space industry. The purpose of the study is to substantiate the possibilities of creating such composites and to assess their prospects for use in spacecraft. The paper defines the key physical and mechanical properties of aramid fibers and the effect of these properties on the characteristics of composite materials based on an epoxy matrix. The analysis of polymer composite manufacturing technologies with comparative characteristics of various matrices, fillers and production methods is also carried out. The results obtained confirm the high potential and expediency of using aramid-epoxy composites in rocket and space technology due to their high strength, lightness and resistance to aggressive environments. For reliable applications, an in-depth study of the stability and durability of such materials in outer space is necessary. Further research should cover aspects such as impact resistance and thermal stability to ensure the safety and reliability of future spacecraft designs.
In space technology, special drives are used to guide antennas, lenses and other systems. They must meet high requirements for positioning accuracy, smooth running, self-braking, reduced dimensions and weight, increased load capacity, service life and efficiency. The mechanical transmissions used in space systems are used in the form of combined converters, such as toothed cylindrical-worm, worm-screw, etc. With the help of worm gears with self-braking, it is possible to obtain precise and small movements. The main disadvantage that prevents an increase in the load capacity of existing globoid worm gears is the irrational geometry of the engagement along the linear contact of the helical surface of the globoid worm and the teeth of the cylindrical worm wheel, which reduces the load capacity and is due to the technological complexity of manufacturing the helical surface of the globoid worm of a radius non-linear profile. The objective of the study is to develop the CTE and manufacturing technology of a profile-conjugated globoid-cylindrical worm pair, providing an increase in the load capacity and a method for calculating the radius of reduced curvature and the contact patch of the conjugated working surfaces. The study was conducted using experimental and mathematical methods. Models, methods and a technological scheme for cutting a helical surface of a concave radius involute profile of a globoid worm by rotary turning were developed. The developed technology for manufacturing a profile-conjugated globoid-cylindrical worm pair can be used in space engineering, aircraft manufacturing, in the production of defense equipment and in general mechanical engineering.
Determining the failure load of aircraft components is a critical aspect of aircraft design and operation. Flight safety, component durability and economic efficiency of operation directly depend on the strength characteristics of materials and structures. In this connection, the problem of numerical and analytical calculation of destructive load is considered. The program implementing the algorithm of destructive load determination using the finite element method in Ansys package has been developed. Validation of the algorithm is performed on plates with a circular hole. Homogeneous plates made of D 16T and B 95 alloys, as well as combined specimens consisting of two plates, one of which is made of D 16T alloy and the other of B 95 alloy, were investigated. In the combined specimens, in the tensile region where the plates are in contact, it is assumed that the friction occurring between their surfaces has little effect on the solution results, i.e., there is no assignment of any contact conditions. In the gripping region,the plates are strongly pressed against each other and rigidly fixed in the gripping devices. The elastic-plastic parameters of the materials determined from tensile tests of smooth specimens without holes are used in the calculations. A satisfactory agreement between the experimental data and the calculation results is obtained.
The «Grebenka» is part of the receiving and computing module of the global satellite system devices and is used to position wires in the socket. When developing the manufacturing technology for this part, problems arose due to the properties of the polyamide material and thin-walled structural elements with tolerances for quality grade 9. The design of the part includes grooves and thin jumpers between them. Processing with a disk cutter using conventional milling methods led to the formation of long burrs and increased the likelihood of obtaining defective products due to the difficulties in performing metalwork on small-sized elements while maintaining tolerances for specified dimensions. The solution to the problem resulted in a change in the cutting direction during milling: from downwind to upwind. General cutting recommendations for the part in question are provided. The number of passes during processing was also increased, which made it possible to cut off burrs and eliminate the metalworking operation performed manually, and to meet the requirements of the design documentation in an automated manner. This method is effective in terms of increasing the probability of producing good products, reducing manufacturing time, and can be applied to serial production by automating the production of similar types of parts and structural elements of polyamide.
