Pub Date : 2024-09-17DOI: 10.1177/17568293241281099
{"title":"Corrigendum to “Exploring tandem wing UAS designs for operation in turbulent urban environments”","authors":"","doi":"10.1177/17568293241281099","DOIUrl":"https://doi.org/10.1177/17568293241281099","url":null,"abstract":"","PeriodicalId":49053,"journal":{"name":"International Journal of Micro Air Vehicles","volume":"60 1","pages":""},"PeriodicalIF":1.4,"publicationDate":"2024-09-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142253215","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2024-08-09DOI: 10.1177/17568293241262323
Zuqiang Yang, Yi Yang, Xingxiu He, Weicheng Qi
Coverage in unknown environment is a commonly concerned problem in ground mapping field of Unmanned Aerial Vehicle (UAV). Based on the concept of incremental cell construction, a practical online coverage path planning method is proposed for mapping in unknown environments with obstacles and boundaries. This method consists of the Boustrophedon motion and D* algorithm. Based on the information from onboard ranging sensor, the UAV uses Boustrophedon motion to incrementally construct coverage cells while exploring the environment. When there are no alternative cells for Boustrophedon motion, the D* algorithm is utilized to plan the backtracking path to the next starting point. Particularly, the backtracking path replanning will be carried out if an unknown obstacle suddenly appears on the path. The static and hardware-in-loop dynamic simulation results show that the proposed method can achieve near-complete coverage in complex unknown environments with low computational and sensor accuracy requirements.
{"title":"Incremental coverage path planning method for UAV ground mapping in unknown area","authors":"Zuqiang Yang, Yi Yang, Xingxiu He, Weicheng Qi","doi":"10.1177/17568293241262323","DOIUrl":"https://doi.org/10.1177/17568293241262323","url":null,"abstract":"Coverage in unknown environment is a commonly concerned problem in ground mapping field of Unmanned Aerial Vehicle (UAV). Based on the concept of incremental cell construction, a practical online coverage path planning method is proposed for mapping in unknown environments with obstacles and boundaries. This method consists of the Boustrophedon motion and D* algorithm. Based on the information from onboard ranging sensor, the UAV uses Boustrophedon motion to incrementally construct coverage cells while exploring the environment. When there are no alternative cells for Boustrophedon motion, the D* algorithm is utilized to plan the backtracking path to the next starting point. Particularly, the backtracking path replanning will be carried out if an unknown obstacle suddenly appears on the path. The static and hardware-in-loop dynamic simulation results show that the proposed method can achieve near-complete coverage in complex unknown environments with low computational and sensor accuracy requirements.","PeriodicalId":49053,"journal":{"name":"International Journal of Micro Air Vehicles","volume":"43 1","pages":""},"PeriodicalIF":1.4,"publicationDate":"2024-08-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141936237","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2024-05-10DOI: 10.1177/17568293241254045
Jiaze Cai, Hunter Denton, Moble Benedict, Hao Kang
This paper describes the development and flight testing of a tail-sitter unmanned aerial vehicle (UAV) platform that has the potential to be tube-launched. Integrated with vertical take-off and landing (VTOL) capability, the platform can perform high-endurance loiter tasks along with low-speed and hovering flights, and land vertically in limited spaces. The current design utilizes a thrust-vectored counter-rotating coaxial propeller combined with a foldable conventional fixed-wing to accomplish both vertical and horizontal flights. A feedback control strategy capable of stabilizing and controlling the vehicle in both vertical and horizontal flight was designed and implemented on a custom-designed 1.7-gram autopilot. Several tests were conducted in hover and edgewise flight with aggressive pilot inputs to demonstrate the controllability of the aircraft even in the presence of moderate wind gusts. Additionally, transition flight tests were also performed, which demonstrated the vehicle’s capability of transitioning from vertical to fixed-wing horizontal flight using thrust-vectoring-based pitch control.
