Pub Date : 2019-12-31DOI: 10.15866/irease.v12i6.16666
I. Iswanto, F. Mujaahid, Rohmansyah Rohmansyah, T. A. Nugraha, V. Shekher
{"title":"Quadrotor Tracking Control Based on Optimized Fuzzy Logic Controller","authors":"I. Iswanto, F. Mujaahid, Rohmansyah Rohmansyah, T. A. Nugraha, V. Shekher","doi":"10.15866/irease.v12i6.16666","DOIUrl":"https://doi.org/10.15866/irease.v12i6.16666","url":null,"abstract":"","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"33 1","pages":"261"},"PeriodicalIF":0.0,"publicationDate":"2019-12-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"89303591","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 : 2018-06-30DOI: 10.15866/irease.v11i3.14775
M. Fioriti
{"title":"Innovative Concepts of Electric System Architectures and Hybrid Propulsion System for Regional Turboprop Aircraft","authors":"M. Fioriti","doi":"10.15866/irease.v11i3.14775","DOIUrl":"https://doi.org/10.15866/irease.v11i3.14775","url":null,"abstract":"","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"21 1","pages":"104"},"PeriodicalIF":0.0,"publicationDate":"2018-06-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"90149540","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 : 2018-04-30DOI: 10.15866/IREASE.V11I2.13663
S. Ekpo
The success of the satellite subsystems engineering depends on the optimal design, modeling, simulation, and validation of the deliverables of the conceptual and mission design objectives. This paper presents the operational times analysis of the thermal control subsystem onboard a 97-kg microsatellite in low-Earth orbit during an eclipse period. Power-storing, communication downlink and uplink, payload processing, and thermal control overpower modes were implemented for a communication mission under worst-case orbital patterns. An embedded digital temperature and lighting controller circuitry was designed and practically validated to effect a desired logic. For an average eclipse period of 34.4 mins, the operational times of the thermal subsystem at altitudes of 400 km, 500 km, and 600 km are 38.6 mins, 38.1 mins, and 37.7 mins respectively. Moreover, the thermal control subsystem simulation reveals that reducing the operational times of non-thermal control subsystems during the eclipse period by 50 % can result in an operational factor of safety of over 1.5. At least 10 dB data link transmission margin can be achieved. The reported findings show that the operational times of spacecraft subsystems overpower modes can be reconfigured in orbit to reliably sustain the operating conditions of the capability-based satellite components for ubiquitous communication.
{"title":"Thermal Subsystem Operational Times Analysis for Ubiquitous Small Satellites Relay in LEO","authors":"S. Ekpo","doi":"10.15866/IREASE.V11I2.13663","DOIUrl":"https://doi.org/10.15866/IREASE.V11I2.13663","url":null,"abstract":"The success of the satellite subsystems engineering depends on the optimal design, modeling, simulation, and validation of the deliverables of the conceptual and mission design objectives. This paper presents the operational times analysis of the thermal control subsystem onboard a 97-kg microsatellite in low-Earth orbit during an eclipse period. Power-storing, communication downlink and uplink, payload processing, and thermal control overpower modes were implemented for a communication mission under worst-case orbital patterns. An embedded digital temperature and lighting controller circuitry was designed and practically validated to effect a desired logic. For an average eclipse period of 34.4 mins, the operational times of the thermal subsystem at altitudes of 400 km, 500 km, and 600 km are 38.6 mins, 38.1 mins, and 37.7 mins respectively. Moreover, the thermal control subsystem simulation reveals that reducing the operational times of non-thermal control subsystems during the eclipse period by 50 % can result in an operational factor of safety of over 1.5. At least 10 dB data link transmission margin can be achieved. The reported findings show that the operational times of spacecraft subsystems overpower modes can be reconfigured in orbit to reliably sustain the operating conditions of the capability-based satellite components for ubiquitous communication.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"17 1","pages":"48-57"},"PeriodicalIF":0.0,"publicationDate":"2018-04-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"73430138","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 : 2018-04-30DOI: 10.15866/IREASE.V11I2.13938
V. N. Tyapkin, A. Korovin, V. Nerovny, I. N. Ishchuk, E. Kabulova
This article discusses the joint functioning of satellite radio navigation systems and their augmentations in the form of pseudolite networks under radio interference of various natures and intensities. The achievable precision in determining the coordinates of the object in noisy environments using and considering the estimates of the signal power level of navigational satellites, pseudolites and interference, is an indicator of the effectiveness of such joint systems. The paper refines the model of undisturbed motion of navigation satellites in terms of determining the geocentric coordinates of pseudolites (PL). A model for determining the signal levels of navigation satellites and pseudolites at the input of user equipment (UE) of satellite radio navigation systems (SRNS) was constructed. The algorithm was refined for calculating the mean square error (MSE) to determine coordinates when sharing signals of pseudolites and navigational satellites (NS) in noisy environments. The method was developed and the energy and precision characteristics of SRNS UE operated by NS and PL signals in noisy environments were determined.
