- Pontypridd, UK
- +44 747 012 6240
Nickolay Zosimovych
Xi'an Jiaotong-Liverpool University, Robotics, Department Member
- Shantou University, Mechatronics, Faculty MemberUniversity of South Wales, Faculty of Computing, Engineering and Science, Faculty Memberadd
Research Interests:
In this article has been proposed an analog model and a new algorithm for random distribution of hard spheres in space (hard disks on the plane), which is applicable to any distribution of particle diameters and volume concentrations up... more
In this article has been proposed an analog model and a new algorithm for random distribution of hard spheres in space (hard disks on the plane), which is applicable to any distribution of particle diameters and volume concentrations up to the maximum possible corresponding to close packing of the particles. The proposed method is called the method of viscous suspension. There has been conducted a simulation of the structure of heterogenous condensed mixtures (HCM) containing one or two monodisperse particles in a wide range of their volume concentrations. We determined the main statistical characteristics describing the internal structure of HCM. It has been shown that the method of viscous suspension allows simulating an appearance of regular structures when the volume concentration of the particles is close to the maximum possible corresponding close packing. It has been demonstrated that the contact particles make in HCM extensive clusters, whose dimensions increase with the increase of volume concentration of the particles.
Research Interests:
Research Interests:
Background: A novel missile guidance law that works effectively for highly maneuverable targets is the major requirement of defense technique. To meet this requirement multi-controller architecture for guidance of missiles has been... more
Background: A novel missile guidance law that works effectively for highly maneuverable targets is the major
requirement of defense technique. To meet this requirement multi-controller architecture for guidance of
missiles has been developed in this paper. A fussy logic-based system is designed to choose the proper control
law for suitable range and closing velocity. The proportional navigational law, ON-OFF controller and fuzzy
proportional navigational law are selected for the design of guidance scheme.
Materials and Methods: If the line-of-sight angles are not small, the large relative acceleration along line of
site vector, or the target perform evasive maneuvers, then intercept performance of proportional navigation can
be seriously degraded. Fuzzy logic system can use knowledge expressed in the form of linguistic rules without
completely resorting to the precise plant models. Moreover, fuzzy logic can solve complex and practical
problems using if-then rules.
Results: The fuzzy guidance law is based on the observation that the classical proportional navigation guidance
law achieves target interception using only the line-of-sight rate measurements. This fact implies that it should
be possible to guide the missile towards the target by applying a few fuzzy logics online-of-sight measurements.
The advantage of including rate of change of LOS angle rate as another input-error signal is the earlier than
proportional navigation guidance law.
Conclusion: In the fuzzy logic controller, different phases of the missile target engagement and the respective
needs of the control commands for the stages have been observed. These observations show that there are many
laws which give excellent performance for different stages. Using this information multi controller architecture
for guidance scheme has been proposed.
Key Word: Guidance; control; fuzzy logic; missile.
requirement of defense technique. To meet this requirement multi-controller architecture for guidance of
missiles has been developed in this paper. A fussy logic-based system is designed to choose the proper control
law for suitable range and closing velocity. The proportional navigational law, ON-OFF controller and fuzzy
proportional navigational law are selected for the design of guidance scheme.
Materials and Methods: If the line-of-sight angles are not small, the large relative acceleration along line of
site vector, or the target perform evasive maneuvers, then intercept performance of proportional navigation can
be seriously degraded. Fuzzy logic system can use knowledge expressed in the form of linguistic rules without
completely resorting to the precise plant models. Moreover, fuzzy logic can solve complex and practical
problems using if-then rules.
Results: The fuzzy guidance law is based on the observation that the classical proportional navigation guidance
law achieves target interception using only the line-of-sight rate measurements. This fact implies that it should
be possible to guide the missile towards the target by applying a few fuzzy logics online-of-sight measurements.
The advantage of including rate of change of LOS angle rate as another input-error signal is the earlier than
proportional navigation guidance law.