{"title":"Development of a tube-launched tail-sitter unmanned aerial vehicle","authors":"Jiaze Cai, Hunter Denton, Moble Benedict, Hao Kang","doi":"10.1177/17568293241254045","DOIUrl":"https://doi.org/10.1177/17568293241254045","url":null,"abstract":"This paper describes the development and flight testing of a tail-sitter unmanned aerial vehicle (UAV) platform that has the potential to be tube-launched. Integrated with vertical take-off and landing (VTOL) capability, the platform can perform high-endurance loiter tasks along with low-speed and hovering flights, and land vertically in limited spaces. The current design utilizes a thrust-vectored counter-rotating coaxial propeller combined with a foldable conventional fixed-wing to accomplish both vertical and horizontal flights. A feedback control strategy capable of stabilizing and controlling the vehicle in both vertical and horizontal flight was designed and implemented on a custom-designed 1.7-gram autopilot. Several tests were conducted in hover and edgewise flight with aggressive pilot inputs to demonstrate the controllability of the aircraft even in the presence of moderate wind gusts. Additionally, transition flight tests were also performed, which demonstrated the vehicle’s capability of transitioning from vertical to fixed-wing horizontal flight using thrust-vectoring-based pitch control.","PeriodicalId":49053,"journal":{"name":"International Journal of Micro Air Vehicles","volume":"18 1","pages":""},"PeriodicalIF":1.4,"publicationDate":"2024-05-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140933190","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2024-03-12DOI: 10.1177/17568293241238019
Linkai Tang, Min Chang, Yaping Huang, Siliang Zu, Junqiang Bai
To achieve underactuated control, a novel swashplateless rotor configuration of asymmetric inclined hinges which can be driven by periodic sinusoidal torque is studied, hopefully eliminating the conventional swashplate mechanism and multiple actuators. Therefore, the traditional mechanism can be intelligently replaced by software. However, high-frequency torque variation will invariably result in vibration noise and energy loss.Thus it is critical to properly design the swashplateless rotor in order to achieve a control process with less torque variation. As a result, in both numerical simulation and experiments, we performed sensitivity analyses on related design parameters such as hinge eccentricity, hinge inclined angle, and wingtip hammer position. The parameter effect on swashplateless rotor control was discovered through the analyses, and the basic law of its design was obtained.
{"title":"Parameter effect on the novel swashplateless rotor control","authors":"Linkai Tang, Min Chang, Yaping Huang, Siliang Zu, Junqiang Bai","doi":"10.1177/17568293241238019","DOIUrl":"https://doi.org/10.1177/17568293241238019","url":null,"abstract":"To achieve underactuated control, a novel swashplateless rotor configuration of asymmetric inclined hinges which can be driven by periodic sinusoidal torque is studied, hopefully eliminating the conventional swashplate mechanism and multiple actuators. Therefore, the traditional mechanism can be intelligently replaced by software. However, high-frequency torque variation will invariably result in vibration noise and energy loss.Thus it is critical to properly design the swashplateless rotor in order to achieve a control process with less torque variation. As a result, in both numerical simulation and experiments, we performed sensitivity analyses on related design parameters such as hinge eccentricity, hinge inclined angle, and wingtip hammer position. The parameter effect on swashplateless rotor control was discovered through the analyses, and the basic law of its design was obtained.","PeriodicalId":49053,"journal":{"name":"International Journal of Micro Air Vehicles","volume":"2016 1","pages":""},"PeriodicalIF":1.4,"publicationDate":"2024-03-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140116190","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2023-01-01DOI: 10.1177/17568293231189999
Carl Runco, Moble Benedict
This paper discusses the development of a micro air vehicle scale quad-cyclocopter for the purpose of investigating cyclorotor application to low Reynolds number ([Formula: see text]) flight. The 70-gram vehicle is the lightest quad-cyclocopter developed to date by an order of magnitude and only the second to achieve forward flight. It utilized two counter-rotating pairs of cyclorotors operating at [Formula: see text] [Formula: see text] to generate thrust and balance the reaction torque. Each cyclorotor had two control parameters, thrust direction and magnitude, giving the quad-cyclocopter eight independent control parameters. Flight tests were conducted to demonstrate several unique maneuvers made possible by the over-actuated system: changing pitch attitude in a point hover and forward translation via thrust vectoring. Data was collected for longitudinal maneuvers to compare forward flight performance when using strictly thrust vectoring for propulsion versus pitching without thrust vectoring. Similar performance was observed between the two modes for the achieved speeds.
