Pub Date : 2017-02-28DOI: 10.15866/IREASE.V10I1.10998
A. Eid, Reyad Abdel-Fadil, M. Abdel-Salam
In this paper, a More-Electric Aircraft (MEA) power distribution system is modeled and controlled using Model Predictive Control (MPC). The MPC has a fast response to dynamic changes and able to deal with multivariable and constraints applied to inputs and states. The studied MEA system is investigated during a transient condition of severe step-load changes (from no-load to full-load) and fault scenarios. The MPC control takes into consideration the verification of aircraft standards during transient and fault conditions for the AC and DC voltages within the aircraft distribution system. The performance of the studied MEA is improved compared to other control techniques such as FLC and PID controllers. The power quality of the studied system under MPC is compared to FLC and PID and it is found the superiority of the MPC regarding overshoot/undershoot, ripples, settling time and harmonic contents. Moreover, the obtained results verify the capability and efficiency of MPC control during severe conditions of large step-load and fault scenarios inside the MEA by verifying the aircraft standards during all operating conditions.
{"title":"Performance and Power Quality Improvements of MEA Power Distribution Systems using Model Predictive Control","authors":"A. Eid, Reyad Abdel-Fadil, M. Abdel-Salam","doi":"10.15866/IREASE.V10I1.10998","DOIUrl":"https://doi.org/10.15866/IREASE.V10I1.10998","url":null,"abstract":"In this paper, a More-Electric Aircraft (MEA) power distribution system is modeled and controlled using Model Predictive Control (MPC). The MPC has a fast response to dynamic changes and able to deal with multivariable and constraints applied to inputs and states. The studied MEA system is investigated during a transient condition of severe step-load changes (from no-load to full-load) and fault scenarios. The MPC control takes into consideration the verification of aircraft standards during transient and fault conditions for the AC and DC voltages within the aircraft distribution system. The performance of the studied MEA is improved compared to other control techniques such as FLC and PID controllers. The power quality of the studied system under MPC is compared to FLC and PID and it is found the superiority of the MPC regarding overshoot/undershoot, ripples, settling time and harmonic contents. Moreover, the obtained results verify the capability and efficiency of MPC control during severe conditions of large step-load and fault scenarios inside the MEA by verifying the aircraft standards during all operating conditions.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"25 1","pages":"31-41"},"PeriodicalIF":0.0,"publicationDate":"2017-02-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"88436648","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 : 2017-01-01DOI: 10.15866/IREASE.V10I4.12589
Tarek N. Dief, Mohamed M. Kamra, S. Yoshida
In this paper, a strategy for the preliminary design of Quad-Rotor problem with emphasis on utilizing system identification methods for system modeling. The algorithm of forgetting least square is applied for the realtime prediction of the system parameters. The presented strategy is applied to the mass-varying tethered Quad-Rotor. The presented system identification method provides the model parameters while the adaptive (Proportional, Integral, Derivative, and Accelerator) PID-A controller controls the system response in real-time flight. In this paper, a mathematical model for the Quad-Rotor is derived. The sensitivity analys is of the system is provided in detail. Then, a system identification algorithm is applied to study the change in parameters during flight. PID-A controller is designed to stabilize the system with mass-varying consideration. Finally, Simulation results of the full system are presented.