Conclusion: In the fuzzy logic controller, different phases of the missile target engagement and the respective
needs of the control commands for the stages have been observed. These observations show that there are many
laws which give excellent performance for different stages. Using this information multi controller architecture
for guidance scheme has been proposed.
Key Word: Guidance; control; fuzzy logic; missile.
Research Interests:
This paper depicts the progress of an appliance of Artificial Intelligence (AI) for Unmanned Aerial System (UAS) control. This job was done as part of the conditions for lectures and labs in AI at the School of Robotics, and a beginning... more
This paper depicts the progress of an appliance of Artificial Intelligence (AI) for Unmanned Aerial System (UAS) control. This job was done as part of the conditions for lectures and labs in AI at the School of Robotics, and a beginning project platform for research projects at Xi'an Jiaotong-Liverpool University for a flexible, healthy, and intelligent unmanned aerial vehicle (UAV) mission control system. A method is outlined which allows a base level application for applying an artificial intelligence method, fuzzy logic, to aspects of control logic for UAV flight. The benefits of using fuzzy logic for a movement planner were shown in this research: a small number of failures, near-optimal pathways, and low control attempts. It is these benefits that make it a nice tool for additional improvement. Some elements of UAV flight, automated direction, altitude is held, and prevention of dynamic obstacles, have been implemented and results analysis displayed. Certain potential clear future works that were not investigated in this study are motion-planning in three dimensions, prevention of dynamic obstacles, and more robust analysis.
Research Interests:
Research Interests:
Current aircraft systems, which are mostly established on wired links are intricate, complex to road, heavy and more susceptible to damage as they should be. In this case most existing and perspective aircraft structures and their... more
Current aircraft systems, which are mostly established on wired links are intricate, complex to road, heavy and more susceptible to damage as they should be. In this case most existing and perspective aircraft structures and their subsystems require periodic and scheduled inspection and maintenance functions. Hence, structural examining is vital, and it has a gigantic capacity to reduce the costs related to these processes. In this case the Kalman filter method is extremely helpful in the kinematic fusion procedure. Through extremely dynamic aircraft systems are continuous in time, the Kalman method is mainly applied. In this article the author studies the notion of integrating the magnitude into the data-fusion, as update as filtering procedure and find a developed and superior evaluation of the state. Accordingly, data update and state-propagation algorithms were used. Due to traditional inference methods for decision making or fusion does not sustain the practice of a priori data...
Research Interests:
Research Interests:
This paper surveys and estimates the potential of one-unit CubeSat platform and reflects about design a more suitable platform for future CubeSats. During CubeSat platform development, the concept of the design process is formulated and... more
This paper surveys and estimates the potential of one-unit CubeSat platform and reflects about design a more suitable platform for future CubeSats. During CubeSat platform development, the concept of the design process is formulated and standard physical relationships are proposed to find number of optimal design solution in terms of basic limitations and features compatibility. Specifically, new modular structure is proposed in order to allows flexible subsystems settlement. A design analysis is also presented concerning the CubeSat platform manufacturing technique. A CubeSat structure has been realized by using a rapid prototyping technique. Such choice allows to optimize a CubeSat design, manufacture, and - assembly.
