bluuebunny/crossref_metadata_2025_split huggingface dataset:
Optimization of ekranoplane flight control over the waved sea
Authors: Nebylov A V , Knyazhsky A Yu , Nebylov V A 
Published: November 2020

Abstract
The paper proposes to minimize the average altitude of the ekranoplane due to the desire to circumvent the low-periodic components of sea waves with smooth vertical maneuvers. To evaluate the effectiveness of the proposed method for optimizing the trajectory, a model was developed consisting of four blocks: simulation of sea waves, simulation of the operation of the measurement and control system of a ekranoplane, modeling the dynamics of the movement of an UAV, and evaluating the effectiveness of altitude minimization. The simulation results showed the possibility of reducing the average altitude of ekranoplane by 0.65m in 6-point sea waves. Also, the overload caused by vertical maneuvers did not exceed 0.16 g, which is acceptable for the transportation of most goods and people
Analysis of the influence of the error of the nanosatellite design and dynamic performances on the quality of angular motion control processes
Authors: Belokonov I V , Kramlikh A V , Melnik M E 
Published: November 2020

Abstract
By the nanosatellite angular motion control in this research is meant terminal control based on inverse dynamics problem solution using the Bellman’s optimality principle. The impact of the error of the nanosatellite design and dynamic performances, which are torques of inertia, attitude angles and angular rates, on the quality of angular motion control processes (i.e. on the accuracy of its reorientation), is investigated. The results of numerical simulation are given through the example of the nanosatellite of the SamSat family.
Taking into account constraints on magnitude and first derivative of the Global Navigation Satellite Systems differential corrections during their forecasting
Authors: Zaitsev O V 
Published: November 2020

Abstract
Algorithms for predicting differential corrections to GNSS measurements have been developed, the low labor intensity of which allows them to be applied in real time. The processing of corrections before the break is performed using the Kalman filter in reverse time. The interval of processed corrections gradually expands as the forecast duration increases. Based on the results of experiments with field GNSS data, a comparison of the algorithms efficiency was made.
Accuracy improvement for GNSS -based compass
Authors: Shafran S V , Kudryavtsev I A 
Published: November 2020

Abstract
To calculate relative position of two navigation antennas with a relatively short baseline phase measurements are commonly used. This approach is associated with technical difficulties related to the synchronization of receivers and resolution of phase ambiguities. Double phase differences of eliminate these errors and therefore allow to calculate the azimuth with better accuracy. Proposed algorithm for phase ambiguities resolution consists of three steps: applying double phase difference model insensitive to full phase due to the usage of cosine function, secondly using differential evolution method to fit model to observation by varying orientation angles and finally computing phase ambiguities from roughly estimated angles. To reduce the phase centre shift influence on azimuth computation error, the correction function depending on navigation signal arrival angles was introduced. To find its numerical values, the experiment with rigidly fixed antennas was carried out. Its idea was to take into account the relative movement of navigation satellites in fixed antenna system. Development of a multi-antenna navigation receiver with an additional channel for calculating phase ambiguities is described.
Application of the polynomial filtering algorithm to identification of the narrowband process parameters
Authors: Vasiliev V A 
Published: November 2020

Abstract
A polynomial filtering algorithm has been implemented to identify the central frequency and correlation interval of a narrowband process. The efficiency of the polynomial filtering algorithm is carried out by comparing it with the potential accuracy calculated using the algorithm based on multi-alternative filtering. Recurrent relations are proposed for determining the lower bound of accuracy for estimating the parameters of a narrowband process. The possibility of using less computationally expensive procedures for calculating the lower bound of accuracy is investigated.
Software-defined Radio GNSS Receiver Signal Tracking Methods
Authors: Kumarin A A , Kudryavtsev I A 
Published: November 2020

Abstract
Software-defined radio (SDR) - based GNSS receivers are flexible. SDR technology allows changing processing algorithms and adding new signals without any hardware modifications. The main drawback of such a receiver is high computation load. Signal tracking module takes most part of CPU time. This paper considers distributed receiver architectures where most of the processing is performed in a remote PC or a server.
The amount of raw data in the SDR receiver is too large for complete transfer. Two methods of reduction are discussed: truncating epochs and disabling tracking for a certain period. The limitations of each method are estimated using simulations. Epochs can be truncated by 50-75% depending on signal-to-noise ratio. The maximum disabling time is about 0.5s for a stationary receiver and 0.1s for a car receiver. Using both methods in combination reduce data volume by 95.4% for a stationary receiver and 83.3% for a car receiver.
Requirements for nanosatellite-mounted GNSS-based instrument measuring ionospheric total electron content
Authors: Nikolaev P N , Kudryavtsev I A , Shafran S V 
Published: November 2020