{"title":"Characteristics of the Ground-Based User Equipment of Satellite Radio Navigation System Employing Pseudolites in Noisy Environments","authors":"V. N. Tyapkin, A. Korovin, V. Nerovny, I. N. Ishchuk, E. Kabulova","doi":"10.15866/IREASE.V11I2.13938","DOIUrl":"https://doi.org/10.15866/IREASE.V11I2.13938","url":null,"abstract":"This article discusses the joint functioning of satellite radio navigation systems and their augmentations in the form of pseudolite networks under radio interference of various natures and intensities. The achievable precision in determining the coordinates of the object in noisy environments using and considering the estimates of the signal power level of navigational satellites, pseudolites and interference, is an indicator of the effectiveness of such joint systems. The paper refines the model of undisturbed motion of navigation satellites in terms of determining the geocentric coordinates of pseudolites (PL). A model for determining the signal levels of navigation satellites and pseudolites at the input of user equipment (UE) of satellite radio navigation systems (SRNS) was constructed. The algorithm was refined for calculating the mean square error (MSE) to determine coordinates when sharing signals of pseudolites and navigational satellites (NS) in noisy environments. The method was developed and the energy and precision characteristics of SRNS UE operated by NS and PL signals in noisy environments were determined.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"39 1","pages":"58-65"},"PeriodicalIF":0.0,"publicationDate":"2018-04-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"74945547","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 : 2018-04-30DOI: 10.15866/IREASE.V11I2.14098
F. Ismagilov, V. Vavilov, I. Sayakhov
This work presents a new topology for unipolar active magnetic bearings for an aircraft air conditioning system with high-speed electrical machines. A mathematical description of the processes of the new technical solution is given. The new topology was studied using the finite element method. The conducted comparison of this solution with the known ones and the assessment of its efficiency allowed to demonstrate the perspective for its use in the industry as well as to reveal its advantages and disadvantages. Using genetic algorithms, the active magnetic bearings optimum geometrical dimensions were chosen. The results of the conducted mock-up experimental research under static conditions were presented. The characteristics of its bearing capacity dependence on the air gap displacement value were obtained and AMB stiffness was assessed under static conditions at various rotor displacements.
{"title":"Unipolar Magnetic Bearing for High-Speed Electric Motor of Aircraft Air Conditioning System: Structure and Optimization","authors":"F. Ismagilov, V. Vavilov, I. Sayakhov","doi":"10.15866/IREASE.V11I2.14098","DOIUrl":"https://doi.org/10.15866/IREASE.V11I2.14098","url":null,"abstract":"This work presents a new topology for unipolar active magnetic bearings for an aircraft air conditioning system with high-speed electrical machines. A mathematical description of the processes of the new technical solution is given. The new topology was studied using the finite element method. The conducted comparison of this solution with the known ones and the assessment of its efficiency allowed to demonstrate the perspective for its use in the industry as well as to reveal its advantages and disadvantages. Using genetic algorithms, the active magnetic bearings optimum geometrical dimensions were chosen. The results of the conducted mock-up experimental research under static conditions were presented. The characteristics of its bearing capacity dependence on the air gap displacement value were obtained and AMB stiffness was assessed under static conditions at various rotor displacements.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"16 1","pages":"84-95"},"PeriodicalIF":0.0,"publicationDate":"2018-04-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"74752174","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 : 2018-04-30DOI: 10.15866/IREASE.V11I2.13238
A. Sedel'nikov
This paper summarizes results of the pre-statistical manipulation of the Earth magnetic field data received by using the scientific instrument “MAGKOM during the test sample operation of the “AIST”-small spacecraft. Large data-samples were analyzed without in-depth study of some sectors which have been excluded from consideration because of actuating elements and scientific gears operating peculiarities. Some conclusions about the measuring devices operation correctness as well as about the received data key specs have been drawn as part of the study. The way to the future detail metric data analysis has been paved. The performed analysis could be used for the uncontrolled angular motion simulation of the “AIST”-small spacecraft as well as for spacecraft environment microaccelerations estimation.