The article presents a method for noise filtering in inter-satellite measurements based on Fourier transform and adaptive colored noise processing. The relevance of the study stems from the need to enhance the accuracy of satellite navigation systems amid increasing interference and operational complexity. The primary goal is to reduce random and systematic errors in measurement residuals caused by discrepancies between calculated and actual signal delays between satellites. The proposed method combines spectral analysis using Fourier transform to decompose signals into frequency components with adaptive algorithms that account for the spectral density characteristics of colored noise. This approach effectively isolates low-frequency useful signals, suppresses high-frequency noise, and minimizes signal distortion. The results demonstrate a noise level reduction of 0.5 m while preserving data structural integrity, confirmed by amplitude and phase spectrum analysis, as well as correlograms. The method proved effective in environments dominated by pink noise associated with long-term trends and hardware delays. The developed technique improves delay estimation accuracy in geodetic tasks, aviation navigation, and monitoring applications. Future research directions include integrating machine learning algorithms for real-time dynamic adjustment of filtering parameters and optimizing computational resources.
The aim of the study is to compare the stress fields and stability of adapters of various configurations made of aluminum Al – 2024 and composite M46. The adapters have a constant mass. The solid and mesh adapters were reinforced with rigid frames along the edges of the structures, the lower edges were fixed with rigid sealing. Parametric discrete models were modeled using the ANSYS finite element software package. A two-node beam end element with six degrees of freedom BEAM4 was used for the mesh adapter. A four-node, six-degree-of-freedom terminal element SHELL181 was inserted into the solid adapter. The load on the structure was transferred using topological connections with an imaginary node located in the center of the upper frame. Topological connections were modeled by a rigid MPC 184 element. An axial compressive load of 108 t.s. was applied to the imaginary node. Analysis of the stress-strain state of the continuous adapters showed that the adapter made of carbon fiber holds the load better than aluminum. The values of the critical load of the stability loss of the aluminum adapter are less than the values of the critical load of the carbon fiber adapter. The analysis of stress and displacement fields has shown that in the mesh adapter, the spiral fins work for compression, and the annular fins work for tension. A comparison of the stress fields of the mesh and solid adapters, as well as the values of critical loads, allows us to conclude that it is more efficient to use a mesh structure in the product.
The new deployment system for a precise rigid petal reflector is proposed and investigated. The deployment of the reflector is performed in two stages. At the first stage, the reflector is transferred from the folded (transport) state to a state close to the deployed (working) one. At the second stage, a high-precision fixation of the final deployed state is performed. To achieve this, a new type of self-setting locks based on kinematic couplings of a novel design is used. Results of computer simulations of the new deployment system are presented. To validate the proposed technical solutions, a physical model of the reflector with a diameter of one meter, consisting of twenty-three petals and a central mirror, was manufactured. This model serves as an experimental platform for testing deployment kinematics, evaluating structural stiffness, and assessing deployment repeatability. Results of both computer and physical simulations are discussed. The problem of numerical measurement of deployment repeatability is addressed. An optical 3D scanning method is employed for this purpose. Measurement results of the physical model demonstrate that the self-setting locks ensure petal positioning accuracy at the level of 0.1 mm without active mirror shape correction.
The primary function of a spacecraft scientific payload is to perform measurements. The voltage reference is a key component of a measurement system, determining its accuracy. During normal system operation, the reference voltage is subject to temperature-induced variations which, unlike initial error, cannot be eliminated by on-ground calibration. The performance of the ISL21090B-50 voltage reference was experimentally evaluated within the typical operating temperature range for space equipment. Its integral and differential temperature coefficients and thermal hysteresis were determined. Conclusions were drawn regarding the theoretically achievable resolution of a precision measurement system based on this integrated circuit, and methods for its improvement are described. The theoretical possibility of improving measurement system resolution is demonstrated for voltage references with a linear voltage-temperature relationship, using mathematical compensation based on the actual temperature of the reference element. The performance of radiation-hard 5306NT025 integrated temperature sensors was experimentally evaluated in a climate chamber for use as internal telemetry sensors in future space projects, and their error vs. temperature curves were obtained. An example of thermal drift compensation for the ISL21090B-50 reference is presented, utilizing the data acquired from the temperature sensors.