Research Interests:
Research Interests:
In this book was considered and modeled the design objectives for an integrated guidance system of a commercial launch vehicle with application of GPS technologies. Has been set the launch vehicle conceptual design for inject small... more
In this book was considered and modeled the design objectives for an integrated guidance system of a commercial launch vehicle with application of GPS technologies. Has been set the launch vehicle conceptual design for inject small artificial Earth satellites into low and medium circular orbits. The conceptual design of the integrated navigation system based on GPS technology involves determination of its structure, models and algorithms, providing the required accuracy and reliability in injecting payloads with due regard to restrictions on weight and dimensions of the system. 1. Zosimovych Nickolay. Commercial Launch Vehicle Design, LAP LAMBERT Academic Publishing, 2016, 184 p., ISBN-10: 3659953512, EAN: 9783659953514 https://www.lap-publishing.com/
Research Interests:
This publication suggests how we can improve the spacecraft centre of mass movement stabilization accuracy in the active phases of trajectory correction. It will be during interplanetary and transfer flights, which in some cases provides... more
This publication suggests how we can improve the spacecraft centre of mass movement stabilization accuracy in the active phases of trajectory correction. It will be during interplanetary and transfer flights, which in some cases provides for high navigation accuracy, when rigid trajectory control method is used. The required stability conditions obtained are consistent with the known criteria in the invariant theory. Computer modelling shows that in a partially invariant stabilization system reveals the significant advantages of such a system in terms of greater accuracy when compared to known stabilization systems.
Research Interests:
Frequencies of natural longitudinal oscillations of liquid at the inlet to the service feed line were calculated for a spherical fuel tank installed in a spacecraft. The authors are also developed a structural scheme for the spacecraft... more
Frequencies of natural longitudinal oscillations of liquid at the inlet to the service feed line were calculated for a spherical fuel tank installed in a spacecraft. The authors are also developed a structural scheme for the spacecraft orientation system and synthesized continuous regulators in the frequency and time domains.
The publication suggests how to significantly improve the spacecraft centre of mass movement stabilization accuracy in the active phases of trajectory correction during interplanetary and transfer flights, which in some cases provides for... more
The publication suggests how to significantly improve the spacecraft centre of mass movement stabilization accuracy in the active phases of trajectory correction during interplanetary and transfer flights, which in some cases provides for high navigation accuracy, when rigid trajectory control method is used. The required stability conditions obtained are consistent with the known criteria in the invariant theory. Computer modelling shows that in a partially invariant stabilization system reveals the significant advantages of such a system in terms of greater accuracy when compared to known stabilization systems.
Research Interests:
This article aims at studying sounding rocket (SR) class, or those vehicles launched from the earth and carrying out various experiments at high altitudes. After the end of their mission, rockets should deliver a payload to a given point... more
This article aims at studying sounding rocket (SR) class, or those vehicles launched from the earth and carrying out various experiments at high altitudes. After the end of their mission, rockets should deliver a payload to a given point or to give range. In general, design tasks are divided into direct and inverse ones. This paper focuses on direct designing tasks. In this respect, the set values are maximum range, payload mass and restrictions on the sounding rocket construction. As a result, a SR general design technique is proposed. This technique includes selection of the SR initial parameters, the number of stages, the relative weights of the fuel components, the specific thrust of the engines for each stage and the initial transverse load on the SR. After selecting the fuel composition, engine design features and rocket as an object, the starting mass can be represented as a complex mathematical function. Moreover, predetermined maximum range, rocket payload, selected fuel c...
Research Interests:
The increase of sounding rocket active part of trajectory compared to the “normal” can be due to the launches of ballistic flying vehicle for the maximum specified range. In this case, rockets should use propulsion systems with a... more
The increase of sounding rocket active part of trajectory compared to the “normal” can be due to the launches of ballistic flying vehicle for the maximum specified range. In this case, rockets should use propulsion systems with a relatively low fuel specific impulse. This effect also occurs in case of implementation of minimum scattering programs during launches at intermediate ranges (between the minimum and maximum mission ranges). In proposed research was developed methods for analysing the influencing of ballistic and navigation support the uncertain factors on the accuracy of sounding rocket motion with an extended active part of trajectory and was given a relevant assessment to the contribution of each component in relation to specific cases of their occurrence.