AbstractA navigation receiver mounted on board of a micro/nanosatellite can be used as part of a scientific instrument for ionospheric study, for instance, identification of patterns in solar-terrestrial links and obtaining a set of statistical data to find the correlation between local fluctuations of the ionosphere and climatic changes. Such a device should produce an array of navigation measurements of carrier phases and pseudoranges, and also calculate on their basis the values of the absolute total electron content (TEC), which are used to study the ionosphere. To calculate the absolute TEC, we use a known technique that combines carrier phase and pseudorange measurements. Taking into account the peculiarities of this technique and the geometry of the measurements, we put forward a number of requirements for a scientific instrument to study the ionosphere.
Nanosatellites Formation Flying Control Approaches Overview
Authors: Ivanov D , Ovchinnikov M , Tkachev S 
Published: November 2020

Abstract
The paper considers various approaches nanosatellites formation flying control, presents dynamic models of the motion of a group of nanosatellites, considers various algorithms for controlling relative angular and translational motions, taking into account the specifics of small satellites and limited inter-satellite communication capabilities. The paper discusses various approaches to the formation flying control, including those using perspective methods that do not require the fuel consumption. With a large number of spacecraft in a group, a new class of space systems appears, defined as a swarm. The main difficulty in implementing a swarm formation flying of satellites is navigation and control of the mutual relative motion of an individual satellite in a swarm, taking into account the fundamental impossibility of having information about the phase state vector of each swarm element. The features of decentralized algorithms for controlling the satellites swarm motion are considered and the dynamics of the swarm is investigated.
Approximate optimal method for controlling the angular motion of a spacecraft as part of an orbital tether system
Authors: Zabolotnov Yu M 
Published: November 2020

Abstract
An approximate optimal method for controlling the movement relative to the center of mass of a spacecraft as part of an orbital tether system is considered. The purpose of the control is to stabilize the spatial angular movement of the spacecraft relative to the direction of the tether connecting it to another spacecraft. If there is no control, the angular movement of the spacecraft relative to the direction of the tether may be unstable. This is primarily due to the disturbances that occur during the formation (deployment) of tether systems, as well as the internal small mass asymmetry of the spacecraft that inevitably occurs during its manufacture. An approximate optimal method for stabilizing the relative motion of a spacecraft on a tether is proposed, based on the Bellman dynamic programming principle and the averaging method. The averaging method is used for approximate solution of the Bellman partial differential equation, which allows in many cases to obtain the regulator’s equations in analytical form. An example of the application of this approach to stabilize the movement of a small spacecraft when deploying an orbital tether system is given.
Stabilization of the rotational motion of a composite nanosatellite with a mobile module mounted on a rotating platform
Authors: Doroshin A V , Eryomenko A V 
Published: November 2020

Abstract
The paper considers the dynamics of the spatial motion of a composite nanosatellite with a movable module making an angular deviation relative to the carrier body. Control laws have been developed to stabilize the rotation of the nanosatellite relative to the longitudinal axis.
Laboratory Study of the Active Debris Removal Algorithms on Air-Bearing Test Bed
Authors: Mahdi Akhloumadi , Filipp Kozin , Ivanov Danil 
Published: November 2020

Abstract
Space debris removal is one of the most important problems in space exploration. This work is devoted to the development and testing of control algorithms for microsatellites mockups on an aerodynamic table. The mock-ups are equipped with thruster’s simulators to control the motion of the center of mass and angular motion on the plane of the table. The aim of the work is to construct a control algorithm using virtual potential functions and apply it to the problems of rendezvous and docking. Simultaneously with these tasks, the problem of avoiding a collision with an object in the event of a dangerous approach not from the docking side is solved. Also the algorithm for autonomous debris observation of the 3U CubeSat is proposed. The results of the control algorithm tests are presented in the paper.
Influence of temperature restrictions on the heliocentric motion controlling of a solar-sailing spacecraft
Authors: Chernyakina I V , Rozhkov M A , Starinova O L 
Published: November 2020

