A survey of hybrid Unmanned Aerial Vehicles

Saeed, Adnan S.; Younes, Ahmad Bani; Cai, Chenxiao; Cai, Guowei

doi:10.1016/j.paerosci.2018.03.007

Cited by 241 publications

(123 citation statements)

References 17 publications

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“…Currently, UAVs are widely used in various military and civilian applications due to their flexibility in configuration, low manufacturing and operating costs, and not risking pilots in demanding missions, such as surveillance, tracking, environment observation, fish finding, and law enforcement. [1][2][3] Most UAV applications require UAVs that are capable of doing a wide range of different and complementary operations within a composite mission. 4 However, conventional fixed-wing UAVs generally have good cruise performance, can fly for long durations at high speeds, and are independent of wind situations within a wide range, 5 but these UAVs suffer from the requirement of runways or special launch and recovery equipment such as catapult launchers, parachutes, or nets for takeoff and landing.…”

Section: Introductionmentioning

confidence: 99%

“…2 Studies have been conducted on VTOL UAV concepts including tilt-rotor, tilt-wing, rotor-wing, tail-sitter, and quadrotor fixed-wing hybrid UAV (QFHUAV). 2,9,10 Table 1 summarizes the advantages and disadvantages of each of these types of the platforms. 2 The types of platforms that include tilt-rotor, tilt-wing, rotor-wing, and tail-sitter suffer from poor aerodynamic performance, complex control systems and transition maneuvers, unstable vertical flight and susceptibility to disturbances in transitions.…”

Section: Introductionmentioning

confidence: 99%

“…2,9,10 Table 1 summarizes the advantages and disadvantages of each of these types of the platforms. 2 The types of platforms that include tilt-rotor, tilt-wing, rotor-wing, and tail-sitter suffer from poor aerodynamic performance, complex control systems and transition maneuvers, unstable vertical flight and susceptibility to disturbances in transitions. As result, large-scale applications of these VTOL UAV concepts are not possible until the technical problems are solved.…”

Section: Introductionmentioning

confidence: 99%

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A method for evaluating the wind disturbance rejection capability of a hybrid UAV in the quadrotor mode

Zhang

Song

Wang

et al. 2019

International Journal of Micro Air Vehicles

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The wind disturbance rejection capability of a quadrotor fixed-wing hybrid unmanned aerial vehicle (QFHUAV) in the quadrotor mode is an important factor restricting its large-scale applications. In this paper, based on static equilibrium analysis of the quadrotor mode of a QFHUAV with a wind disturbance, a method for analyzing and evaluating the wind disturbance rejection capability of the QFHUAV in the quadrotor mode is presented. The six degrees-of-freedom (6-DOF) static equilibrium equations of the QFHUAV are established in headwind and crosswind situations. The maximum wind velocity that satisfies the equilibrium equations under the constraints of the maximum thrust and torque of the quadrotor propulsion system is used to determine the wind disturbance rejection capability of the QFHUAV in the quadrotor mode. A QFHUAV with a twin-boom is used as an example to analyze and evaluate its wind disturbance rejection capability in the quadrotor mode. The configuration parameters, quadrotor propulsion system parameters, and aerodynamic parameters affecting the wind disturbance rejection capability of the QFHUAV in the quadrotor mode are presented, discussed, and explained. The yawing moment from the wind disturbance is the main factor threatening the safe flight of the QFHUAV in the quadrotor mode. The rotor disk angle, the maximum thrust of the quadrotor propulsion system, and the moment arms of the components of the quadrotor propulsion system thrust are the main factors affecting the wind disturbance rejection capability of the QFHUAV in the quadrotor mode. Increasing these parameter values is an effective approach to improve the wind disturbance rejection capability of the QFHUAV in the quadrotor mode. From the perspective of wind disturbance rejection capability, tailless and X-type layouts are better choices for QFHUAVs. The correctness of results obtained by the proposed method is verified by two flight test schemes. KeywordsWind disturbance rejection capability, quadrotor fixed-wing hybrid unmanned aerial vehicle (QFHUAV), analyze and evaluate, quadrotor mode, maximum wind velocity, factors, improvement approaches