Research Interests:
Research Interests:
In most of the known spacecraft stabilization systems the control signal in the centre of mass movement channel is generated according to proportional plus integral control law, based on the measurements of tangential velocity of the... more
In most of the known spacecraft stabilization systems the control signal in the centre of mass movement channel is generated according to proportional plus integral control law, based on the measurements of tangential velocity of the centre of mass and its integral-linear drift. In the angular stabilization channel, the control signal shall be generated in proportion to the spacecraft deviation angle in the transverse plane and the angular velocity of the spacecraft rotation in this plane. In practice, a spacecraft’s stabilization system, which is partially invariant to the disturbing moment, is the easiest to implement. The velocity performance limitation of the control actuator has the most influence upon stability of the system among all the nonlinearities considered in the mathematical modelling. Therefore, we shall consider a model of an invariant stabilization system with due regard to nonlinearity. For the system under consideration, it is possible to construct lines of equal...
Research Interests:
Research Interests:
Research Interests:
A MODEL OF DYNAMICS OF A CONSTELLATION OF NAVIGATION SATELLITES In the article has been chosen and modeled integrated guidance system of a commercial launch vehicle with application of GPS technologies. For this was set methodology... more
A MODEL OF DYNAMICS OF A CONSTELLATION OF NAVIGATION SATELLITES In the article has been chosen and modeled integrated guidance system of a commercial launch vehicle with application of GPS technologies. For this was set methodology simulation of dynamics of a constellation of navigation satellites. Under researching was developed process of simulation of the dynamics of the spacecraft constellation, providing the process of functioning integrated navigation system of the launch vehicle.
In this article have been modeled the inertial navigation system with integrating schemes for a commercial launch vehicle. Has been set a technical problem of the conceptual design of an integrated navigation system for the space launch... more
In this article have been modeled the inertial navigation system with integrating schemes for a commercial launch vehicle. Has been set a technical problem of the conceptual design of an integrated navigation system for the space launch vehicle qualified to inject small artificial Earth satellites into low and medium circular orbits with application of GPS technologies.
В монографии на основании методов структурно-параметрической оптимизации силовых конструкций анализируются общие вопросы проектирования внешнего облика и системы управления беспилотного летательного аппарата для оперативного... more
В монографии на основании методов структурно-параметрической оптимизации силовых конструкций анализируются общие вопросы проектирования внешнего облика и системы управления беспилотного летательного аппарата для оперативного природоресурсного и экологического мониторинга окружающей среды. Методика включает аэробаллистическое проектирование, проектирование информационно-управляющих моделей наземного комплекса управления, математическое моделирование управляющих воздействий оператора в процессе управления (адаптивных и цифровых систем). Технологические основы проектирования конструкций содержат основные направления повышения качества внешних поверхностей и выбор допусков на наружные поверхности беспилотных летательных аппаратов.
Design Objectives for a Commercial Launch Vehicle with Integrated Guidance System Nickolay Zosimovych1, Anatoly Voytsytskyy2 In the article has been proposed the design objectives for an integrated guidance system of a commercial launch... more
Design Objectives for a Commercial Launch Vehicle with Integrated Guidance System Nickolay Zosimovych1, Anatoly Voytsytskyy2 In the article has been proposed the design objectives for an integrated guidance system of a commercial launch vehicle with application of GPS technologies. Was set a technical problem of the conceptual design of an integrated navigation system for the space launch vehicle qualified to inject small artificial Earth satellites into low and medium circular orbits. The conceptual design of the integrated navigation system based on GPS technology involves determination of its structure, models and algorithms, providing the required accuracy and reliability in injecting payloads with due regard to restrictions on weight and dimensions of the system.
Modeling the Integrated Guidance System of a Commercial Launch Vehicle. In the article has been chosen and modeled the design objectives for an integrated guidance system of a commercial launch vehicle with application of GPS... more
Modeling the Integrated Guidance System of a Commercial Launch Vehicle. In the article has been chosen and modeled the design objectives for an integrated guidance system of a commercial launch vehicle with application of GPS technologies. Was set the conceptual design of an integrated navigation system for the space launch vehicle qualified to inject small artificial Earth satellites into low and medium circular orbits. The conceptual design of the integrated navigation system based on GPS technology involves determination of its structure, models and algorithms, providing the required accuracy and reliability in injecting payloads with due regard to restrictions on weight and dimensions of the system.