{"title":"Design, development, and flight testing of a 70-gram micro quad-cyclocopter","authors":"Carl Runco, Moble Benedict","doi":"10.1177/17568293231189999","DOIUrl":"https://doi.org/10.1177/17568293231189999","url":null,"abstract":"This paper discusses the development of a micro air vehicle scale quad-cyclocopter for the purpose of investigating cyclorotor application to low Reynolds number ([Formula: see text]) flight. The 70-gram vehicle is the lightest quad-cyclocopter developed to date by an order of magnitude and only the second to achieve forward flight. It utilized two counter-rotating pairs of cyclorotors operating at [Formula: see text] [Formula: see text] to generate thrust and balance the reaction torque. Each cyclorotor had two control parameters, thrust direction and magnitude, giving the quad-cyclocopter eight independent control parameters. Flight tests were conducted to demonstrate several unique maneuvers made possible by the over-actuated system: changing pitch attitude in a point hover and forward translation via thrust vectoring. Data was collected for longitudinal maneuvers to compare forward flight performance when using strictly thrust vectoring for propulsion versus pitching without thrust vectoring. Similar performance was observed between the two modes for the achieved speeds.","PeriodicalId":49053,"journal":{"name":"International Journal of Micro Air Vehicles","volume":" ","pages":""},"PeriodicalIF":1.4,"publicationDate":"2023-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"43508188","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2023-01-01DOI: 10.1177/17568293221147923
Van Duc Nguyen, V. D. Duong, Minh Hoang Trinh, Hoang Quan Nguyen, Dang Thai Son Nguyen
Low order modelings are performed in this paper, including iterative Brinkman penalized vortex method (IBVM) and data-driven dynamic mode decomposition (DMD) for dynamic stall study of symmetric airfoil. The data are extracted from IBVM as input for flow field reconstruction using combinations of DMD dominant modes, representing extracted flow features. The primary mode together with its harmonics, and the mean mode are termed to be dominant for the airfoil wake duplication at fixed angles of attack ([Formula: see text]) ranging from [Formula: see text] to [Formula: see text]. For the dynamic stall duplication, at small and large pitching amplitudes, the nearfield and farfield vorticty contours from the DMD generally agree well with those from the IBVM. In addition, the lift coefficient from the DMD collapses well with that from the IBVM and the experiment.
{"title":"Low order modeling of dynamic stall using vortex particle method and dynamic mode decomposition","authors":"Van Duc Nguyen, V. D. Duong, Minh Hoang Trinh, Hoang Quan Nguyen, Dang Thai Son Nguyen","doi":"10.1177/17568293221147923","DOIUrl":"https://doi.org/10.1177/17568293221147923","url":null,"abstract":"Low order modelings are performed in this paper, including iterative Brinkman penalized vortex method (IBVM) and data-driven dynamic mode decomposition (DMD) for dynamic stall study of symmetric airfoil. The data are extracted from IBVM as input for flow field reconstruction using combinations of DMD dominant modes, representing extracted flow features. The primary mode together with its harmonics, and the mean mode are termed to be dominant for the airfoil wake duplication at fixed angles of attack ([Formula: see text]) ranging from [Formula: see text] to [Formula: see text]. For the dynamic stall duplication, at small and large pitching amplitudes, the nearfield and farfield vorticty contours from the DMD generally agree well with those from the IBVM. In addition, the lift coefficient from the DMD collapses well with that from the IBVM and the experiment.","PeriodicalId":49053,"journal":{"name":"International Journal of Micro Air Vehicles","volume":" ","pages":""},"PeriodicalIF":1.4,"publicationDate":"2023-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"42586575","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2023-01-01DOI: 10.1177/17568293221148385
Ze Wang, Jingang Qu, P. Morin
This article concerns airflow-based odometry for estimating MAV flight speed from airflow measurements provided by a set of thermal anemometers. Our approach relies on a Gated Recurrent Unit (GRU) based deep learning approach to extract deep features from noisy and turbulent measurement signals of triaxial thermal anemometers, in order to establish the underlying mapping between the airflow measurement and the flight speed. The proposed solution is validated on a multi-rotor MAV. The results show that the GRU-based model can effectively extract noise features and perform denoising, and compensate for induced velocity effects along the propellers’ rotation axis. As a consequence, robust prediction of the flight speed is performed, including during takeoff and landing that induce ground effects and strong variations of vertical airflow.
