Design, modelling and hovering control of a tail-sitter with single thrust-vectored propeller

Wang, Wufan; Zhu, Jihong; Kuang, Minchi

doi:10.1109/iros.2017.8206492

Cited by 9 publications

(9 citation statements)

References 15 publications

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Section: Related Workmentioning

confidence: 99%

“…Although models with flying wings predominate, models with a conventional configuration consisting of a fuselage and empennage are also studied [33], [41]. Also, models with only a single rotor are under study [13], [41], [43]. Due to the complexity of control, they use more complex structures, with fuselage and empennage, and vertical and horizontal stabilizers with control surfaces [43].…”

Section: Related Workmentioning

confidence: 99%

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Double Hybrid Tailsitter Unmanned Aerial Vehicle With Vertical Takeoff and Landing

2022

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We propose a new concept and architectural design for a double hybrid tailsitter unmanned aerial vehicle with vertical takeoff and landing capability. Basically, it consists of a modified flying wing with a single combustion powertrain set and a multirotor with 2 powertrain sets with electric motors. To this end, we have designed, built, and tested a prototype that spends less energy on vertical taking off and landing and also on horizontal flight, for maximizing flight endurance and distance. With electric propellers fixed at the leading wing edge, the tailsitter has two standard surfaces for elevation control and two vertical stabilizers that are used to give the necessary direction on vertical takeoff and landing. Experiments and results show the versatility of our hybrid tailsitter for operations in a restricted field. We performed several tests starting with the aircraft on the ground in vertical positioning. These tests include executing vertical takeoffs and landing, transitions from vertical to horizontal flight modes and transitions back from horizontal to vertical flight modes, and hovering, which were carried out successfully. Transition fourth and back from combustion to multirotor modes are inherent to some of those flight mode transitions, which have been performed smoothly. We also performed tests (in bench) to estimate the flight endurance. Final autonomous flight adjustments were not performed due to the Covid-19 pandemic caused by SARS-CoV-2. To this end the proposed and currently built prototype has proven to be functional as an effective hybrid UAV system.

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Section: Related Workmentioning

confidence: 99%

Section: Related Workmentioning

confidence: 99%

Double Hybrid Tailsitter Unmanned Aerial Vehicle With Vertical Takeoff and Landing

2022

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“…Equation (19) describes the gyroscopic interaction between the propellers and the fuselage with J p equals to the propeller inertia. The vehicle's equations of motion are given by equation (21).…”

Section: Equations Of Motionmentioning

confidence: 99%

“…19,20 However, instability problems with adaptive control methods can still exist with regard to unmodeled dynamics or inaccurate models used in the adaptation criterion of controller’s gains. Different research topics applying nonlinear control techniques on hybrid MAVs, such as backstepping, 19,21,22 NDI 20,23,24 and INDI, 25 appears to be positively researched in literature. The INDI approach, which is a control that depends less on the model, was experimentally flight tested providing excellent performance against wind disturbances.…”

Section: Introductionmentioning

confidence: 99%

Model-free control algorithms for micro air vehicles with transitioning flight capabilities

Barth

Condomines

Bronz

et al. 2020

International Journal of Micro Air Vehicles

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Micro air vehicles with transitioning flight capabilities, or simply hybrid micro air vehicles, combine the beneficial features of fixed-wing configurations, in terms of endurance, with vertical takeoff and landing capabilities of rotorcrafts to perform five different flight phases during typical missions, such as vertical takeoff, transitioning flight, forward flight, hovering and vertical landing. This promising micro air vehicle class has a wider flight envelope than conventional micro air vehicles, which implies new challenges for both control community and aerodynamic designers. One of the major challenges of hybrid micro air vehicles is the fast variation of aerodynamic forces and moments during the transition flight phase which is difficult to model accurately. To overcome this problem, we propose a flight control architecture that estimates and counteracts in real-time these fast dynamics with an intelligent feedback controller. The proposed flight controller is designed to stabilize the hybrid micro air vehicle attitude as well as its velocity and position during all flight phases. By using model-free control algorithms, the proposed flight control architecture bypasses the need for a precise hybrid micro air vehicle model that is costly and time consuming to obtain. A comprehensive set of flight simulations covering the entire flight envelope of tailsitter micro air vehicles is presented. Finally, real-world flight tests were conducted to compare the model-free control performance to that of the Incremental Nonlinear Dynamic Inversion controller, which has been applied to a variety of aircraft providing effective flight performances.

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“…In the literature, several designs were proposed for hybrid UAVs able to take off and land vertically and fly horizontally with high velocity as tailsitters. These aircraft usually contain complex mechanism, like ducted-fan rotors with control vanes (NALDI; MAR-CONI, 2013; ARGYLE; BEARD; MORRIS, 2013; JUNG; SHIM, 2012), tilting rotors (GUERRERO et al, 2009;GARCIA-SALAZAR et al, 2008;PAPACHRISTOS;TZES, 2013;ROSAS et al, 2012;CETINSOY, 2015;, counter-rotating propellers (GARCIA et al, 2012), cyclic/collective rotor (SONG; UNDERWOOD, 2007) and vectored-thrust motors (XILI;YONG;JIHONG, 2008;HANG et al, 2013;MIYAZAKI;TSUBAKINO, 2017;KUANG, 2017).…”

Section: Related Workmentioning

confidence: 99%

Development of an autonomous unmanned aerial vehicle specification of a fixed-wing vertical takeoff and landing aircraft

Silva¹

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Design, modelling and hovering control of a tail-sitter with single thrust-vectored propeller

Cited by 9 publications

References 15 publications

Double Hybrid Tailsitter Unmanned Aerial Vehicle With Vertical Takeoff and Landing

Double Hybrid Tailsitter Unmanned Aerial Vehicle With Vertical Takeoff and Landing

Model-free control algorithms for micro air vehicles with transitioning flight capabilities

Development of an autonomous unmanned aerial vehicle specification of a fixed-wing vertical takeoff and landing aircraft

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