The paper addresses the issues occurring during updating of computational dynamic models of aircraft based on ground vibration test results. These include selection of modal testing methodology based on the analysis of ratio between forced monophase modes and eigenmodes. Structural damping properties can be identified from test results. It is worth noting that the errors in experimental determination of eigenfrequencies are significantly lower than the ones in general masses and damping coefficients. The method for updating elastic properties of finite element models is developed. The mass matrix is assumed to be accurately defined.The objective function is a weighted sum of squares of differences between experimental and calculated eigenfrequencies. The objective function is minimized iteratively. The robustness of the approach with respect to errors in ground vibration test results is investigated. The approach to model structural damping properties based on ground vibration test results is presented. The damping coefficients are computed and chosen as the target ones for each experimentally determined eigenmode. That indicates that in modal coordinates the matrix which consists of these coefficients is diagonal. In order to construct the damping matrix in physical coordinates, the Rayleigh damping model is used. The finite element models of aircraft wing and the aircraft of flying wing type have been updated.
This article presents in detail the results of the research and development of a unique active electromagnetic weight compensation system created by engineers at JSC «Reshetnev». The primary purpose of this system is to conduct modal testing of modern, weakly damped structures typical of the space industry. The key objective of the system is to create and maintain conditions that accurately simulate zero-gravity conditions on Earth. This effect is achieved through a complex, precisely controlled interaction of electrodynamic forces. The authors describe in detail the system's basic operating principle and its design implementation, paying particular attention to the description of key components. An innovative method for generating the control current dependence on the coordinates of the moving element, which forms the basis for precise control, is proposed and mathematically substantiated. To ensure the highest stability and dynamic accuracy, advanced control algorithms using PID control were integrated and adapted into the system. A significant improvement in control quality was achieved through the implementation of a specialized high-power current amplifier, which eliminated the induced electromotive force and significantly increased the accuracy of the excitation force setting. A series of experimental studies and tests fully confirmed the high operational feasibility and effectiveness of all developed technical solutions. The results also allowed us to identify specific promising areas for further optimization of the system to improve its performance.
The article is devoted to the comprehensive development of a dual-mode waveguide filter for the Ku-band, featuring an elliptic amplitude-frequency response. The relevance of the work is driven by the growing requirements for satellite communication equipment, such as increased selectivity, reduced mass and size, lower passband losses, and ensuring group delay flatness. The work details the fundamental advantages of the dual-mode waveguide filter compared to classical single-mode counterparts, the chief among them being the ability to achieve high selectivity with half the number of resonators. The design method based on the application of modern computer-aided design systems is described: CST Filter Designer for coupling matrix synthesis and initial analysis, Fest3D for accelerated electromagnetic synthesis, and CST Studio Suitе for final modeling and optimization of the filter geometry. The simulation results for a fifth-order dual-mode waveguide filter are presented, confirming that its characteristics meet the specified requirements. The effectiveness and simplicity of the proposed methodology are demonstrated, as well as the high accuracy of the correlation between the simulated and experimental data. The developed filter shows high potential for application in advanced satellite communication systems.
