Pub Date : 2020-05-01DOI: 10.23919/icins43215.2020.9133811
E. Barinova, I. Belokonov, I. Timbai
This paper considers the space motion relative to the center of mass of a CubeSat nanosatellite on a low circular orbit under the aerodynamic moment. The possibility of resonant modes of motion due to their inherent form factor of a rectangular parallelepiped and the presence of a small mass asymmetry (a transverse displacement of the center of mass from the axis of symmetry) is analyzed. We obtained the formulas for determining the critical value of the longitudinal angular velocity of a nanosatellite, at which the conditions for the appearance of resonances are satisfied. It is also shown the possibility of a roll resonance when the nanosatellite faces the incoming stream with one side edge and the average angular velocity of its own rotation is close to zero.
{"title":"Study of Resonant Modes of Cubesat Nanosatellite Motion under the Influence of the Aerodynamic Moment","authors":"E. Barinova, I. Belokonov, I. Timbai","doi":"10.23919/icins43215.2020.9133811","DOIUrl":"https://doi.org/10.23919/icins43215.2020.9133811","url":null,"abstract":"This paper considers the space motion relative to the center of mass of a CubeSat nanosatellite on a low circular orbit under the aerodynamic moment. The possibility of resonant modes of motion due to their inherent form factor of a rectangular parallelepiped and the presence of a small mass asymmetry (a transverse displacement of the center of mass from the axis of symmetry) is analyzed. We obtained the formulas for determining the critical value of the longitudinal angular velocity of a nanosatellite, at which the conditions for the appearance of resonances are satisfied. It is also shown the possibility of a roll resonance when the nanosatellite faces the incoming stream with one side edge and the average angular velocity of its own rotation is close to zero.","PeriodicalId":127936,"journal":{"name":"2020 27th Saint Petersburg International Conference on Integrated Navigation Systems (ICINS)","volume":"21 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-05-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134234769","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2020-05-01DOI: 10.23919/icins43215.2020.9133844
Y. Somov, S. Butyrin, S. Somov
A new method of autonomous angular guidance and attitude control of satellite in the tracking mode using reference model of changes in the vector of modified Rodrigues parameters is presented.
{"title":"Autonomous Angular Guidance and Attitude Control of an Information Satellite in the Tracking Mode","authors":"Y. Somov, S. Butyrin, S. Somov","doi":"10.23919/icins43215.2020.9133844","DOIUrl":"https://doi.org/10.23919/icins43215.2020.9133844","url":null,"abstract":"A new method of autonomous angular guidance and attitude control of satellite in the tracking mode using reference model of changes in the vector of modified Rodrigues parameters is presented.","PeriodicalId":127936,"journal":{"name":"2020 27th Saint Petersburg International Conference on Integrated Navigation Systems (ICINS)","volume":"33 5","pages":"1-5"},"PeriodicalIF":0.0,"publicationDate":"2020-05-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141207503","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2020-05-01DOI: 10.23919/icins43215.2020.9133897
V. Shiryaev, Darya Klepach, A. Romanova
A dynamic system, in particular a spacecraft, for which the task of combining information from sensors of navigation systems arises, is considered. Inertial navigation system and star sensor are used as the main navigation systems. The algorithm of guaranteed evaluation when combining the information of inertial navigation system and star sensor is proposed. When solving the estimation problem using a minimax filter, constructing an information set that is guaranteed to contain the true state of the system is a computationally difficult task for large-dimensional systems. That's why instead of exact construction of information sets their approximate value is used, i.e. approximation in the form of convex polyhedron obtained by approximation from above of “exact” but set implicitly by the system of linear equations and inequalities of information set. The result of guaranteed estimation is compared with the result of estimation with the Kalman filter.