{"title":"Airflow-based odometry for MAVs using thermal anemometers","authors":"Ze Wang, Jingang Qu, P. Morin","doi":"10.1177/17568293221148385","DOIUrl":"https://doi.org/10.1177/17568293221148385","url":null,"abstract":"This article concerns airflow-based odometry for estimating MAV flight speed from airflow measurements provided by a set of thermal anemometers. Our approach relies on a Gated Recurrent Unit (GRU) based deep learning approach to extract deep features from noisy and turbulent measurement signals of triaxial thermal anemometers, in order to establish the underlying mapping between the airflow measurement and the flight speed. The proposed solution is validated on a multi-rotor MAV. The results show that the GRU-based model can effectively extract noise features and perform denoising, and compensate for induced velocity effects along the propellers’ rotation axis. As a consequence, robust prediction of the flight speed is performed, including during takeoff and landing that induce ground effects and strong variations of vertical airflow.","PeriodicalId":49053,"journal":{"name":"International Journal of Micro Air Vehicles","volume":" ","pages":""},"PeriodicalIF":1.4,"publicationDate":"2023-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"41968940","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2023-01-01DOI: 10.1177/17568293221148380
Lucia Bergantin, C. Coquet, Jonathan Dumon, Amaury Nègre, Thibaut, Raharijaona, Nicolas Marchand, Franck Ruffier
Estimating distance traveled is a frequently arising problem in robotic applications designed for use in environments where GPS is only intermittently or not at all available. In UAVs, the presence of weight and computational power constraints makes it necessary to develop odometric strategies based on minimilastic equipment. In this study, a hexarotor was made to perform up-and-down oscillatory movements while flying forward in order to test a self-scaled optic flow based odometer. The resulting self-oscillatory trajectory generated series of contractions and expansions in the optic flow vector field, from which the flight height of the hexarotor could be estimated using an Extended Kalman Filter. For the odometry, the downward translational optic flow was scaled by this current visually estimated flight height before being mathematically integrated to obtain the distance traveled. Here we present three strategies based on sensor fusion requiring no, precise or rough prior knowledge of the optic flow variations generated by the sinusoidal trajectory. The “rough prior knowledge” strategy is based on the shape and timing of the variations in the optic flow. Tests were performed first in a flight arena, where the hexarotor followed a circular trajectory while oscillating up and down over a distance of about [Formula: see text] m under illuminances of [Formula: see text] lux and [Formula: see text] lux. Preliminary field tests were then performed, in which the hexarotor followed a longitudinal bouncing [Formula: see text]-long trajectory over an irregular pattern of grass.
{"title":"Indoor and outdoor in-flight odometry based solely on optic flows with oscillatory trajectories","authors":"Lucia Bergantin, C. Coquet, Jonathan Dumon, Amaury Nègre, Thibaut, Raharijaona, Nicolas Marchand, Franck Ruffier","doi":"10.1177/17568293221148380","DOIUrl":"https://doi.org/10.1177/17568293221148380","url":null,"abstract":"Estimating distance traveled is a frequently arising problem in robotic applications designed for use in environments where GPS is only intermittently or not at all available. In UAVs, the presence of weight and computational power constraints makes it necessary to develop odometric strategies based on minimilastic equipment. In this study, a hexarotor was made to perform up-and-down oscillatory movements while flying forward in order to test a self-scaled optic flow based odometer. The resulting self-oscillatory trajectory generated series of contractions and expansions in the optic flow vector field, from which the flight height of the hexarotor could be estimated using an Extended Kalman Filter. For the odometry, the downward translational optic flow was scaled by this current visually estimated flight height before being mathematically integrated to obtain the distance traveled. Here we present three strategies based on sensor fusion requiring no, precise or rough prior knowledge of the optic flow variations generated by the sinusoidal trajectory. The “rough prior knowledge” strategy is based on the shape and timing of the variations in the optic flow. Tests were performed first in a flight arena, where the hexarotor followed a circular trajectory while oscillating up and down over a distance of about [Formula: see text] m under illuminances of [Formula: see text] lux and [Formula: see text] lux. Preliminary field tests were then performed, in which the hexarotor followed a longitudinal bouncing [Formula: see text]-long trajectory over an irregular pattern of grass.","PeriodicalId":49053,"journal":{"name":"International Journal of Micro Air Vehicles","volume":" ","pages":""},"PeriodicalIF":1.4,"publicationDate":"2023-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"44495921","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2023-01-01DOI: 10.1177/17568293231178263
Thomas Roelandt, D. Vandepitte
Maneuverability of flapping wing fliers inevitably goes with inherent system instability. Inherent instability means that flapping wing systems require a flight controller and that these vehicles are prone to crashing. This work proposes a design feature to stabilize the descent of a flapping wing aerial vehicle. The vehicle is based on the KUlibrie, a flapping wing nano robot that is under development at KU Leuven. A computational study indicates that upwardly elevated wings provide inherently stable descending flight. The vehicle performs a free flight starting from different initial conditions. The system dynamics display convergence towards a limit cycle. Wing elevation and center of gravity position determine pitch and roll stiffness with respect to vertical descent and climb. The same effects that stabilize descent also destabilize climbing flight.