Additive manufacturing methods are currently being introduced into the aerospace industry. Additive manufacturing enables the creation of complexly configured parts, thereby ensuring high efficiency. However, one of the key challenges facing additive manufacturing is residual stress, which arises during additive manufacturing and is present at all stages. Residual stress, a consequence of thermal heating and cooling of the structure, can have a significant impact on the mechanical and operational properties of manufactured parts. This article examines the causes of residual stress in various additive manufacturing methods. Their impact on the strength characteristics of printed structures and the geometric accuracy of their manufacture is assessed. Methods for reducing residual stress at various stages of additive manufacturing are discussed, including additive part modeling and post-manufacturing processing. A review of existing approaches and methods for modeling and predicting residual stress in additively manufactured structures is provided, which is particularly important for reducing residual stress and increasing strength and reliability in critical aerospace components.
Using the CAE system Ansys Fluent, a numerical solution was obtained for the aerodynamics problem of a recoverable carrier-rocket block whose prototype is the central core of the Soyuz-2-1a launch vehicle, on the descent segment to Earth. At each time step of the integration of the spatial motion equations, an algorithm for computing aerodynamic coefficients is implemented: the motion-integration module calls Ansys Workbench to solve a steady gasdynamic problem by the finite-volume method. The procedure includes construction of the computational domain geometry, mesh generation, specification of the physical model and boundary conditions in Ansys Fluent, and extraction of lift, drag and side forces as well as moments as functions of angle of attack. Plots of the steady aerodynamic coefficients versus angle of attack were obtained and used in models of the free uncontrolled motion of the block after separation. Using the refined aerodynamic coefficients at each integration step, an integral trajectory calculation was performed accounting for wind loading, which made it possible to estimate the expected coordinates and impact areas. The presented methodology enables obtaining refined motion trajectories, accounting for non-axisymmetric configurations and, in future work, incorporating structural elasticity to improve prediction accuracy and reduce potential environmental harm.
Over the past 25 years, CubeSats have accounted for nearly 15 % of all spacecraft launched into orbit. To support a comprehensive review of existing CubeSat missions and to enable the use of related data for planning and developing future missions, a unified and easily accessible information source is required. This paper presents a new open-access Russian-language database of CubeSats, which compiles information on their principal design characteristics as well as both current and historical orbital parameters. A classification scheme is presented that organizes CubeSats by family, structural design, and mission purpose. The study uses data current as of autumn 2025 for 2,783 CubeSats, which, according to the proposed classification, are grouped into 896 families, 129 models, six functional classes, and five application domains. The work also describes the possible deployment methods, which are divided into two categories: deployment from the ISS or deployment from other launch or carrier systems. The most common orbital classes for CubeSats are identified, namely Sun-synchronous orbits and ISS-inclination orbits.
This paper considers the urgent problem of developing modern initiating devices for space technology that provide high reliability with minimal impact. The research is aimed at creating an electromagnetic initiating device capable of replacing traditional pyrotechnic systems, which have a number of significant disadvantages, such as high shock loads, one-time use, and the complexity of ground-based mining. The main purpose of the work is to develop the design of an electromagnetic control unit with optimal weight and size characteristics, ensuring a high response rate with minimal impact. The article discusses in detail the principle of operation of the device based on the interaction of the solenoid with the conductive shell of the core, where the braking effect is achieved by generating eddy currents. This principle makes it possible to significantly reduce shock loads compared to traditional solutions. Special attention in the study is paid to the methodology of parametric analysis and optimization of the structure. The application of the finite element method in the ANSYS Maxwell software package made it possible to identify the key design parameters that have the greatest impact on the device's performance. To build an accurate mathematical model, a machine learning algorithm based on polynomial regression with regularization was used, which provided high prediction accuracy. An important part of the study was the multi-purpose optimization of the design using the game theory algorithm. This approach made it possible to effectively solve the problem of simultaneously increasing the useful operation of the actuator with a minimal increase in the mass of the device. The optimization results are confirmed by complex simulation of the device dynamics in the MATLAB Simulink environment. The calculations and simulations performed demonstrated the appropriate operational characteristics of the developed device. The results obtained are of practical importance for the space industry, opening up opportunities for replacing traditional pyrotechnic systems with more reliable and safe electromagnetic analogues.
