The Experts below are selected from a list of 279 Experts worldwide ranked by ideXlab platform
Pierluigi Della Vecchia - One of the best experts on this subject based on the ideXlab platform.
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roll performance assessment of a light aircraft Flight simulations and Flight Tests
Aerospace Science and Technology, 2018Co-Authors: Fabrizio Nicolosi, Agostino De Marco, Vito Sabetta, Pierluigi Della VecchiaAbstract:Abstract A methodology is presented for the roll performance assessment of a light aircraft. The study is based both on Flight simulations and Flight Tests, focusing on the accurate determination of the lateral control power. The chosen test airplane was a Tecnam P92, a two-seat ultralight aircraft which was specifically equipped with a lightweight and accurate instrumentation for the planned set of Flight data measurements. A matrix of Flight experiments for the test campaign was established with the support of 6-degree-of-freedom simulations, implementing a carefully constructed baseline dynamic model of the aircraft. The article discusses first the general problem of a reliable evaluation of aircraft roll performance indicators, i.e. the estimation of the aerodynamic derivatives that mainly influence the airplane ability to roll. Next, the results of extensive Flight test activities are presented. The analysis of several roll maneuvers performed at different Flight speeds and with different aileron maximum deflections showed interesting rolling characteristics for this non-aerobatic aircraft. One notable finding was a clear nonlinear dependency of the aileron efficiency index on aileron deflection amplitude. A control power derivative extracted from Flight data in the form of lookup table was used to correct the baseline Flight dynamics model. Flight simulations outputs based on the updated model showed a satisfactory agreement with experimental time histories. According to this, the present effort proposes a new method to estimate the aileron control derivative in whole the Flight envelope for light aircraft.
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Flight Tests performances and Flight certification of a twin engine light aircraft
Journal of Aircraft, 2011Co-Authors: Fabrizio Nicolosi, Agostino De Marco, Pierluigi Della VecchiaAbstract:This paper deals with Flight test activities performed on P2006T, a twin-engine light aircraft recently designed and produced by Tecnam. Research activities and Flight Tests have been conducted during the Flight certification of P2006T for the normal category under CS23. All the acquired data and Flight results presented have been focused on both aircraft certification and on aircraft performances, stability and Flight qualities measurement. The data have been acquired through a light, accurate and reliable Flight instrumentation available at DIAS (Department of Aerospace Engineering). Some Flight data about aircraft leveled speed, stall speed, climb characteristics and ground performances (take-off and landing) will be presented. After preliminary Flight Tests, winglets have been designed and added to the final configuration in order to obtain good climb performances also in OEI (One Engine Inoperative) conditions. Accurate stall Tests have been performed in all configurations and influence of both entry-rate and load factor on stall speed have been highlighted. Excellent ground performances have been measured with short take-off and landing distances compared with similar airplanes. All measured Flight performances can be considered very good for this aircraft category and have been used to demonstrate aircraft safety and to obtain CS23 certification.
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Flight Tests, Performances and Flight Certification of a Twin-Engine Light Aircraft
Journal of Aircraft, 2011Co-Authors: Fabrizio Nicolosi, Agostino De Marco, Pierluigi Della VecchiaAbstract:This paper deals with Flight test activities performed on P2006T, a twin-engine light aircraft recently designed and produced by Tecnam. Research activities and Flight Tests have been conducted during the Flight certification of P2006T for the normal category under CS23. All the acquired data and Flight results presented have been focused on both aircraft certification and on aircraft performances, stability and Flight qualities measurement. The data have been acquired through a light, accurate and reliable Flight instrumentation available at DIAS (Department of Aerospace Engineering). Some Flight data about aircraft leveled speed, stall speed, climb characteristics and ground performances (take-off and landing) will be presented. After preliminary Flight Tests, winglets have been designed and added to the final configuration in order to obtain good climb performances also in OEI (One Engine Inoperative) conditions. Accurate stall Tests have been performed in all configurations and influence of both entry-rate and load factor on stall speed have been highlighted. Excellent ground performances have been measured with short take-off and landing distances compared with similar airplanes. All measured Flight performances can be considered very good for this aircraft category and have been used to demonstrate aircraft safety and to obtain CS23 certification.
