Modelling and Design of a Hybrid Aerial Vehicle Combining VTOL Capabilities with Fixed Wing Aircraft

Joshi, Alaukik; Amritanshu, Tripathi; Ponnalgu, R. N.

doi:10.1109/ica.2019.8916678

Cited by 8 publications

(2 citation statements)

References 13 publications

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“…This means that after taking off vertically, they are capable of travelling at fast speeds using fixed wings like an airplane. Although most hybrid VTOL aircrafts are either unmanned or remotely controlled, there exist some exceptions [3,4]. A unique example is the V-22 Osprey by Boeing, which is a manned aircraft with the ability to significantly change the angle of its rotors, and thus use the rotors for both vertical and horizontal acceleration.…”

Section: Hybrid Vs Rotary Wing Aircraftmentioning

confidence: 99%

Vertical takeoff and landing aircraft: Categories, applications, and technology

Qin

2023

TNS

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A Vertical Take-Off and Landing (VTOL) aircraft is an aircraft with the ability to take off and land vertically. The ability of removing the need for a runway allows VTOL aircraft to be used for applications that standard aircraft cannot be used for. These applications include military, firefighting, and transportation applications. For the purposes of this paper, helicopters will be considered to be VTOL aircraft, as they fit the general criteria and are among the first to be widely used. VTOL aircraft can be split into several categories, including hybrid VTOL aircraft, VTOL Unmanned Aerial Vehicles, and electric VTOL aircraft. These categories of VTOL aircraft are compared. Famous VTOL aircrafts like Osprey and Harrier are introduced. The technology behind VTOL aircraft is explained, and the ways in which VTOL aircraft can be made useful are reviewed. In addition, the prospect of VTOL aircraft has been made. This paper may offer a reference for the future works about VTOL.

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Section: Hybrid Vs Rotary Wing Aircraftmentioning

confidence: 99%

Vertical takeoff and landing aircraft: Categories, applications, and technology

Qin

2023

TNS

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“…Tilt-rotor UAVs have been proposed in different research works (21,(51)(52)(53)(54)(55)(56) , and tilt-body UAVs were presented in Refs (16,57,58) , are another category of transformable UAVs that presents several advantages such as enhanced agility and precision, high endurance and maneuverability, adjustment of the thrust force by compensation in the event of a breakdown, horizontal and vertical displacement, elimination of the over-actuation problem and higher speed. However, the main disadvantage of tilting rotors is their poor hover performance caused by the small rotor diameters and large rotor mast.…”

Section: Related Workmentioning

confidence: 99%

Towards a new design with generic modeling and adaptive control of a transformable quadrotor

2021

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Recently, transformable Unmanned Aerial Vehicles (UAVs) have become a subject of great interest in the field of flying systems, due to their maneuverability, agility and morphological capacities. They can be used for specific missions and in more congested spaces. Moreover, this novel class of UAVs is considered as a viable solution for providing flying robots with specific and versatile functionalities. In this paper, we propose (i) a new design of a transformable quadrotor with (ii) generic modeling and (iii) adaptive control strategy. The proposed UAV is able to change its flight configuration by rotating its four arms independently around a central body, thanks to its adaptive geometry. To simplify and lighten the prototype, a simple mechanism with a light mechanical structure is proposed. Since the Center of Gravity (CoG) of the UAV moves according to the desired morphology of the system, a variation of the inertia and the allocation matrix occurs instantly. These dynamics parameters play an important role in the system control and its stability, representing a key difference compared with the classic quadrotor. Thus, a new generic model is developed, taking into account all these variations together with aerodynamic effects. To validate this model and ensure the stability of the designed UAV, an adaptive backstepping control strategy based on the change in the flight configuration is applied. MATLAB simulations are provided to evaluate and illustrate the performance and efficiency of the proposed controller. Finally, some experimental tests are presented.

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