東華大學圖書館 |

Control of a Passively-Coupled Hybrid Aircraft.

紀錄類型:	書目-電子資源 : Monograph/item
正題名/作者:	Control of a Passively-Coupled Hybrid Aircraft./
作者:	Patience, Christian A.
面頁冊數:	1 online resource (88 pages)
附註:	Source: Masters Abstracts International, Volume: 83-10.
Contained By:	Masters Abstracts International83-10.
標題:	Aircraft. -
電子資源:	http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=29043507click for full text (PQDT)
ISBN:	9798209932147

Control of a Passively-Coupled Hybrid Aircraft.
Patience, Christian A.

Control of a Passively-Coupled Hybrid Aircraft. - 1 online resource (88 pages)

Source: Masters Abstracts International, Volume: 83-10.

Thesis (M.Sc.)--McGill University (Canada), 2021.

Includes bibliographical references

Unmanned aerial vehicles have gained popularity in applications such as agricultural monitoring and package delivery, due to their low cost and versatility. The two traditional existing aircraft architectures are fixed-wing and rotorcraft, each with distinct advantages. Tilt-rotor hybrid aircraft blend these two architectures and retain the advantages of both. However, their complex dynamics and broader flight envelope make them more difficult to control. The Vogi UAV, which is the focus on this thesis, can be classified as a tilt-rotor aircraft and comprises a fixed-wing body with a passively-hinged quadrotor frame.In this thesis, we present a single controller that seamlessly handles the transition from vertical to forward flight, while balancing the use of propellers and control surfaces. It is largely platform-independent, and can be generalized to other tilt-rotor aircraft with modifications to the control allocation. The controller is evaluated in a comprehensive Matlab/Simulink flight simulation, and its performance is assessed using two test trajectories. Together, they cover all flight modes that a hybrid aircraft would undergo, including vertical take off, forward flight with turns, and vertical landing. In general, speed and position tracking very good, with peak errors typically occuring at the onset of acceleration or deceleration. The wing pitch converges slowly in steady state, but responds quickly to changes in reference. Despite the vehicle transitioning between trajectory segments smoothly, the heading reference transition from quadcopter-dominant flight to fixed-wing dominant flight results in an abrupt reaction, due to the discontinuous heading reference.We generate explicit reference trajectories for the position, velocity, attitude, and body rate reference trajectories for two bodies differing in pitch, with just the inertial velocity being user-specified. The rest of the reference states are subsequently generated from aerodynamic analyses, a control law, and transformations. One such aerodynamic analysis consists of an optimization for flight endurance by specifying the pitch angle of the wing throughout the trajectory, as well as the propeller thrust direction. Conventional propeller models rarely account for the effects that the vehicle motion has on thrust, and those that do typically assume they are operating in axial flow conditions. Tiltrotor propellers, however, are often operated in oblique flow conditions. We propose a thrust model that spans 360°, based on the assumption that there is no loss of thrust in a cross-flow. Under the most common operating conditions, our model reported a mean absolute error of e = 0.09 N.

Electronic reproduction.
Ann Arbor, Mich. :
ProQuest,
2023

Mode of access: World Wide Web

ISBN: 9798209932147Subjects--Topical Terms:

832698
Aircraft.
Index Terms--Genre/Form:

542853
Electronic books.

Control of a Passively-Coupled Hybrid Aircraft.
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500 $a Source: Masters Abstracts International, Volume: 83-10.
500 $a Advisor: Nahon, Meyer.
502 $a Thesis (M.Sc.)--McGill University (Canada), 2021.
504 $a Includes bibliographical references
520 $a Unmanned aerial vehicles have gained popularity in applications such as agricultural monitoring and package delivery, due to their low cost and versatility. The two traditional existing aircraft architectures are fixed-wing and rotorcraft, each with distinct advantages. Tilt-rotor hybrid aircraft blend these two architectures and retain the advantages of both. However, their complex dynamics and broader flight envelope make them more difficult to control. The Vogi UAV, which is the focus on this thesis, can be classified as a tilt-rotor aircraft and comprises a fixed-wing body with a passively-hinged quadrotor frame.In this thesis, we present a single controller that seamlessly handles the transition from vertical to forward flight, while balancing the use of propellers and control surfaces. It is largely platform-independent, and can be generalized to other tilt-rotor aircraft with modifications to the control allocation. The controller is evaluated in a comprehensive Matlab/Simulink flight simulation, and its performance is assessed using two test trajectories. Together, they cover all flight modes that a hybrid aircraft would undergo, including vertical take off, forward flight with turns, and vertical landing. In general, speed and position tracking very good, with peak errors typically occuring at the onset of acceleration or deceleration. The wing pitch converges slowly in steady state, but responds quickly to changes in reference. Despite the vehicle transitioning between trajectory segments smoothly, the heading reference transition from quadcopter-dominant flight to fixed-wing dominant flight results in an abrupt reaction, due to the discontinuous heading reference.We generate explicit reference trajectories for the position, velocity, attitude, and body rate reference trajectories for two bodies differing in pitch, with just the inertial velocity being user-specified. The rest of the reference states are subsequently generated from aerodynamic analyses, a control law, and transformations. One such aerodynamic analysis consists of an optimization for flight endurance by specifying the pitch angle of the wing throughout the trajectory, as well as the propeller thrust direction. Conventional propeller models rarely account for the effects that the vehicle motion has on thrust, and those that do typically assume they are operating in axial flow conditions. Tiltrotor propellers, however, are often operated in oblique flow conditions. We propose a thrust model that spans 360°, based on the assumption that there is no loss of thrust in a cross-flow. Under the most common operating conditions, our model reported a mean absolute error of e = 0.09 N.
520 $a Les vehicules aeriens autonomes ont gagne en popularite dans des applications telles que la surveillance agricole et la livraison de colis, en raison detre economique et polyvalents. Les deux architectures traditionnelles existantes sont les drones a voilure fixe et les tiltrotors (un aeronef avec des rotors basculants), chacun ayant des avantages distincts. Les avions hybrides a rotor basculant combinent les deux architectures en conservant leurs avantages. Toutefois, leur dynamique complexe et leur plus vaste enveloppe de vol les rendent plus difficiles a controler. Le drone Vogi, qui est l'objet de cette these, peut etre classe comme un aeronef a rotor basculant et comprend un corps a voilure fixe avec un cadre de quadrotor a charniere passive. ans cette these', nous presentons un controleur unique qui gere de maniere transparente la transition entre le vol vertical et le vol vers l'avant, tout en equilibrant l'utilisation ses helices et ses surfaces de controle. Il est largement independant de la plate-forme, et peut etre generalise a d'autres aeronefs a rotors basculant en modifiant l'allocation des commandes. Le controleur est evalue dans le cadre d'une simulation de vol complete Matlab/Simulink, et ses performances sont evaluees a' l'aide de deux trajectoires. Les trajectoires utilisees couvrent tous les modes de vol qu'un avion hybride pourrait subir, y compris le decollage vertical, le vol vers l'avant avec virages et l'atterrissage vertical. En general, le suivi de la vitesse et de la position est tres bon, les erreurs maximales se produisant generalement au debut de l'acceleration ou de la deceleration. L'inclinaison de l'aile converge lentement en regime stationnaire, mais reagit rapidement aux changements de reference. Bien que le vehicule passe d'une trajectoire a l'autre sans probleme', la transition de la reference de cap entre le vol a dominance quadcoptere et le vol a dominance aile fixe entraine une reaction brusque en raison de la referance de cap non continu.Nous generons des trajectoires de reference explicites pour la position, la vitesse, l'attitude et la vitesse angulaire pour deux corps dont l'inclinaison differe, seule la vitesse inertielle etant specifiee par l'utilisateur. Les autres etats de reference sont ensuite generes a partir d'analyses aerodynamiques, d'une loi de controle et de transformations. L'une de ces analyses aerodynamiques consistait a optimiser l'endurance du vol en specifiant l'angle de tangage de l'aile tout au long de la trajectoire, ainsi que la direction de la poussee de l'helice. Les modeles d'helices conventionnels tiennent rarement compte des effets du mouvement du vehicule sur la poussee, et ceux qui le font supposent generalement qu'elles fonctionnent dans des conditions d'ecoulement axial. Cependant, les helices des aeronefs avec des rotors basculants se trouvent souvent dans des conditions d'ecoulement oblique. Nous proposons un modele de poussee qui s'etend sur 360°, fonde sur l'hypothese qu'il n'y a pas de perte de poussee dans un ecoulement transversal. Dans les conditions de fonctionnement les plus courantes, notre modele a donne lieu a une erreur absolue moyenne de quelques pour cent de la poussee maximale.
533 $a Electronic reproduction. $b Ann Arbor, Mich. : $c ProQuest, $d 2023
538 $a Mode of access: World Wide Web
650 4 $a Aircraft. $3 832698
650 4 $a Motion control. $3 3681673
650 4 $a Unmanned aerial vehicles. $3 3560267
650 4 $a Wind. $3 3681788
650 4 $a Visualization. $3 586179
650 4 $a Neural networks. $3 677449
650 4 $a Controllers. $3 3559217
650 4 $a Aerospace engineering. $3 1002622
650 4 $a Artificial intelligence. $3 516317
650 4 $a Atmospheric sciences. $3 3168354
650 4 $a Engineering. $3 586835
650 4 $a Robotics. $3 519753
650 4 $a Transportation. $3 555912
655 7 $a Electronic books. $2 lcsh $3 542853
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710 2 $a ProQuest Information and Learning Co. $3 783688
710 2 $a McGill University (Canada). $3 1018122
773 0 $t Masters Abstracts International $g 83-10.
856 4 0 $u http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=29043507 $z click for full text (PQDT)