{"title":"Implementation of the Algorithm for Estimating the State Vector of a Dynamic System in Undefined Conditions","authors":"V. Shiryaev, Darya Klepach, A. Romanova","doi":"10.23919/icins43215.2020.9133897","DOIUrl":"https://doi.org/10.23919/icins43215.2020.9133897","url":null,"abstract":"A dynamic system, in particular a spacecraft, for which the task of combining information from sensors of navigation systems arises, is considered. Inertial navigation system and star sensor are used as the main navigation systems. The algorithm of guaranteed evaluation when combining the information of inertial navigation system and star sensor is proposed. When solving the estimation problem using a minimax filter, constructing an information set that is guaranteed to contain the true state of the system is a computationally difficult task for large-dimensional systems. That's why instead of exact construction of information sets their approximate value is used, i.e. approximation in the form of convex polyhedron obtained by approximation from above of “exact” but set implicitly by the system of linear equations and inequalities of information set. The result of guaranteed estimation is compared with the result of estimation with the Kalman filter.","PeriodicalId":127936,"journal":{"name":"2020 27th Saint Petersburg International Conference on Integrated Navigation Systems (ICINS)","volume":"26 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-05-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114540367","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
The features of the carrier-based aircraft operation under conditions of high sea state were researched. A highly efficient relay algorithm for predicting the pitching parameters of an aircraft carrier's deck has been developed. The algorithm switches the models of various accuracy in a relay manner depending on the forecast horizon. To accomplish prediction, the relay algorithm uses both linear trends and non-linear models constructed by the self-organization algorithm. Linear trends help to complete the prediction as soon as possible. The results of mathematical modeling have showed the effectiveness of the developed relay algorithm in predicting the pitching parameters of an aircraft carrier's deck.
{"title":"Pitching Prediction Algorithm for Landing on Aircraft Carrier Deck","authors":"Zhou Ruiyang, Neysipin Konstantin, Selezneva Maria, Proletarsky Andrey","doi":"10.23919/icins43215.2020.9134026","DOIUrl":"https://doi.org/10.23919/icins43215.2020.9134026","url":null,"abstract":"The features of the carrier-based aircraft operation under conditions of high sea state were researched. A highly efficient relay algorithm for predicting the pitching parameters of an aircraft carrier's deck has been developed. The algorithm switches the models of various accuracy in a relay manner depending on the forecast horizon. To accomplish prediction, the relay algorithm uses both linear trends and non-linear models constructed by the self-organization algorithm. Linear trends help to complete the prediction as soon as possible. The results of mathematical modeling have showed the effectiveness of the developed relay algorithm in predicting the pitching parameters of an aircraft carrier's deck.","PeriodicalId":127936,"journal":{"name":"2020 27th Saint Petersburg International Conference on Integrated Navigation Systems (ICINS)","volume":"228 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-05-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123296240","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2020-05-01DOI: 10.23919/icins43215.2020.9133802
V. Nikiforov, A. Gusev, K. Andreev, S. Osokin, A. Shiryaev, N.P. Stikhareva
This article presents a method of sequential approximations to solve the nonlinear terminal control problem. The “ideal” model of a uniaxial gyrostabilizer is used for the synthesis of the terminal law of control. Components of moment disturbances are presented as uncertainties. The mathematical modeling of terminal control with disturbances was conducted.
{"title":"Using a Method of Sequential Approximations of Uniaxial Gyrostabilizer Model to Solve the Nonlinear Terminal Control Problem","authors":"V. Nikiforov, A. Gusev, K. Andreev, S. Osokin, A. Shiryaev, N.P. Stikhareva","doi":"10.23919/icins43215.2020.9133802","DOIUrl":"https://doi.org/10.23919/icins43215.2020.9133802","url":null,"abstract":"This article presents a method of sequential approximations to solve the nonlinear terminal control problem. The “ideal” model of a uniaxial gyrostabilizer is used for the synthesis of the terminal law of control. Components of moment disturbances are presented as uncertainties. The mathematical modeling of terminal control with disturbances was conducted.","PeriodicalId":127936,"journal":{"name":"2020 27th Saint Petersburg International Conference on Integrated Navigation Systems (ICINS)","volume":"2021 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-05-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123023271","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2020-05-01DOI: 10.23919/icins43215.2020.9133819
Alexey Prohortsov, A. Soloviev, V. Smirnov
Mathematical model of semi-analytic gyrocompassing is considered. Requirements for the elements of the semianalytic gyrocompassing system are estimated.