{"title":"Fast Analysis of Onboard Measurements of the Earth Magnetic Field for the Purpose of Microaccelerations Decrement on Board of the “AIST” Small Spacecraft During its Uncontrolled Orbital Flight","authors":"A. Sedel'nikov","doi":"10.15866/IREASE.V11I2.13238","DOIUrl":"https://doi.org/10.15866/IREASE.V11I2.13238","url":null,"abstract":"This paper summarizes results of the pre-statistical manipulation of the Earth magnetic field data received by using the scientific instrument “MAGKOM during the test sample operation of the “AIST”-small spacecraft. Large data-samples were analyzed without in-depth study of some sectors which have been excluded from consideration because of actuating elements and scientific gears operating peculiarities. Some conclusions about the measuring devices operation correctness as well as about the received data key specs have been drawn as part of the study. The way to the future detail metric data analysis has been paved. The performed analysis could be used for the uncontrolled angular motion simulation of the “AIST”-small spacecraft as well as for spacecraft environment microaccelerations estimation.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"11 1","pages":"76-83"},"PeriodicalIF":0.0,"publicationDate":"2018-04-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"79807101","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 : 2018-04-30DOI: 10.15866/IREASE.V11I2.13365
F. Ismagilov, V. Vavilov, R. Urazbakhtin
In this article, the authors offer a new optimization algorithm for the LSPMSM based on genetic algorithms, as well as the methods for their implementation for the design of electrical machines. With this algorithm, 7 different topologies of the LSPMSM with fixed frequency, network frequency and supply voltage were simultaneously optimized. As a result, about 6000 different combinations of geometric sizes and various topologies of the LSPMSM were considered. After this, two optimal topologies with optimal geometric dimensions for input conditions were identified. The topology data were calculated using FEMM methods and a model of one of them was created.
{"title":"Optimization of Synchronous Electric Motors with Asynchronous Start by Genetic Algorithms","authors":"F. Ismagilov, V. Vavilov, R. Urazbakhtin","doi":"10.15866/IREASE.V11I2.13365","DOIUrl":"https://doi.org/10.15866/IREASE.V11I2.13365","url":null,"abstract":"In this article, the authors offer a new optimization algorithm for the LSPMSM based on genetic algorithms, as well as the methods for their implementation for the design of electrical machines. With this algorithm, 7 different topologies of the LSPMSM with fixed frequency, network frequency and supply voltage were simultaneously optimized. As a result, about 6000 different combinations of geometric sizes and various topologies of the LSPMSM were considered. After this, two optimal topologies with optimal geometric dimensions for input conditions were identified. The topology data were calculated using FEMM methods and a model of one of them was created.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"108 1","pages":"66-75"},"PeriodicalIF":0.0,"publicationDate":"2018-04-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"89008023","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 : 2018-02-28DOI: 10.15866/irease.v11i1.13460
Soukaina Krafes, Z. Chalh, A. Saka
{"title":"Visual Servoing of a Spherical Inverted Pendulum on a Quadrotor Using Backstepping Controller","authors":"Soukaina Krafes, Z. Chalh, A. Saka","doi":"10.15866/irease.v11i1.13460","DOIUrl":"https://doi.org/10.15866/irease.v11i1.13460","url":null,"abstract":"","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"4 1","pages":"6"},"PeriodicalIF":0.0,"publicationDate":"2018-02-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"91428198","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 : 2018-02-28DOI: 10.15866/IREASE.V11I1.13466
A. Kartashev, A. Martynov, O. Mashkov
Increasing efficiency and extending the stable operating range of a turbocharger centrifugal compressor for combustion engine boost is one way to improve engines economical operation indices. In order to increase the centrifugal compressor’s efficiency, this work involves the numerical studies of the flow structure in the most widespread types of vaned diffusers: one-row, two-row, three-row, splitter and wedge diffuser. To confirm the adequacy of the numerical modeling results, the authors verified the design model and formulated recommendations on its settings to ensure the best correspondence between calculation results and experimental data. To extend the stable operating range of the centrifugal compressor, the authors performed numerical and experimental studies of casing treatments - ported shrouds and ring grooves in the shroud. The research findings demonstrated the high efficiency of the ported shroud, which allows the extension of the stable operating range by 4.5%. The authors carried out experimental studies of the influence of the centrifugal compressor diffuser type – vaned and vaneless – on the ported shroud efficiency. The displacement of the surge line is achieved in the configuration with the vaneless diffuser due to the implementation of the ported shroud is 10-12% greater than in the configuration with the vaned diffuser. The article is also of interest for designers of centrifugal compressors of turboshaft and small-sized turbojet engines, for which the problem of increasing the efficiency and extending the stable operating range of the compressor is also actual.
