Design of an unmanned aircraft system for high-altitude 1 kW fuel cell power system

Reid, William A.; Albayati, Ibrahim M.

doi:10.1007/s42401-021-00101-1

Cited by 6 publications

(7 citation statements)

References 15 publications

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“…The constant mass of UAV is 9.65 Kg and battery of UAV is 500 KJ [71]. The maximum speed at which UAV can fly is 15 m/s [72]. The time of flight and time of hovering is 1 sec and 7 sec respectively.…”

Section: ) Simulation Parametersmentioning

confidence: 99%

A DRL Strategy for Optimal Resource Allocation Along With 3D Trajectory Dynamics in UAV-MEC Network

et al. 2023

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Advances in Unmanned Air Vehicle (UAV) technology have paved a way for numerous configurations and applications in communication systems. However, UAV dynamics play an important role in determining its effective use. In this article, while considering UAV dynamics, we evaluate the performance of a UAV equipped with a Mobile-Edge Computing (MEC) server that provides services to End-user Devices (EuDs). The EuDs due to their limited energy resources offload a portion of their computational task to nearby MEC-based UAV. To this end, we jointly optimize the computational cost and 3D UAV placement along with resource allocation subject to the network, communication, and environment constraints. A Deep Reinforcement Learning (DRL) technique based on a continuous action space approach, namely Deep Deterministic Policy Gradient (DDPG) is utilized. By exploiting DDPG, we propose an optimization strategy to obtain an optimal offloading policy in the presence of UAV dynamics, which is not considered in earlier studies. The proposed strategy can be classified into three cases namely; training through an ideal scenario, training through error dynamics, and training through extreme values. We compared the performance of these individual cases based on cost percentage and concluded that case II (training through error dynamics) achieves minimum cost i.e., 37.75 %, whereas case I and case III settles at 67.25% and 67.50% respectively. Numerical simulations are performed, and extensive results are obtained which shows that the advanced DDPG based algorithm along with error dynamic protocol is able to converge to near optimum. To validate the efficacy of the proposed algorithm, a comparison with state-of-the-art Deep Q-Network (DQN) is carried out, which shows that our algorithm has significant improvements.

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Section: ) Simulation Parametersmentioning

confidence: 99%

A DRL Strategy for Optimal Resource Allocation Along With 3D Trajectory Dynamics in UAV-MEC Network

et al. 2023

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“…Tapering the wing provides significant aerodynamic advantages (reducing drag force and increasing lift distribution) as well as structural benefits (weight savings for the wing). In the case of UAVs, this taper ratio typically has a value of 0.5 [77,78], a value obtained from data of UAV's with similar configurations and missions. However, for the UAV model analyzed in this paper, a higher value (λ = 0.57) was chosen because a winglet will be mounted at the tip of wing.…”

Section: Uav Model Wing Designmentioning

confidence: 99%

“…This taper ratio is necessary, as the wing-tip chord needs to provide a larger surface area to facilitate the winglet connection and achieve a higher strength. The root chord of the UAV model was calculated using Equation (2) [77,78], while the tip chord was determined using Equation (3) [77,78].…”

Section: Uav Model Wing Designmentioning

confidence: 99%

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Material Extrusion Additive Manufacturing of the Composite UAV Used for Search-and-Rescue Missions

Zaharia,

Pascariu,

Chicos

et al. 2023

Drones

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The additive processes used in the manufacture of components for unmanned aerial vehicles (UAVs), from composite filaments, have an important advantage compared to classical technologies. This study focused on three-dimensional design, preliminary aerodynamic analysis, fabrication and assembly of thermoplastic extruded composite components, flight testing and search-rescue performance of an UAV. The UAV model was designed to have the highest possible structural strength (the fuselage has a structure with stiffening frames and the wing is a tri-spar), but also taking into account the limitations of the thermoplastic extrusion process. From the preliminary aerodynamic analysis of the UAV model, it was found that the maximum lift coefficient of 1.2 and the maximum drag coefficient of 0.06 were obtained at the angle of attack of 12°. After conducting flight tests, it can be stated that the UAV model, with components manufactured by the thermoplastic extrusion process, presented high stability and maneuverability, a wide range of speeds and good aerodynamic characteristics. The lack of this type of aircraft, equipped with electric motors, a traffic management system, and a thermal module designed for search-and-rescue missions, within the additive manufacturing UAV market, validates the uniqueness of the innovation of the UAV model presented in the current paper.

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Novel custom-made design and analysis of hydrogen PEM fuel cell for high endurance small UAV applications

Prajapati,

Thakar,

Markana

2023

Environ Sci Pollut Res

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The purpose of this paper is to propose a new methodology to devise a custom-made hydrogen-based proton exchange membrane fuel cell (PEMFC) system for a class of experimental fixed-wing small unmanned aerial vehicles (SUAVs). The proposed fuel cell provides three times higher flight endurance than the conventional battery-based powertrain.The chosen SUAV represents ac l a s so fh i g h -a l t i t u d eU A V s ,h a v i n g an operational altitude of 4500m ( 14,760ft), cruising speed of 12-20 m/s (39.4 -65.6 ft/s), take-off weight of 4 kg, wing-span of 1.61 m (5.28 ft) and battery-powered flight endurance of one hour. The characteristic parameters and design configurations of the fuel cell are determined by employing the first principles of electrochemistry and thermodynamics. Corresponding simulations are performed using popular development tools like MATLAB/Simulink. The vital results in the form of -polarization and power curves for fuel cell, against the current density are obtained, which are further narrowed down to meet 1 Manuscript revised tex file latex Click here to access/download;Manuscript;Revised_Manu Click here to view linked References Springer Nature 2021 L A T E X template 2 Article Title the target power requirements for determining the size of the hydrogen storage tank. The paper also comments on the auxiliary systems and fuel cell powertrain for SUAVs. Finally, the design efficiency of 54% for the fuel cell is achieved with respect to equivalent voltage for heating value with the calculated hydrogen storage tank size of 5.688 litres. This yields three times higher flight endurance as compared to the flight time found in literature for the same class of SUAVs.

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Design of an unmanned aircraft system for high-altitude 1 kW fuel cell power system

Cited by 6 publications

References 15 publications

A DRL Strategy for Optimal Resource Allocation Along With 3D Trajectory Dynamics in UAV-MEC Network

A DRL Strategy for Optimal Resource Allocation Along With 3D Trajectory Dynamics in UAV-MEC Network

Material Extrusion Additive Manufacturing of the Composite UAV Used for Search-and-Rescue Missions

Novel custom-made design and analysis of hydrogen PEM fuel cell for high endurance small UAV applications

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