{"title":"Modeling, system identification and PID-A controller for tethered unmanned quad-rotor helicopter","authors":"Tarek N. Dief, Mohamed M. Kamra, S. Yoshida","doi":"10.15866/IREASE.V10I4.12589","DOIUrl":"https://doi.org/10.15866/IREASE.V10I4.12589","url":null,"abstract":"In this paper, a strategy for the preliminary design of Quad-Rotor problem with emphasis on utilizing system identification methods for system modeling. The algorithm of forgetting least square is applied for the realtime prediction of the system parameters. The presented strategy is applied to the mass-varying tethered Quad-Rotor. The presented system identification method provides the model parameters while the adaptive (Proportional, Integral, Derivative, and Accelerator) PID-A controller controls the system response in real-time flight. In this paper, a mathematical model for the Quad-Rotor is derived. The sensitivity analys is of the system is provided in detail. Then, a system identification algorithm is applied to study the change in parameters during flight. PID-A controller is designed to stabilize the system with mass-varying consideration. Finally, Simulation results of the full system are presented.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"24 1","pages":"215-223"},"PeriodicalIF":0.0,"publicationDate":"2017-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"81460010","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 : 2016-12-31DOI: 10.15866/IREASE.V9I6.10774
M. Alias, A. Rafie, S. Wiriadidjaja
Efforts in this century for Unmanned Aerial Vehicle, UAV aerodynamic technology led to a broad of applications. Currently, UAV users are demanding of small, unprepared field or even no field for the aircraft to take off and landing operation. Aligned for the needs, several studies revealed the feasibility of rotating cylinders produced lifting which will impact the improvement of on lift coefficient. Magnus effect on rotating cylinder has the potential as a good lift generator. The studies have discovered the limitation on implementation discovered caused by induced and parasite drag occurrences. Accordingly, rotational rate, α, and Reynold number, Re, are the highlight in this study. The previous experimental and numerical data were used as a basis to compare the results. The methodological approach used for this research in order to prove the presence of Magnus effect, Finite Element Numerical Analysis method in form of 2D numerical is chosen and the simulation done by using ANSYS FLUENT R15.0 to examine the coefficient of lift, drag and understand the aerodynamic characteristics of the rotating cylinder surfaced body. Previous experimental studies carried out by Elliott G. Reid simulated on-design in 2D numerical analysis for validation. The results obtained showed 90.6% accuracy for the validation where the cylinder size to be tested was smaller compared to on-design size. The cylinder size of 30mm as adapted to J. Seifert studies on Magnus effect is used to compare the original size of 114.3mm where the Reynold number tested at the range of 1.17×103 ≤ Re ≤ 1.69×105 with rotational rate ranging from 0 ≤ α ≤ 4.32 determined by air velocity range within 5 ms-1 ≤ U ≤ 15 ms-1. Lift coefficient, CL and drag coefficient, CD determined in every stage analysis were recorded. The results obtained showed that the lift coefficient is slightly lower compared to the original size of cylinder at U are 5ms-1, 7ms-1, 10 ms-1 and 15 ms-1. However, the drag coefficient showed higher value U of 15 ms-1 and 10 ms-1 but lower at U of 5 ms-1 and 7 ms-1.
{"title":"Two Dimensional Numerical Study of Aerodynamic Characteristic for Rotating Cylinder at High Reynolds Number","authors":"M. Alias, A. Rafie, S. Wiriadidjaja","doi":"10.15866/IREASE.V9I6.10774","DOIUrl":"https://doi.org/10.15866/IREASE.V9I6.10774","url":null,"abstract":"Efforts in this century for Unmanned Aerial Vehicle, UAV aerodynamic technology led to a broad of applications. Currently, UAV users are demanding of small, unprepared field or even no field for the aircraft to take off and landing operation. Aligned for the needs, several studies revealed the feasibility of rotating cylinders produced lifting which will impact the improvement of on lift coefficient. Magnus effect on rotating cylinder has the potential as a good lift generator. The studies have discovered the limitation on implementation discovered caused by induced and parasite drag occurrences. Accordingly, rotational rate, α, and Reynold number, Re, are the highlight in this study. The previous experimental and numerical data were used as a basis to compare the results. The methodological approach used for this research in order to prove the presence of Magnus effect, Finite Element Numerical Analysis method in form of 2D numerical is chosen and the simulation done by using ANSYS FLUENT R15.0 to examine the coefficient of lift, drag and understand the aerodynamic characteristics of the rotating cylinder surfaced body. Previous experimental studies carried out by Elliott G. Reid simulated on-design in 2D numerical analysis for