Abstract
Solar sailing spacecraft uses the light pressure to change the trajectory and are most effective in the immediate Sun vicinity, but the sail surface temperature most significant increases in the same area. Therefore, when designing solar sailing “hot” missions, we should consider the temperature restriction when choosing the control laws. The paper proposes the following approach to the implementation of the temperature restriction. When exceeding a predetermined temperature limit values the sail deviates from the direction of the radiation flux so that the direction of the acceleration projection on the Ecliptic plane is not changed, but the total sail orientation angle increased. The additional acceleration that occurs when using this approach, directed along the Ecliptic normal, can be used to rotate the orbital plane, if this is necessary to fulfill the flight purpose or to form a cylindrical orbit.
Analysis of the deployment of a three-mass tethered satellite formation
Authors: Chen Shumin , Li Aijun , Wang Changqing 
Published: November 2020

Abstract
Tethered satellite formation has obtained widespread attention in recent years. The main causes of the increasing study interest around tethered formation lie in its promised applications in space, such as interferometric measurements. The deployment of a tethered formation system in low Earth orbit is investigated in this paper. The orbital tethered system consists of three nanosatellites connected via tethers end-to-end, and the desired arrangement for the end masses is an equilateral triangle. For the sake of brevity, the formation system is modeled as a particle-rigid rod system, in which the elasticity of the tethers is omitted. The deployment process is carried out using tension forces and active external forces generated by low-thrust engines. The numerical results confirm that it is possible to deploy a triangular tethered system, which rotates at a given initial angular velocity, to an expected arrangement using the proposed control law of tether tensions and active forces.
Motion control of a space robot at launching and approaching a geostationary satellite
Authors: Starinova O , Somov Ye , Butyrin S 
Published: November 2020

Abstract
The problems of putting a space robot into a geostationary orbit using a combined scheme and its approach to an information geostationary satellite are considered. When approaching, the robot’s attitude and orbit control system uses an electric propulsion unit, a propulsion system based on eight electro-catalytic reaction engines with pulse-width modulation of their thrust, and a gyroscopic moment cluster based on four single gimbal control moment gyroscopes (gyrodines). Numerical results are presented that demonstrate the effectiveness of the developed discrete guidance and control algorithms.
Investigation and selection of a functional in the problem of synthesis of an optimal control law providing inspection motion
Authors: Shcherbakov M.S. , Ananev A.V. , Avariaskin D.P. 
Published: November 2020

Abstract
In this paper we consider the problem of keeping a nanosatellite near the nominal inspection ellipse, which is the Hill ellipse. The source of the disturbing effect, leading to the deformation of the nominal trajectory, is the drag of the atmosphere and the nonlinearity of the central attraction field. Using the traditional approach to finding the control law in the form of a linear-quadratic controller does not always meet the specified requirements, since it is based on the formation of a control law based on a linearized model of motion dynamics. The method of control law synthesis in the form of a linear-quadratic controller, using a quasilinear model of motion (SDRE-method), allows to increase the accuracy of the implementation of the inspection motion. In this work, a study was carried out to select the parameters of the quadratic quality criterion from the conditions to provide the requirements for energy costs and the quality of implementation of the inspection motion.
Control system and optimization of parameters of a closed biosystem the size of a pico-satellite
Authors: Mastalieva V A , Perliouk V V 
Published: November 2020

Abstract
The paper researched the sustainable functioning of the closed self-regulating biological system based on macrophytes Fucus vesiculosus, Fucus inflatus, Laminaria saccharina and Chlorella vulgaris. The authors describe the methods and apparatus for monitoring the composition and control of biological experiments with such a system, which is offered to spend on board the International Space Station (ISS). We also consider the option of the experiment on board the small satellite. The main task of automatically controlled experiment is to ensure the long-term functioning of the isolated biological system under conditions of weightlessness. Based on the analysis of the interaction structure of the main components of biological systems under study was developed a mathematical model of a closed biological system on the basis of aquatic organisms and holds its computer simulation, with which defined the conditions for the forecast can be carried out and state control investigated the conditions of maintaining it stable life. We consider the automated control system of a biological system, providing its stable operation. The main indicator of the functioning of biological systems encouraged to use the amount of oxygen in the air section and dissolved in water. As a biological control system parameters used by the lighting level and temperature of the water environment. In the experiment on autonomous spacecraft (microsatellite) proposed to manage the dampers in the heat-insulating sheath. The dependencies for defining the threshold oxygen concentration at which a correction of the control parameters.
Analysis and design of halo orbits in cislunar space
Authors: Chongrui D , Fain M K , Starinova O L 
Published: November 2020