Research Interests:
ABSTRACT Nickolay Zosimovych National Aviation University, Kyiv, Ukraine SIMULATION OF THE INTEGRATED ONBOARD SYSTEM FOR A COMMERCIAL LAUNCH VEHICLE In the article has been chosen and modeled integrated guidance system of a commercial... more
ABSTRACT Nickolay Zosimovych National Aviation University, Kyiv, Ukraine SIMULATION OF THE INTEGRATED ONBOARD SYSTEM FOR A COMMERCIAL LAUNCH VEHICLE In the article has been chosen and modeled integrated guidance system of a commercial launch vehicle with application of GPS technologies. Under researching was developed process of simulation of the dynamics of the spacecraft constellation, providing the process of functioning integrated navigation system of the launch vehicle by using object-oriented approach. Keywords: Guidance, Launch Vehicle (LV), Onboard Integrated Control System (OICS), Inertial Navigation System (INS), Global Positioning System (GSP), gyro, satellite, constellation, Gravitational Potential of the Earth (GPE), Sun, Moon, pseudorange, pseudovelocity, object-oriented approach (OOA).
In this article have been proposed the design objectives for an integrated guidance system of a commercial launch vehicle with application of GPS technologies and has been set a technical problem of the conceptual design of an integrated... more
In this article have been proposed the design objectives for an integrated guidance system of a commercial launch vehicle with application of GPS technologies and has been set a technical problem of the conceptual design of an integrated navigation system for the space launch vehicle qualified to inject small artificial Earth satellites into low and medium circular orbits. The conceptual design of the integrated navigation system based on GPS technology involves determination of its structure, models and algorithms, providing the required accuracy and reliability in injecting payloads with due regard to restrictions on weight and dimensions of the system.
Research Interests:
Research Interests:
Research Interests:
The CubeSat design process is comprised of choice of its trajectory, determination of components and main parameters of its systems, development of external and internal layouts, determination of the number of satellite-born antennas and... more
The CubeSat design process is comprised of choice of its trajectory, determination of components and main parameters of its systems, development of external and internal layouts, determination of the number of satellite-born antennas and their main characteristics. The potential of CubeSat has prompted the scientific community to rethink the existing spacecraft technologies, and think about how to make them suitable for CubeSats. In terms of specialization of engineering works during SmallSats development, was formulated concept of the design process and recognized physical relationships to find some optimal design solution about compatibility of basic parameters and characteristics. The purpose of SmallSats rational design is to create a project of a vehicle for which the value of the selected criterion is close to the maximum or minimum value. As a result, the design algorithm version was making.
Research Interests:
Research Interests:
Research Interests:
Research Interests:
Research Interests:
This paper proposes a communication system for nanosatellite Earth observation preliminary design technique as useful tools for managing and improving various aspects of regional and national resources. Under analysis was proposed a... more
This paper proposes a communication system for nanosatellite Earth observation preliminary design technique as useful tools for managing and improving various aspects of regional and national resources. Under analysis was proposed a design process for the low Earth orbit nanosatellite communication system. In proposed paper, there have been formulated and solved next goals: reviewed Earth observation systems and studied their design parameters, analyzed the on-board antennas design background and provided analytical estimations, such as design a passband quadrature phase shift keying transmitter and receiver in Simulink, was obtained a bit error rate curves by using a Simulink/MathWorks, generated an offset quadrature phase shift keying waveform and investigated their characteristics, observed and analyzed the diagrams, constellation, and the signal trajectories of quadrature phase shift keying according contemporary design concept. As a result, this allows to propose innovative communication system design techniques applied for the nanosatellite category.