validation. The results obtained showed 90.6% accuracy for the validation where the cylinder size to be tested was smaller compared to on-design size. The cylinder size of 30mm as adapted to J. Seifert studies on Magnus effect is used to compare the original size of 114.3mm where the Reynold number tested at the range of 1.17×103 ≤ Re ≤ 1.69×105 with rotational rate ranging from 0 ≤ α ≤ 4.32 determined by air velocity range within 5 ms-1 ≤ U ≤ 15 ms-1. Lift coefficient, CL and drag coefficient, CD determined in every stage analysis were recorded. The results obtained showed that the lift coefficient is slightly lower compared to the original size of cylinder at U are 5ms-1, 7ms-1, 10 ms-1 and 15 ms-1. However, the drag coefficient showed higher value U of 15 ms-1 and 10 ms-1 but lower at U of 5 ms-1 and 7 ms-1.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"2015 1","pages":"208-215"},"PeriodicalIF":0.0,"publicationDate":"2016-12-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"89058280","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 : 2016-12-31DOI: 10.15866/IREASE.V9I6.10893
F. Ismagilov, V. Vavilov, L. E. Roginskaya, S. Semen, D. Gusakov
This paper examines the problem of the installation of the electric machine to the high pressure shaft to increase the electrification of aircraft engines and create More Electrical Engine. Different ways of synchronous generator integration in the aircraft engine by worldwide aircraft engines manufacturers was discussed. A new design of the high temperature synchronous generator mounted on high pressure shaft is proposed. To evaluate the effectiveness of synchronous generator the electromagnetic, thermal and mechanical calculations are made. High temperature synchronous generator cooling system was designed and system of mechanical decoupling of the stator at short circuits is proposed.
{"title":"Design of High Temperature Six-Phase Starter-Generator Embedded in Aerospace Engine","authors":"F. Ismagilov, V. Vavilov, L. E. Roginskaya, S. Semen, D. Gusakov","doi":"10.15866/IREASE.V9I6.10893","DOIUrl":"https://doi.org/10.15866/IREASE.V9I6.10893","url":null,"abstract":"This paper examines the problem of the installation of the electric machine to the high pressure shaft to increase the electrification of aircraft engines and create More Electrical Engine. Different ways of synchronous generator integration in the aircraft engine by worldwide aircraft engines manufacturers was discussed. A new design of the high temperature synchronous generator mounted on high pressure shaft is proposed. To evaluate the effectiveness of synchronous generator the electromagnetic, thermal and mechanical calculations are made. High temperature synchronous generator cooling system was designed and system of mechanical decoupling of the stator at short circuits is proposed.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"39 1","pages":"216-225"},"PeriodicalIF":0.0,"publicationDate":"2016-12-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"90587419","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 : 2016-12-31DOI: 10.15866/IREASE.V9I6.10929
F. Ismagilov, L. Roginskaya, S. Shapiro, V. Vavilov, R. Karimov, V. Ayguzina
{"title":"Integrated Electrical Machines with Permanent Magnets for Aerospace Industry","authors":"F. Ismagilov, L. Roginskaya, S. Shapiro, V. Vavilov, R. Karimov, V. Ayguzina","doi":"10.15866/IREASE.V9I6.10929","DOIUrl":"https://doi.org/10.15866/IREASE.V9I6.10929","url":null,"abstract":"","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"12 1","pages":"226"},"PeriodicalIF":0.0,"publicationDate":"2016-12-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"90436782","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 : 2016-12-31DOI: 10.15866/IREASE.V9I6.10364
A. Bajpai, E. Rathakrishnan
The mixing efficiency of limiting tabs of three geometries with triangular corrugations, in promoting the mixing of a Mach 2 elliptic jet has been studied. Limiting tabs of rectangular, triangular and circular-arc geometries with 5% blockage are placed along major and minor axis at the nozzle exit are tested for nozzle pressure ratio from 4 to 8 in steps of one. All the tabs are found to be efficient mixing promoter at all tested NPRs, when placed along major axis at the nozzle exit. However at NPR 4 and 5 circular-arc tab along minor axis is found to retard the near field jet mixing. But the corrugated rectangular tab along minor axis is found to be the best mixing promoter among tested geometries. It causes a maximum reduction of 89% in core length at NPR 6. The corresponding core length reduction for corrugated triangular and circular-arc tab is 78% and 84% respectively. The maximum reduction in core length obtained for corrugated triangular and circular arc tab is found when placed along major axis at the exit of elliptical nozzle. The shadowgraph pictures of the jet reveal that the waves prevailing in the elliptic jet controlled with corrugated limiting tabs along major axis are significantly weaker than those in uncontrolled and controlled (with tabs along minor axis) elliptic jet.