建立了半解析陀螺仪罗盘的数学模型。估计了半解析陀螺仪罗盘系统的元件要求。
{"title":"Mathematical Model of Semianalytic Gyrocompassing","authors":"Alexey Prohortsov, A. Soloviev, V. Smirnov","doi":"10.23919/icins43215.2020.9133819","DOIUrl":"https://doi.org/10.23919/icins43215.2020.9133819","url":null,"abstract":"Mathematical model of semi-analytic gyrocompassing is considered. Requirements for the elements of the semianalytic gyrocompassing system are estimated.","PeriodicalId":127936,"journal":{"name":"2020 27th Saint Petersburg International Conference on Integrated Navigation Systems (ICINS)","volume":"3 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-05-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122678766","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2020-05-01DOI: 10.23919/icins43215.2020.9134019
A. Kramlikh, I. Lomaka, S. Shafran
This work suggests and investigates method that allows to estimate orbital parameters of the nanosatellite in case of abnormal operation of the on-board navigation equipment. Abnormal operation means the possibility to receive signals from not more than two navigation spacecraft. Abnormal operation of the on-board navigation equipment may be due to the performance degradation of the antenna-feeder system and amplifiers, damage of the navigation equipment during launch, and other reasons leading to the change of the antenna pattern, which prevents from receiving of all accessible signals from the navigation spacecraft.
{"title":"Estimation Method for Nanosatellite Orbital Parameters in Case of Abnormal Operation of Navigation Equipment","authors":"A. Kramlikh, I. Lomaka, S. Shafran","doi":"10.23919/icins43215.2020.9134019","DOIUrl":"https://doi.org/10.23919/icins43215.2020.9134019","url":null,"abstract":"This work suggests and investigates method that allows to estimate orbital parameters of the nanosatellite in case of abnormal operation of the on-board navigation equipment. Abnormal operation means the possibility to receive signals from not more than two navigation spacecraft. Abnormal operation of the on-board navigation equipment may be due to the performance degradation of the antenna-feeder system and amplifiers, damage of the navigation equipment during launch, and other reasons leading to the change of the antenna pattern, which prevents from receiving of all accessible signals from the navigation spacecraft.","PeriodicalId":127936,"journal":{"name":"2020 27th Saint Petersburg International Conference on Integrated Navigation Systems (ICINS)","volume":"246 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-05-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122931352","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2020-05-01DOI: 10.23919/icins43215.2020.9133941
Pham Xuan Truong, N. Konstantin, Selezneva Mariya
The research object of this article is a route correction system of an unmanned aerial vehicle. In order to correct the flight path of the UAV under study, an airborne radar system is used. In the case of active jamming, the radar image cannot be used for route correction. Therefore, the onboard navigation system with algorithm correction is proposed. The error compensation scheme of navigation system is used in the output signal, and the prediction model of system error is constructed by the algorithm. The predictive model is constructed using the genetic algorithm and group method of data handling. The quality of algorithms for constructing predictive model is compared by mathematical model. Algorithmic support that functions with the radar system and in conditions of active interference (these signals are unavailable) for the UAV navigation system has been formed. Correction algorithms for autonomous UAV navigation systems including genetic algorithms and prediction algorithms have been developed. The simulation results prove the performance and efficiency of the developed correction algorithm, which shows that the accuracy of navigation system can be improved and the UAV problems can be solved by using this algorithm.