Research Interests:
This article aims at studying sounding rocket (SR) class, or those vehicles launched from the earth and carrying out various experiments at high altitudes. After the end of their mission, rockets should deliver a payload to a given point... more
This article aims at studying sounding rocket (SR) class, or those vehicles launched from the earth and carrying out various experiments at high altitudes. After the end of their mission, rockets should deliver a payload to a given point or to give range. In general, design tasks are divided into direct and inverse ones. This paper focuses on direct designing tasks. In this respect, the set values are maximum range, payload mass and restrictions on the sounding rocket construction. As a result, a SR general design technique is proposed. This technique includes selection of the SR initial parameters, the number of stages, the relative weights of the fuel components, the specific thrust of the engines for each stage and the initial transverse load on the SR. After selecting the fuel composition, engine design features and rocket as an object, the starting mass can be represented as a complex mathematical function. Moreover, predetermined maximum range, rocket payload, selected fuel components, structural design, materials, design parameters allow for a definite SR weight determination. Finally, overall and power characteristics of the SR are proposed within this technique. Such characteristics are accepted as design parameters. Index Terms-Rocket, design, structure, parameter, sounding rocket, solid rocket motor (SRM), liquid rocket motor (LRM).
This paper surveys and estimates the potential of one-unit CubeSat platform and reflects about design a more suitable platform for future CubeSats. During CubeSat platform development, the concept of the design process is formulated... more
This paper surveys and estimates the potential of one-unit CubeSat platform and reflects about design a more
suitable platform for future CubeSats. During CubeSat platform development, the concept of the design process is formulated
and standard physical relationships are proposed to find number of optimal design solution in terms of basic limitations and
features compatibility. Specifically, new modular structure is proposed in order to allows flexible subsystems settlement. A
design analysis is also presented concerning the CubeSat platform manufacturing technique. A CubeSat structure has been
realized by using a rapid prototyping technique. Such choice allows to optimize a CubeSat design, manufacture, and -assembly.
suitable platform for future CubeSats. During CubeSat platform development, the concept of the design process is formulated
and standard physical relationships are proposed to find number of optimal design solution in terms of basic limitations and
features compatibility. Specifically, new modular structure is proposed in order to allows flexible subsystems settlement. A
design analysis is also presented concerning the CubeSat platform manufacturing technique. A CubeSat structure has been
realized by using a rapid prototyping technique. Such choice allows to optimize a CubeSat design, manufacture, and -assembly.
Research Interests:
In this research defines the preliminary design - synthesis of a general visual inspection system of quadrotor type, for remote sensing of landscapes. It was shown that as a flying vehicle, the quadrotor has respectable place among... more
In this research defines the preliminary design - synthesis of a general visual inspection
system of quadrotor type, for remote sensing of landscapes. It was shown that as a flying
vehicle, the quadrotor has respectable place among vertical take-off and landing vehicles for
this purpose. Was made definition unmanned aerial system configuration according design
constraints. After analysis was proposed and described unmanned aerial system, selected
for this request. For chosen system was made close-range camera calibration, studied image
features such as Harris Corners which can serve as a compact image representation for
remote sensing of landscapes.
system of quadrotor type, for remote sensing of landscapes. It was shown that as a flying
vehicle, the quadrotor has respectable place among vertical take-off and landing vehicles for
this purpose. Was made definition unmanned aerial system configuration according design
constraints. After analysis was proposed and described unmanned aerial system, selected
for this request. For chosen system was made close-range camera calibration, studied image
features such as Harris Corners which can serve as a compact image representation for
remote sensing of landscapes.
Research Interests:
This publication suggests how we can improve the spacecraft centre of mass movement stabilization accuracy in the active phases of trajectory correction. It will be during interplanetary and transfer flights, which in some cases provides... more
This publication suggests how we can improve the spacecraft centre of mass movement stabilization accuracy in the active phases of trajectory correction. It will be during interplanetary and transfer flights, which in some cases provides for high navigation accuracy, when rigid trajectory control method is used. The required stability conditions obtained are consistent with the known criteria in the invariant theory. Computer modelling shows that in a partially invariant stabilization system reveals the significant advantages of such a system in terms of greater accuracy when compared to known stabilization systems.