Robert J. Wood - One of the best experts on this subject based on the ideXlab platform.
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Stabilizing air dampers for hovering aerial robotics: design, insect-scale Flight Tests, and scaling
Autonomous Robots, 2017Co-Authors: Sawyer B Fuller, Pakpong Chirarattananon, Néstor O. Pérez-arancibia, Jack Greenberg, Zhi Ern Teoh, Robert J. WoodAbstract:Most hovering aircraft such as helicopters and animal-inspired flapping-wing flyers are dynamically unstable in Flight, quickly tumbling in the absence of feedback control. The addition of feedback loops can stabilize, but at the cost of additional sensing and actuation components. This can add expense, weight, and complexity. An alternative to feedback is the use of passive mechanisms such as aerodynamic drag to stabilize attitude. Previous work has suggested that small aircraft can be stabilized by adding air dampers above and below the center of mass. We present Flight Tests of an insect-scale robot operating under this principle. When controlled to a constant altitude, it remains stably upright while undergoing cyclic attitude oscillations. To characterize these oscillations, we present a nonlinear analytic model derived from first principles that reproduces the observed behavior. Using numerical simulation, we analyze how changing damper size, position, mass, and midpoint offset affect these oscillations, building on previous work that considered only a single configuration. Our results indicate that only by increasing damper size can lateral oscillation amplitude be significantly reduced, at the cost of increased damper mass. Additionally, we show that as scale diminishes, the damper size must get relatively larger. This suggests that smaller damper-equipped robots must operate in low-wind areas or in boundary-layer flow near surfaces.
Fabrizio Nicolosi - One of the best experts on this subject based on the ideXlab platform.
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roll performance assessment of a light aircraft Flight simulations and Flight Tests
Aerospace Science and Technology, 2018Co-Authors: Fabrizio Nicolosi, Agostino De Marco, Vito Sabetta, Pierluigi Della VecchiaAbstract:Abstract A methodology is presented for the roll performance assessment of a light aircraft. The study is based both on Flight simulations and Flight Tests, focusing on the accurate determination of the lateral control power. The chosen test airplane was a Tecnam P92, a two-seat ultralight aircraft which was specifically equipped with a lightweight and accurate instrumentation for the planned set of Flight data measurements. A matrix of Flight experiments for the test campaign was established with the support of 6-degree-of-freedom simulations, implementing a carefully constructed baseline dynamic model of the aircraft. The article discusses first the general problem of a reliable evaluation of aircraft roll performance indicators, i.e. the estimation of the aerodynamic derivatives that mainly influence the airplane ability to roll. Next, the results of extensive Flight test activities are presented. The analysis of several roll maneuvers performed at different Flight speeds and with different aileron maximum deflections showed interesting rolling characteristics for this non-aerobatic aircraft. One notable finding was a clear nonlinear dependency of the aileron efficiency index on aileron deflection amplitude. A control power derivative extracted from Flight data in the form of lookup table was used to correct the baseline Flight dynamics model. Flight simulations outputs based on the updated model showed a satisfactory agreement with experimental time histories. According to this, the present effort proposes a new method to estimate the aileron control derivative in whole the Flight envelope for light aircraft.
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Flight Tests performances and Flight certification of a twin engine light aircraft
Journal of Aircraft, 2011Co-Authors: Fabrizio Nicolosi, Agostino De Marco, Pierluigi Della VecchiaAbstract:This paper deals with Flight test activities performed on P2006T, a twin-engine light aircraft recently designed and produced by Tecnam. Research activities and Flight Tests have been conducted during the Flight certification of P2006T for the normal category under CS23. All the acquired data and Flight results presented have been focused on both aircraft certification and on aircraft performances, stability and Flight qualities measurement. The data have been acquired through a light, accurate and reliable Flight instrumentation available at DIAS (Department of Aerospace Engineering). Some Flight data about aircraft leveled speed, stall speed, climb characteristics and ground performances (take-off and landing) will be presented. After preliminary Flight Tests, winglets have been designed and added to the final configuration in order to obtain good climb performances also in OEI (One Engine Inoperative) conditions. Accurate stall Tests have been performed in all configurations and influence of both entry-rate and load factor on stall speed have been highlighted. Excellent ground performances have been measured with short take-off and landing distances compared with similar airplanes. All measured Flight performances can be considered very good for this aircraft category and have been used to demonstrate aircraft safety and to obtain CS23 certification.