{"title":"Corrugated Limiting Tab for Supersonic Jet Mixing","authors":"A. Bajpai, E. Rathakrishnan","doi":"10.15866/IREASE.V9I6.10364","DOIUrl":"https://doi.org/10.15866/IREASE.V9I6.10364","url":null,"abstract":"The mixing efficiency of limiting tabs of three geometries with triangular corrugations, in promoting the mixing of a Mach 2 elliptic jet has been studied. Limiting tabs of rectangular, triangular and circular-arc geometries with 5% blockage are placed along major and minor axis at the nozzle exit are tested for nozzle pressure ratio from 4 to 8 in steps of one. All the tabs are found to be efficient mixing promoter at all tested NPRs, when placed along major axis at the nozzle exit. However at NPR 4 and 5 circular-arc tab along minor axis is found to retard the near field jet mixing. But the corrugated rectangular tab along minor axis is found to be the best mixing promoter among tested geometries. It causes a maximum reduction of 89% in core length at NPR 6. The corresponding core length reduction for corrugated triangular and circular-arc tab is 78% and 84% respectively. The maximum reduction in core length obtained for corrugated triangular and circular arc tab is found when placed along major axis at the exit of elliptical nozzle. The shadowgraph pictures of the jet reveal that the waves prevailing in the elliptic jet controlled with corrugated limiting tabs along major axis are significantly weaker than those in uncontrolled and controlled (with tabs along minor axis) elliptic jet.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"26 1","pages":"180-194"},"PeriodicalIF":0.0,"publicationDate":"2016-12-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"83265020","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 : 2016-12-31DOI: 10.15866/IREASE.V9I6.10041
A. Anwar, M. M. Osman
The polyimide performance was monitored and evaluated after exposure to ionized and particulate radiation as a space hazard. The material was irradiated with three different doses 500, 750 and 1000kGy in CO60 source in the presence of air. Both non-irradiated and irradiated materials were characterized by tensile test, Thermo-Gravimetric Analysis (TGA) and Fourier Transform Infra-Red (FTIR). Quantum modeling was executed by using "Gaussian 5" software program for chemical structure verification. The non-irradiated material showed a super ductility but revealed a brittle behavior when irradiated with 500 and 1000 kGy gamma doses. Nevertheless, the material attained moderate ductility when exposed to 750kGy. Results by the stated characterization tools matched with the evaluated behavior and confirmed by the quantum modeling.