Research Interests:
This paper is devoted to the study of CubeSat rational designing technique. The CubeSat design process is comprised of choice of its trajectory, determination of components and main parameters of its systems, development of external and... more
This paper is devoted to the study of CubeSat rational designing technique. The CubeSat design process is comprised of choice of its trajectory, determination of components and main parameters of its systems, development of external and internal layouts, determination of the number of satellite-born antennas and their main characteristics. The potential of CubeSat has prompted the scientific community to rethink the existing spacecraft technologies and think about how to make them suitable for CubeSats. In terms of specialization of engineering works during Smallsat development, was formulated concept of the design process and recognized physical relationships to find some optimal design solution about compatibility of basic parameters and characteristics. The purpose of Smallsat rational design is to create a project of a vehicle for which the value of the selected criterion is close to the maximum or minimum value. As a result, the design algorithm version was making. The described method of rational design, of course, does not deny the process of intuitive creative thinking. This process reveals itself in assumptions and development of reference versions, as well as in ballistic design.
The publication suggests how to significantly improve the spacecraft centre of mass movement stabilization accuracy in the active phases of trajectory correction during interplanetary and transfer flights, which in some cases provides for... more
The publication suggests how to significantly improve the spacecraft centre of mass movement stabilization accuracy in the active phases of trajectory correction during interplanetary and transfer flights, which in some cases provides for high navigation accuracy, when rigid trajectory control method is used. The required stability conditions obtained are consistent with the known criteria in the invariant theory. Computer modelling shows that in a partially invariant stabilization system reveals the significant advantages of such a system in terms of greater accuracy when compared to known stabilization systems.
Research Interests:
The publication suggests how to significantly improve the spacecraft center of mass movement stabilization accuracy in the active phases of trajectory correction during interplanetary and transfer flights, which in some cases provides for... more
The publication suggests how to significantly improve the spacecraft center of mass movement
stabilization accuracy in the active phases of trajectory correction during interplanetary and transfer flights,
which in some cases provides for high navigation accuracy, when rigid trajectory control method is used. In
order to improve the accuracy of the synthesized algorithms, we propose the application of self-configuring
elements, which turn the operating device and X-axis of the spacecraft at angles recorded at the end of the
previous active phase before a new active phase begins.
stabilization accuracy in the active phases of trajectory correction during interplanetary and transfer flights,
which in some cases provides for high navigation accuracy, when rigid trajectory control method is used. In
order to improve the accuracy of the synthesized algorithms, we propose the application of self-configuring
elements, which turn the operating device and X-axis of the spacecraft at angles recorded at the end of the
previous active phase before a new active phase begins.
Research Interests:
The publication suggests how to significantly improve the spacecraft center of mass movement stabilization accuracy in the active phases of trajectory correction during interplanetary and transfer flights, which in some cases provides for... more
The publication suggests how to significantly improve the spacecraft center of mass movement stabilization accuracy in the active phases of trajectory correction during interplanetary and transfer flights, which in some cases provides for high navigation accuracy, when rigid trajectory control method is used. Keywords:-Space probe (SP), stabilization controller (SC), on-board computer (OC), gyro-stabilized platform (GSP), propulsion system (PS), angular velocity sensor (AVS), operating device (OD), space vehicle (SV), feedback (FB), control actuator (CA), control system (CS), angular stabilization (AS), center of mass (CM).