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Flight Tests, Performances and Flight Certification of a Twin-Engine Light Aircraft
Journal of Aircraft, 2011Co-Authors: Fabrizio Nicolosi, Agostino De Marco, Pierluigi Della VecchiaAbstract:This paper deals with Flight test activities performed on P2006T, a twin-engine light aircraft recently designed and produced by Tecnam. Research activities and Flight Tests have been conducted during the Flight certification of P2006T for the normal category under CS23. All the acquired data and Flight results presented have been focused on both aircraft certification and on aircraft performances, stability and Flight qualities measurement. The data have been acquired through a light, accurate and reliable Flight instrumentation available at DIAS (Department of Aerospace Engineering). Some Flight data about aircraft leveled speed, stall speed, climb characteristics and ground performances (take-off and landing) will be presented. After preliminary Flight Tests, winglets have been designed and added to the final configuration in order to obtain good climb performances also in OEI (One Engine Inoperative) conditions. Accurate stall Tests have been performed in all configurations and influence of both entry-rate and load factor on stall speed have been highlighted. Excellent ground performances have been measured with short take-off and landing distances compared with similar airplanes. All measured Flight performances can be considered very good for this aircraft category and have been used to demonstrate aircraft safety and to obtain CS23 certification.
Sawyer B Fuller - One of the best experts on this subject based on the ideXlab platform.
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Stabilizing air dampers for hovering aerial robotics: design, insect-scale Flight Tests, and scaling
Autonomous Robots, 2017Co-Authors: Sawyer B Fuller, Pakpong Chirarattananon, Néstor O. Pérez-arancibia, Jack Greenberg, Zhi Ern Teoh, Robert J. WoodAbstract:Most hovering aircraft such as helicopters and animal-inspired flapping-wing flyers are dynamically unstable in Flight, quickly tumbling in the absence of feedback control. The addition of feedback loops can stabilize, but at the cost of additional sensing and actuation components. This can add expense, weight, and complexity. An alternative to feedback is the use of passive mechanisms such as aerodynamic drag to stabilize attitude. Previous work has suggested that small aircraft can be stabilized by adding air dampers above and below the center of mass. We present Flight Tests of an insect-scale robot operating under this principle. When controlled to a constant altitude, it remains stably upright while undergoing cyclic attitude oscillations. To characterize these oscillations, we present a nonlinear analytic model derived from first principles that reproduces the observed behavior. Using numerical simulation, we analyze how changing damper size, position, mass, and midpoint offset affect these oscillations, building on previous work that considered only a single configuration. Our results indicate that only by increasing damper size can lateral oscillation amplitude be significantly reduced, at the cost of increased damper mass. Additionally, we show that as scale diminishes, the damper size must get relatively larger. This suggests that smaller damper-equipped robots must operate in low-wind areas or in boundary-layer flow near surfaces.
Patrick J Lauffs - One of the best experts on this subject based on the ideXlab platform.
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Flightplan Flight Tests of an experimental da42 general aviation aircraft
International Conference on Control Automation Robotics and Vision, 2016Co-Authors: Simon P Schatz, Volker Schneider, Erik Karlsson, Florian Holzapfel, Thaddaus Baier, Christoph Dorhofer, Markus Hochstrasser, Agnes Gabrys, Christoph Krause, Patrick J LauffsAbstract:The recent emergence of unmanned aerial vehicles asked for both well-performing auto-Flight systems and fly-by-wire architectures. Towards this end, the trajectory control module of an integrated auto-Flight control system is introduced in this paper, which utilizes nonlinear second-order error dynamics of the position error and uses nonlinear dynamic inversion as a control methodology. Flight test results of a Flightplan mission conducted on the institute's general aviation aircraft — a DA42 augmented with experimental fly-by-wire — are presented and the controller's performance is evaluated.