{"title":"Numerical and Experimental Studies of a Turbocharger Centrifugal Compressor for Combustion Engine Boost","authors":"A. Kartashev, A. Martynov, O. Mashkov","doi":"10.15866/IREASE.V11I1.13466","DOIUrl":"https://doi.org/10.15866/IREASE.V11I1.13466","url":null,"abstract":"Increasing efficiency and extending the stable operating range of a turbocharger centrifugal compressor for combustion engine boost is one way to improve engines economical operation indices. In order to increase the centrifugal compressor’s efficiency, this work involves the numerical studies of the flow structure in the most widespread types of vaned diffusers: one-row, two-row, three-row, splitter and wedge diffuser. To confirm the adequacy of the numerical modeling results, the authors verified the design model and formulated recommendations on its settings to ensure the best correspondence between calculation results and experimental data. To extend the stable operating range of the centrifugal compressor, the authors performed numerical and experimental studies of casing treatments - ported shrouds and ring grooves in the shroud. The research findings demonstrated the high efficiency of the ported shroud, which allows the extension of the stable operating range by 4.5%. The authors carried out experimental studies of the influence of the centrifugal compressor diffuser type – vaned and vaneless – on the ported shroud efficiency. The displacement of the surge line is achieved in the configuration with the vaneless diffuser due to the implementation of the ported shroud is 10-12% greater than in the configuration with the vaned diffuser. The article is also of interest for designers of centrifugal compressors of turboshaft and small-sized turbojet engines, for which the problem of increasing the efficiency and extending the stable operating range of the compressor is also actual.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"17 1","pages":"27-38"},"PeriodicalIF":0.0,"publicationDate":"2018-02-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"78765927","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 : 2018-02-28DOI: 10.15866/IREASE.V11I1.13696
O. Şugar‐Gabor
A numerical study of the aerodynamics of a circular cylinder section in proximity to the ground surface was performed, for Mach numbers of 1.5 and 2.9 and ground clearances between 2 and 0.125, non-dimensional with respect to the cylinder diameter. The supersonic flow was computed using a finite-volume Reynolds-averaged Navier-Stokes solver, using adequately stabilized numerical schemes. The flow field computed in ground effect conditions was complex, and significantly varied as a function of both variables. The shape and standoff distance of the detached bow shock were very sensitive to changes in ground clearance. The velocity profile in the gap between the cylinder and ground showed significant interactions between the two boundary layers, and a gradually reduced supersonic expansion close the body surface.
{"title":"Numerical study of the circular cylinder in supersonic ground effect conditions","authors":"O. Şugar‐Gabor","doi":"10.15866/IREASE.V11I1.13696","DOIUrl":"https://doi.org/10.15866/IREASE.V11I1.13696","url":null,"abstract":"A numerical study of the aerodynamics of a circular cylinder section in proximity to the ground surface was performed, for Mach numbers of 1.5 and 2.9 and ground clearances between 2 and 0.125, non-dimensional with respect to the cylinder diameter. The supersonic flow was computed using a finite-volume Reynolds-averaged Navier-Stokes solver, using adequately stabilized numerical schemes. The flow field computed in ground effect conditions was complex, and significantly varied as a function of both variables. The shape and standoff distance of the detached bow shock were very sensitive to changes in ground clearance. The velocity profile in the gap between the cylinder and ground showed significant interactions between the two boundary layers, and a gradually reduced supersonic expansion close the body surface.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"1 1","pages":"15"},"PeriodicalIF":0.0,"publicationDate":"2018-02-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"86111380","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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