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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A method for evaluating the wind disturbance rejection capability of a hybrid UAV in the quadrotor mode

Zhang

Song

Wang

et al. 2019

International Journal of Micro Air Vehicles

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“…Hybrid UAV combine the advantage of helicopter hovering and fixed-wing range efficiency. 2 One of the many concepts for combining long range with VTOL is the tailsitter or tilt-body hybrid UAV. 3 This concept has its rotors pointed upwards during hover, but can tilt downward by 90 to transition to forward flight.…”

Section: Introductionmentioning

confidence: 99%

Modeling the unstable DelftaCopter vertical take-off and landing tailsitter unmanned air vehicle in hover and forward flight from flight test data

Wagter

Meulenbeld

2019

International Journal of Micro Air Vehicles

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The DelftaCopter is a tilt-body tailsitter unmanned air vehicle which combines a large swashplate controlled helicopter rotor with a biplane delta-wing. Previous research has shown that the large moment of inertia of the wing and fuselage significantly interacts with the dynamics of the rotor. While this rigid rotor cylinder dynamics model has allowed initial flight testing, part of the dynamics remains unexplained. In particular, higher frequency dynamics and the forward flight dynamics were not modeled. In this work, the cylinder dynamics model is compared with the tip-path plane model, which includes the steady-state flapping dynamics of the blades. The model is then extended to include the wing and elevon dynamics during forward flight. Flight test data consisting of excitations with a large frequency content are used to identify the model parameters using grey-box modeling. Since the DelftaCopter is unstable, flight tests can only be performed while at least a rate feedback controller is active. To reduce the influence of this active controller on the identification of the dynamics, one axis is identified at a time while white noise is introduced on all other axes. The tippath plane model is shown to be much more accurate in reproducing the high-frequency attitude dynamics of the DelftaCopter. The significant rotor-wing interaction is shown to differ greatly from what is seen in traditional helicopter models. Finally, an Linear-Quadratic Regulator (LQR) controller based on the tip-path plane model is derived and tested to validate its applicability. Modeling the attitude dynamics of the unstable DelftaCopter from flight test data has been shown to be possible even in the presence of the unavoidable baseline controller.

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“…Within the extensive range of drones that exists nowadays, this paper focuses on unmanned aerial vehicles (UAV) [2,3] those that operate at a chord-based…”

Section: Introductionmentioning

confidence: 99%

On the study of transitional low-Reynolds number flows over airfoils operating at high angles of attack and their prediction using transitional turbulence models

Wauters

Degroote

2018

Progress in Aerospace Sciences

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In this survey paper transitional turbulence modeling is approached from the point of view relevant to small unmanned aerial vehicles (span ≈ 1m), of which the flow is characterized by very low values of turbulent intensity and transition is predominantly of the separation induced kind. The physical mechanisms that are present during transition are discussed based on the experimental and numerical findings of the last five decades and their influence on high angle of attack behavior, with the appearance of abrupt stall, stall cells, low frequency oscillations and hysteresis are reviewed. Furthermore, an overview will be given of the different methodologies that exist to predict transitional flows. Emphasis will be placed on the modeling of separation bubbles within the RANS-based environment: a number of transitional turbulence models will be summarized and categorized based on their transition predicting methodologies. Four different turbulence models for low Reynolds number flow will be discussed in depth: Menter's k − ω SST model with Wilcox's low-Re modification, Menter & Langtry's (k − ω SST) γ − Re θ model, it's simplified (k − ω SST) γ model and Walters & Cokljat's k − k l − ω model.

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A survey of hybrid Unmanned Aerial Vehicles

Cited by 241 publications

References 17 publications

A method for evaluating the wind disturbance rejection capability of a hybrid UAV in the quadrotor mode

A method for evaluating the wind disturbance rejection capability of a hybrid UAV in the quadrotor mode

Modeling the unstable DelftaCopter vertical take-off and landing tailsitter unmanned air vehicle in hover and forward flight from flight test data

On the study of transitional low-Reynolds number flows over airfoils operating at high angles of attack and their prediction using transitional turbulence models

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