{"title":"Influence of Simulated Space Hazards on Polyimide ArtilonTM Type Used in Space Applications","authors":"A. Anwar, M. M. Osman","doi":"10.15866/IREASE.V9I6.10041","DOIUrl":"https://doi.org/10.15866/IREASE.V9I6.10041","url":null,"abstract":"The polyimide performance was monitored and evaluated after exposure to ionized and particulate radiation as a space hazard. The material was irradiated with three different doses 500, 750 and 1000kGy in CO60 source in the presence of air. Both non-irradiated and irradiated materials were characterized by tensile test, Thermo-Gravimetric Analysis (TGA) and Fourier Transform Infra-Red (FTIR). Quantum modeling was executed by using \"Gaussian 5\" software program for chemical structure verification. The non-irradiated material showed a super ductility but revealed a brittle behavior when irradiated with 500 and 1000 kGy gamma doses. Nevertheless, the material attained moderate ductility when exposed to 750kGy. Results by the stated characterization tools matched with the evaluated behavior and confirmed by the quantum modeling.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"33 1","pages":"195-199"},"PeriodicalIF":0.0,"publicationDate":"2016-12-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"88637162","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 : 2016-10-31DOI: 10.15866/IREASE.V9I5.10391
A. Ceruti, Tiziano Bombardi, L. Piancastelli
This paper describes a handheld application to help pilots when entering degraded visibility conditions. In this case, the loss of control is a typical emergency situation from which a pilot should be able to recover, but often he/she doesn’t do owing to problems of situation awareness. A new instrument, based on the use of accelerometers/GPS equipping modern handheld devices has been designed, virtually tested in flight simulators and finally tested in flight. Attention has been given to show essential information in a very simple and intuitive way, so that the instrument can be useful in case of pilot disorientation, panic or high stress levels. After a testing phase, the instrument showed useful to provide an indication about the attitude of the plane and to provide the pilot an indication of the stick and throttle movements needed to restore a safe levelled flight. The use of this application by pilots in emergency situation can enhance the survivability in Instrument Meteorological Conditions also without a specific training. This paper shows how the high computation capability and advanced visualization devices typical of smartphones can be useful to increase the flight safety by developing a new class of emergency not-certified instruments. A further testing phase of the instrument in critical conditions like gusty environment or deteriorated weather will be carried out as a future development of this work to better evaluate the limits of the instrument herein described.
{"title":"Visual Flight Rules Pilots Into Instrumental Meteorological Conditions: a Proposal for a Mobile Application to Increase In-flight Survivability","authors":"A. Ceruti, Tiziano Bombardi, L. Piancastelli","doi":"10.15866/IREASE.V9I5.10391","DOIUrl":"https://doi.org/10.15866/IREASE.V9I5.10391","url":null,"abstract":"This paper describes a handheld application to help pilots when entering degraded visibility conditions. In this case, the loss of control is a typical emergency situation from which a pilot should be able to recover, but often he/she doesn’t do owing to problems of situation awareness. A new instrument, based on the use of accelerometers/GPS equipping modern handheld devices has been designed, virtually tested in flight simulators and finally tested in flight. Attention has been given to show essential information in a very simple and intuitive way, so that the instrument can be useful in case of pilot disorientation, panic or high stress levels. After a testing phase, the instrument showed useful to provide an indication about the attitude of the plane and to provide the pilot an indication of the stick and throttle movements needed to restore a safe levelled flight. The use of this application by pilots in emergency situation can enhance the survivability in Instrument Meteorological Conditions also without a specific training. This paper shows how the high computation capability and advanced visualization devices typical of smartphones can be useful to increase the flight safety by developing a new class of emergency not-certified instruments. A further testing phase of the instrument in critical conditions like gusty environment or deteriorated weather will be carried out as a future development of this work to better evaluate the limits of the instrument herein described.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"27 10 1","pages":"144-151"},"PeriodicalIF":0.0,"publicationDate":"2016-10-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"84653111","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 : 2016-10-31DOI: 10.15866/IREASE.V9I5.10432
F. Ismagilov, V. Vavilov, V. Bekuzin, V. Ayguzina
{"title":"High-Speed Magneto-Electric Slotless Generator, Integrated into Auxiliary Power Unit: Design and Experimental Research of a Scaled-Size Prototype","authors":"F. Ismagilov, V. Vavilov, V. Bekuzin, V. Ayguzina","doi":"10.15866/IREASE.V9I5.10432","DOIUrl":"https://doi.org/10.15866/IREASE.V9I5.10432","url":null,"abstract":"","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"209 1","pages":"173"},"PeriodicalIF":0.0,"publicationDate":"2016-10-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"72698374","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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