S. V. Khoroshylov

The Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and the State Space Agency of Ukraine, Dnipro, Ukraine

The article analyses the deployment performance of a mesh antenna, which consists of scissor-like and V-folding elements and does not have any synchronizers for the adjacent bays. A multibody model of the antenna is established considering the effects of the truss flexibility, joint friction, and complex coupling between the metallic mesh and net-t...

The structure of foldable cosmic reflectors, which serves as a base for building the space-based synthetic aperture radar EOS SAR (Medzmariashvili, Deployable space reflector, Patent GE P 2005 3604B, National Intellectual Property Center of Georgia, Sakpatenti, 2005 (In Georgian),; Richard and Feys, United States Patent № US 20190221944A1, 2019,; a...

This paper considers the problem of control of a parametrically uncertain dynamic system using an extended state observer. The control system is implemented using a two-loop scheme, where the outer loop ensures the fulfillment of the selected criterion for controlling the state vector, and the inner loop compensates for or reduces the influence of...

The article investigates the task of spacecraft relative control using reactive actuators, the output of which has two states, "on" or "off". For cases where the resolution of the thrusters does not provide an accurate approximation of linear control laws using a pulse-width thrust modulator, the possibility of applying reinforcement learning metho...

In orbital injection, the launch vehicle (LV) structure and the spacecraft are subjected to extreme dynamic loads, in particular to vibroacoustic loads (from rocket engine thrust oscillations and aerodynamic loads), which may cause spacecraft instrumentation malfunction and damage spacecraft light-weight thin-walled structures. This paper is dedica...

The advances in deep learning have revolutionized the field of artificial intelligence. These advances, as well as new tasks and requirements in space exploration, have led to an increased interest in these deep learning methods among space scientists and practitioners. The problems of controlling the attitude and relative motion of spacecraft are...

The aim of work is to create a dynamic model of a space antenna with the pantograph structure and study the processes of its deployment using open-source software. The methods of theoretical mechanics, multi-body dynamics, computational mechanics, and computer modeling were used for this research. The object for modeling is a novel mesh antenna, wh...

Introduction. Space debris is a serious problem that significantly complicates space activity. This problem can be mitigated by active space debris removal. The ion beam shepherd (IBS) concept assumes the contactless removal of a space debris object (SDO) by the plume of an ion thruster (IT). Techniques for determining the force impact from the IT...

The aim of this article is to develop a simplified method for modeling cable-pulley deployment systems of rod structures based on the calculation of cable tensions and nodal driving forces with account for friction and other features of the system. Methods of theoretical mechanics, multibody dynamics, numerical integration of differential equations...

Vibration loads on the launch vehicle and spacecraft can reach a high level, leading to abnormal and emergency situations. Therefore, the spacecraft structure must not only support the payload and subsystems of the spacecraft but also have sufficient strength and rigid- ity to exclude any emergencies (damage, destruction, unwanted deformations of t...

This study presents dynamics models and analysis of deployable mesh reflector antenna for mini-satellites equipped with synthetic aperture radar (SAR) payload. The antenna is of offset type with a diameter of 3.35 m and a mass of about 11 kg. The antenna design should provide reliable synchronous deployment of the structure given limited driving po...

This work tackles the problem of attitude control of a space-based synthetic aperture radar with a deployable reflector antenna, representing a lightly damped uncertain vibratory system with highly nonlinear dynamics. A control strategy based on two identifiable in-orbit vector parameters is proposed to make the robust controller less conservative....

The goal of this article is to develop a dynamic model of a space antenna with the pantograph structure and to study the processes of its deployment using open-source software. Methods of theoretical mechanics, multibody dynamics, computational mechanics, and computer modeling were used in the research. A mesh antenna of the novel design, which is...

The subject of research is the process of creating a neural network model (NNM) for determining the force impact of an ion thruster (IT) plume on an orbital object during non-contact space debris removal. The work aims to develop NNMs and study the influence of various factors on the accuracy of determining the force transmitted by the ion plume of...

Introduction. Electromagnetic actuators are widely used in spacecraft (SC) attitude control systems. These actuators can be modified by using slewing permanent magnets (ASPM) as sources of torque instead of electromagnets. These modified devices consume less onboard electricity for SC attitude control than the conventional ones.Problem Statement. A...

The advances in deep learning have revolutionized the field of artificial intelligence, demonstrating the ability to create autonomous systems with a high level of understanding of the environments where they operate. These advances, as well as new tasks and requirements in space exploration, have led to an increased interest in these deep learning...

The aim of the article is to model the processes of centrifugal deployment of a three-section boom and preliminary analyze the feasibility of this deployment method for an Earth remote sensing (ERS) minisatellite (MS). During the research, methods of theoretical mechanics, multibody dynamics, control theory, and computer modeling were used. Centrif...

The article investigates the feasibility of using an aerodynamic compensator for contactless removal of space debris from low Earth orbits, taking into account aerodynamic disturbances in the direction perpendicular to the orbital plane. The object of the research is a modified scheme of the “ion beam shepherd” de-orbiting concept. The modification...

This paper is devoted to the development of a light-weight deployable mesh reflector antenna for mini satellites with synthetic aperture radar (SAR) payload. The analyses of the electromagnetic and mechanical properties of the multi-beam deployable reflector antenna are performed for the space-borne dual-band (X- and S-bands) synthetic aperture rad...