{"title":"Study of the System of Route Correction of the UAV Navigation System","authors":"Pham Xuan Truong, N. Konstantin, Selezneva Mariya","doi":"10.23919/icins43215.2020.9133941","DOIUrl":"https://doi.org/10.23919/icins43215.2020.9133941","url":null,"abstract":"The research object of this article is a route correction system of an unmanned aerial vehicle. In order to correct the flight path of the UAV under study, an airborne radar system is used. In the case of active jamming, the radar image cannot be used for route correction. Therefore, the onboard navigation system with algorithm correction is proposed. The error compensation scheme of navigation system is used in the output signal, and the prediction model of system error is constructed by the algorithm. The predictive model is constructed using the genetic algorithm and group method of data handling. The quality of algorithms for constructing predictive model is compared by mathematical model. Algorithmic support that functions with the radar system and in conditions of active interference (these signals are unavailable) for the UAV navigation system has been formed. Correction algorithms for autonomous UAV navigation systems including genetic algorithms and prediction algorithms have been developed. The simulation results prove the performance and efficiency of the developed correction algorithm, which shows that the accuracy of navigation system can be improved and the UAV problems can be solved by using this algorithm.","PeriodicalId":127936,"journal":{"name":"2020 27th Saint Petersburg International Conference on Integrated Navigation Systems (ICINS)","volume":"20 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-05-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124191147","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2020-05-01DOI: 10.23919/icins43215.2020.9133905
A. Krylov
The report studies the effect of linear acceleration up to 100g on the readings of a MEMS gyroscope (as a part of IMU). A method for zero offset finding is described, when it is used in the conditions of skews in the places of IMU installation on the rotational stand. The calibration method that takes into account the occurring zero offsets from the acceleration, measured along three axes is proposed. The main results of the developed method application are presented.
{"title":"Technology For Elimination of MEMS Gyroscope Zero Offset under the Influence of Linear Acceleration and the Occurrence of Skewnesses in the Locations of Sensor Block Installation","authors":"A. Krylov","doi":"10.23919/icins43215.2020.9133905","DOIUrl":"https://doi.org/10.23919/icins43215.2020.9133905","url":null,"abstract":"The report studies the effect of linear acceleration up to 100g on the readings of a MEMS gyroscope (as a part of IMU). A method for zero offset finding is described, when it is used in the conditions of skews in the places of IMU installation on the rotational stand. The calibration method that takes into account the occurring zero offsets from the acceleration, measured along three axes is proposed. The main results of the developed method application are presented.","PeriodicalId":127936,"journal":{"name":"2020 27th Saint Petersburg International Conference on Integrated Navigation Systems (ICINS)","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-05-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129825415","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2020-05-01DOI: 10.23919/icins43215.2020.9133957
I. Belokonov, M. S. Shcherbakov
This paper studies passive relative motion of two spacecraft (SC) in one orbital plane taking into account the second zonal harmonic J2 of the Earth gravitational field. Inspector spacecraft moves in the area of the inspection ellipse, in the center of which the target spacecraft is placed. Inspection motion for different orbits is analyzed. Method for selecting the initial conditions of both spacecraft motion that ensure the permissible variation of the inspector SC relative trajectory from nominal one at the given time interval is proposed. Results of the numerical study support the computed stability conditions, which make it possible to reduce the fuel costs for inspection motion.
{"title":"Choosing the Motion Initial Conditions, Ensuring the Technical Sustainability of Spacecraft Formation Flight","authors":"I. Belokonov, M. S. Shcherbakov","doi":"10.23919/icins43215.2020.9133957","DOIUrl":"https://doi.org/10.23919/icins43215.2020.9133957","url":null,"abstract":"This paper studies passive relative motion of two spacecraft (SC) in one orbital plane taking into account the second zonal harmonic J2 of the Earth gravitational field. Inspector spacecraft moves in the area of the inspection ellipse, in the center of which the target spacecraft is placed. Inspection motion for different orbits is analyzed. Method for selecting the initial conditions of both spacecraft motion that ensure the permissible variation of the inspector SC relative trajectory from nominal one at the given time interval is proposed. Results of the numerical study support the computed stability conditions, which make it possible to reduce the fuel costs for inspection motion.","PeriodicalId":127936,"journal":{"name":"2020 27th Saint Petersburg International Conference on Integrated Navigation Systems (ICINS)","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-05-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130271228","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
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