{"title":"Inherently stable descending flight of a tailless flapping wing micro air vehicle by upward wing elevation","authors":"Thomas Roelandt, D. Vandepitte","doi":"10.1177/17568293231178263","DOIUrl":"https://doi.org/10.1177/17568293231178263","url":null,"abstract":"Maneuverability of flapping wing fliers inevitably goes with inherent system instability. Inherent instability means that flapping wing systems require a flight controller and that these vehicles are prone to crashing. This work proposes a design feature to stabilize the descent of a flapping wing aerial vehicle. The vehicle is based on the KUlibrie, a flapping wing nano robot that is under development at KU Leuven. A computational study indicates that upwardly elevated wings provide inherently stable descending flight. The vehicle performs a free flight starting from different initial conditions. The system dynamics display convergence towards a limit cycle. Wing elevation and center of gravity position determine pitch and roll stiffness with respect to vertical descent and climb. The same effects that stabilize descent also destabilize climbing flight.","PeriodicalId":49053,"journal":{"name":"International Journal of Micro Air Vehicles","volume":" ","pages":""},"PeriodicalIF":1.4,"publicationDate":"2023-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"48762620","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2023-01-01DOI: 10.1177/17568293231197127
A Esmaeili, JMM Sousa
This study presents the design, implementation, and assessment of a combined passive and active flow control technique with the aim of increasing the aerodynamic performance of fixed-wing Micro Air Vehicles (MAVs). Power consumption restrictions in MAVs support the choice of passive flow control solutions such as the use of a modified (tubercled) wing leading edge. This strategy successfully allows to delay and mitigate aerodynamic stall but detrimental effects are found at pre-stall operating conditions. In order to retrieve the lift-generation capabilities of the baseline wing at pre-stall, a subsidiary active flow control method making use of air blowing was designed and installed in the modified wing. Guidance to the selection of optimum settings was provided by experimental and computational analyses. The resulting hybrid flow control system demonstrated its effectiveness, thus producing generalized lift enhancements irrespectively of the attitude of the wing.
{"title":"Combined passive and active flow control for fixed-wing micro air vehicles","authors":"A Esmaeili, JMM Sousa","doi":"10.1177/17568293231197127","DOIUrl":"https://doi.org/10.1177/17568293231197127","url":null,"abstract":"This study presents the design, implementation, and assessment of a combined passive and active flow control technique with the aim of increasing the aerodynamic performance of fixed-wing Micro Air Vehicles (MAVs). Power consumption restrictions in MAVs support the choice of passive flow control solutions such as the use of a modified (tubercled) wing leading edge. This strategy successfully allows to delay and mitigate aerodynamic stall but detrimental effects are found at pre-stall operating conditions. In order to retrieve the lift-generation capabilities of the baseline wing at pre-stall, a subsidiary active flow control method making use of air blowing was designed and installed in the modified wing. Guidance to the selection of optimum settings was provided by experimental and computational analyses. The resulting hybrid flow control system demonstrated its effectiveness, thus producing generalized lift enhancements irrespectively of the attitude of the wing.","PeriodicalId":49053,"journal":{"name":"International Journal of Micro Air Vehicles","volume":"33 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135800050","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
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