A modified scheme of the known technology for contactless space debris removal, which is called Ion Beam Shepherd, is considered. This scheme uses an aerodynamic compensator in order to reduce the propellant consumption of the additional electrojet thruster of the shepherd spacecraft. The thruster serves to compensate the spacecraft motion caused b...

The aim of the article is to approximate optimal relative control of an underactuated spacecraft using reinforcement learning and to study the influence of various factors on the quality of such a solution. In the course of this study, methods of theoretical mechanics, control theory, stability theory, machine learning, and computer modeling were u...

The “ion-beam shepherd” is a contactless space debris removal concept, which implies that the shepherd satellite (SS) must be controlled to move at a certain small distance in front of a space debris object during the de-orbiting phase. As shown in recent studies, the strategy to control the relative motion of this formation using only one compensa...

It is known that the synthesis of the relevant control law is performed and appropriate control devices are selected for specific tasks of controlling relative spacecraft motion. Flywheels, control moment gyroscopes, electromagnetic devices with permanent magnets and micro-jet engines are used as actuators in controlling the orientation and stabili...

The study has considered the possibility of creating an aeromagnetic system for removing space debris from low Earth orbits. The peculiarity of the design of the aeromagnetic deorbiting system is the use of magnetic controls for the relative position of the aerodynamic element with permanent rotary magnets that are shielded with the help of special...

According to the concept of active debris removal, named “ion beam shepherd”, a shepherd satellite must be controlled to move at a certain small distance in front of a space debris object during the de-orbiting phase. Due to the considerable duration of this phase, the propellant consumption is a key driver for the control system design. As shown i...

The article is devoted to the improvement of the technology for contactless space debris removal called "Ion Beam Shepherd". The control law has been synthesized to maintain the required position of the shepherd spacecraft relative to the space debris object in the orbital plane by changing the thrust of only one compensating ion thruster in a cert...

The book is devoted to a promising technology for contactless removal of space debris, dubbed “ion beam shepherd”. Dynamic models to simulate and study the motion of the “shepherd” and the space debris object during its contactless de-orbiting are presented. Simplified analytical models have been developed to calculate the ion beam impact. Algorith...

The article deals with the feasibility of aerodynamic compensator application in the scheme of the so-called noncontact method of space garbage collection on the low near-earth orbits without mechanical contact of the spacecraft and space garbage. Previously, in relation to one of the technologies for implementing such method of collection, referre...

Introduction. The research deals with the development of a spacecraft control system for contactless space debris removal using the “ion beam shepherd” technology. Such a system is necessary to provide conditions for effective transfer of decelerating impulse to a space debris object by ion beam in the deorbiting phase. Problem Statement. The desig...

The “ion beam shepherd” is a recently proposed concept for removing space debris in a contactless manner. A shepherd satellite must be controlled to move at a certain small distance in front of a space debris object during the de-orbiting phase. Because of the considerable duration of this phase, the propellant consumption is a key requirement for...

Introduction. The research deals with the development of a spacecraft control system for contactless space debris removal using the “ion beam shepherd” technology. Such a system is necessary to provide conditions for effective transfer of decelerating impulse to a space debris object by ion beam in the deorbiting phase. Problem Statement. The desig...

Монография посвящена перспективной технологии бесконтактного удаления космического мусора, получившей название «Пастух с ионным лучом». Проведен краткий анализ различных аспектов проблемы космического мусора. Рассмотрены различные методы и средства предотвращения образования космического мусора и активного его удаления. Представлены модели динамики...

The goal of the paper is to analyze the robustness of the system to control the "ion beam shepherd" motion with respect to a space debris object. The robustness is analyzed considering the time-varying and parametric uncertain plant in the presence of the ion beam and orbital perturbations, sensor noise, actuation errors, taking into account limita...

The study objective is to synthesize a motion controller for an ion beam shepherd with respect to space debris object during its contactless de-orbiting. It is assumed that the control system has sensors for measuring the shepherd attitude with respect to space debris. Hydrazine thrusters with thrust pulse-width modulation have been used as actuato...

A simplified approach to determine the impact on a space-debris object (a target) from the ion thruster of a spacecraft (a shepherd), which was proposed before in the context the ion beam shepherd technology for space debris removal, was considered. This simplified approach is based on the assumption of the validity of the self-similar model of the...

A simplified approach to determine the impact on a space-debris object (a target) from the ion thruster of a spacecraft (a shepherd), which was proposed before in the context the ion beam shepherd technology for space debris removal, was considered. This simplified approach is based on the assumption of the validity of the self-similar model of the...

An approach to determine the force transmitted by the plasma plume of an ion thruster to an orbital object immersed in it using its central projection on a selected plane is proposed. A photo camera is used to obtain the image of the object central projection. The algorithms for the calculation of the transmission of momentum by the impacting ion b...

Рассмотрена задача использования тетраэдральной схемы установки гиродинов для управления ориентацией и стабилизации космических аппаратов. Для такой схемы установки получены численные значения параметров, характеризующих ориентацию осей подвеса рамок гиродинов. Определены положения осей вращения роторов гиродинов при их первом включении. The prob...