Research Interests:
Keywords: Parametric optimization (PO), technical system (TS), flying vehicle (FV), design and development (D&D), structural optimization (SO), mathematical model (MM), standard theoretical solutions (STS), engineering design solutions... more
Keywords: Parametric optimization (PO), technical system (TS), flying vehicle (FV), design and development (D&D), structural optimization (SO), mathematical model (MM), standard theoretical solutions (STS), engineering design solutions (EDS), elementary design base (EDB), airframe, prescribed form method (PFM), structure and parameter optimization (SPO), essential features (EF), matrix, finite difference method (FDM), stress-strain behavior (SSB), prescribed form method (DSM).
Research Interests:
In most of the known spacecraft stabilization systems the control signal in the centre of mass movement channel is generated according to proportional plus integral control law, based on the measurements of tangential velocity of the... more
In most of the known spacecraft stabilization systems the control signal in the centre of mass movement channel is generated according to proportional plus integral control law, based on the measurements of tangential velocity of the centre of mass and its integral-linear drift. In the angular stabilization channel, the control signal shall be generated in proportion to the spacecraft deviation angle in the transverse plane and the angular velocity of the spacecraft rotation in this plane. In practice, a spacecraft's stabilization system, which is partially invariant to the disturbing moment, is the easiest to implement. The velocity performance limitation of the control actuator has the most influence upon stability of the system among all the nonlinearities considered in the mathematical modelling. Therefore, we shall consider a model of an invariant stabilization system with due regard to nonlinearity. For the system under consideration, it is possible to construct lines of equal values of the auto oscillation amplitude in a two-parameter plane. The study of the stability of the proposed partially invariant stabilization system revealed that it is possible to ensure sufficient stability margins in the system under consideration by choosing parameters for the stabilization controller. At the same time, it allows to provide high quality of the transition process.
Research Interests:
The present study predicts the flow field and the pressure distribution for a laminar flow in the gap between a stationary and a rotating disk. The fluid enters the gap between two concentric disks at the centre of the disks and diverges... more
The present study predicts the flow field and the pressure distribution for a laminar flow in the gap between a stationary and a rotating disk. The fluid enters the gap between two concentric disks at the centre of the disks and diverges to the outer periphery. The closed form solutions for radial velocity, tangential velocity and pressure are obtained by simplifying the Navier Stokes equations. The velocity and pressure distributions are compared with the experimental data of other investigators. The theoretical and the experimental results are found in good agreement. The present solutions deviate from the experimental results at high rotational Reynolds number. The flow separation has been predicted near the stationery disk due to the effect of centrifugal force.
Research Interests:
In this book was considered and modeled the design objectives for an integrated guidance system of a commercial launch vehicle with application of GPS technologies. Has been set the launch vehicle conceptual design for inject small... more
In this book was considered and modeled the design objectives for an integrated guidance system of a commercial launch vehicle with application of GPS technologies. Has been set the launch vehicle conceptual design for inject small artificial Earth satellites into low and medium circular orbits. The conceptual design of the integrated navigation system based on GPS technology involves determination of its structure, models and algorithms, providing the required accuracy and reliability in injecting payloads with due regard to restrictions on weight and dimensions of the system.
1. Zosimovych Nickolay. Commercial Launch Vehicle Design, LAP LAMBERT Academic Publishing, 2016, 184 p., ISBN-10: 3659953512, EAN: 9783659953514
https://www.lap-publishing.com/
1. Zosimovych Nickolay. Commercial Launch Vehicle Design, LAP LAMBERT Academic Publishing, 2016, 184 p., ISBN-10: 3659953512, EAN: 9783659953514
https://www.lap-publishing.com/
Research Interests:
Lecture notes (Part-1)_Design for Aeronautical Engineering. For 2nd year Aeronautical Engineering students. Instructor - Dr Nickolay Zosimovych. USW, 2016.
Research Interests:
Lec-1-3: Avionics (RPG Collinson book) Dr N Zosimovych
Research Interests:
Lec-1-3: Avionics_(RPG Collinson book)_Dr N Zosimovych
Research Interests:
Lec-1-3: Avionics_(RPG Collinson book)_Dr N Zosimovych