Abstract
This paper examines the formation of halo-orbits by a spacecraft around L1 and L2 libration points of the Earth-Moon system. Perturbations from the gravitation of the Sun and the non-centrality of the gravitational fields of the Moon and the Earth are taken into account (LP165p model). The proposed perturbed model is an intermediate stage between the dynamic model of the three bodies of the Earth-Moon system and the high-precision non-periodic ephemeris model. The paper proposes two strategies for maintaining halo orbits. The first is to use a small impulse performed on each half of the orbit. The second is to use continuation methods to form a periodic orbit that does not require additional corrections. The essence of the second strategy is to use the perturbation periodicity to generate a special multi-circular halo orbit resonating with the perturbation period. The results of these two approaches are presented for various perturbed models.
Support subspace method and conforming estimation in autonomous navigation tasks
Authors: Fursov V A , Minaev E Y , Kotov A P , Zherdev D A 
Published: November 2020

Abstract
The article discusses the technology of autonomous navigation by optical observations. A scheme based on the recognition of three-dimensional landmarks is considered. To improve the accuracy and reliability of recognition, a survey model is constructed for each landmark. When calculating the parameters of this model, the most conformed data is selected. The problem of recognition is solved using the method of support subspaces. Support subspaces are formed from a set of vectors of each reference landmark. An important advantage of the technology is the ability to refine the landmark models based on the results of current observations during operation.
Functional and test diagnosis of onboard systems using dynamic models
Authors: Lukoyanov E V , Gruzlikov A M , Kolesov N V 
Published: November 2020

Abstract
The paper discusses the problems of troubleshooting in onboard computing and control systems. Herewith the approaches based on the methods of functional and test diagnostics are analyzed. Both approaches involve the introduction of redundancy, which in fact is a dynamic software model of the systems being diagnosed. In the case of functional diagnostics, a full-fledged model is used that forms the basis for diagnostic observers; in the case of test diagnostics, it is a simplified event model.
Application of artificial intelligence technology in the nanosatellite attitude determination problem
Authors: Belokonov I V , Kramlikh A V , Melnik M E 
Published: November 2020

Abstract
The paper proposes an approach of the nanosatellite attitude determination problem solution using elements of artificial intelligence technology. This approach consists in the reconfiguration of the algorithms of the nanosatellite attitude determination problem solution based on the knowledge database that can be enriched to ensure the robustness of the feedback loop (the nanosatellite attitude determination using different combinations of different types of measurement information by various algorithms). This research results are presented in relation to the nanosatellite of the SamSat family: values of measurement significance coefficients are chosen; then generalized algorithm significance coefficients are calculated for various combinations of operable measuring means using chosen coefficients.
Sensitivity analysis for filtering with preliminary processing of measurements
Authors: Titov R , Motorin A 
Published: November 2020

Abstract
The sensitivity of estimation algorithms to the parameters of the preliminary filter is analyzed, using the problem of gravity anomaly estimation using a damped gravimeter as an example. Two models for preliminary filter are considered, which corresponds the models for gravimeter sensitive element in the example. First is a physically substantiated elastic pendulum model. Second is its simplified version in the form of a first-order system model. The results of the sensitivity analysis of gravity anomaly estimation accuracy to the models are presented.
Procedure of experimental evaluation of nanoclass spacecraft design parameters using the ground test equipment
Authors: Belokonov I V , Kliuchnik V N , Barinova E V , Ivliev A V , Boltov E A 
Published: November 2020

Abstract
As it is impossible to set high accuracy of the initial data for theoretical calculations of the design parameters, such as the mass-centering and inertial characteristics of nanosatellites, the problem of experimental determination of their actual values arises. For a number of reasons, the devices designed for large spacecraft are not appropriate for the small ones. This paper describes a device developed at Samara University for measuring the center of mass coordinates and moments of inertia specifically for CubeSat nanosatellites, as well as a technology for experimental evaluation of the design parameters of nanoclass spacecraft. The accuracy of determining the design parameters using the proposed device is confirmed by a series of experiments with standards.
Probabilistic analysis of maneuvering nanosatellites with electrothermal propulsion system
Authors: Sinitsin L I , Belokonov I V 
Published: November 2020

Abstract
A method is proposed for assessing the results of correction maneuvers for a nanosatellite (NS) with an electrothermal propulsion system (ETPS). Common causes of maneuvering errors associated with technological errors in creation of the propulsion system and the nanosatellite as a whole are revealed by an example of the SamSat-M NS being under development. The analysis of the NS maneuvering process was carried out in a probabilistic setting. A factor analysis is carried out and the contribution of the design parameters of the NS and ETPS to the spread of the projections of the velocity increase vector of the NS motion and the arising angular motion is determined.