Sizing and Mission Profile Analysis of the Hybrid-Electric Propulsion System for Retrofitting a Fixed Wing VTOL Aircraft

Zong, Jianan; Zhu, Boqing; Hou, Zhanqiang; Yang, X. H.; Zhai, Jiaqi

doi:10.1155/2022/9384931

Cited by 4 publications

(1 citation statement)

References 21 publications

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“…Unmanned aerial vehicles (UAVs) have become extremely important in the areas of data collection [1], mapping, surveying, monitoring, and object tracking, among many other fields [2]. Electric propulsion systems have been preferred for small vehicles, but due to the limited endurance provided by current technology batteries [3] other technologies are used, such as Hybrid Electric Propulsion System (HEPS). In addition to the problem of carbon emission [4] of conventional propulsion systems, HEPS provides better operational flexibility, which combines the advantages of both combustion and electric propulsion approaches and offers more possibilities for managing the different mission phases while reducing the energy consumption and pollutant emissions.…”

Section: Introductionmentioning

confidence: 99%

Flight Simulation of a Hybrid Electric Propulsion VTOL UAV for Mission Performance Assessment

Benmoussa,

Gamboa

2024

Advances in Science and Technology

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Hybrid Electric Propulsion Systems (HEPS) have grown to be a promising topic of research for Unmanned Aerial Vehicles (UAVs) applications as they combine the complimentary benefits of internal combustion engine and electric propulsion systems while reducing pollutant emissions. Controlling UAVs in any flight condition is essential for its successful application in practical missions. In general, hybrid-electric UAVs exhibit three flight modes: vertical flight mode, fixed-wing mode and transition mode. The transition control design from vertical and hover flights to fixed-wing flight mode or vice versa still remains a challenge due to the multiple nonlinearities in the model and the optimal design results have a strong effect on mission performance. In the present study, a numerical model was developed to enhance the flight performance and the transition control of a hybrid electric multi-rotor UAV during a specific flight mission. This model is based on the control of forward thrust, lift thrust, and pitch angle to achieve the speed, altitude, and position defined in the mission profile of the flight simulation. The simulation results show that, of the two applied control strategies, the one that separates the segment into one below stall speed and another above stall speed provides better performance and faster response during transition from vertical flight mode (VTOL) to horizontal fight mode (fixed-wing) and vice versa, where significant changes in speed and pitching angle occur.

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Section: Introductionmentioning

confidence: 99%

Flight Simulation of a Hybrid Electric Propulsion VTOL UAV for Mission Performance Assessment

Benmoussa,

Gamboa

2024

Advances in Science and Technology

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Design, Modeling, and Testing of Hybrid-Electric Fixed-Wing VTOL Aircraft Propulsion System

Tao,

Li,

et al. 2024

Lecture Notes in Electrical Engineering

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Effect of Control Parameters on Hybrid Electric Propulsion UAV Performance for Various Flight Conditions: Parametric Study

Benmoussa

Gamboa

2023

Applied Mechanics

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Nowadays, great efforts of ongoing research are devoted to hybrid-electric propulsion technology that offers various benefits, such as reduced noise and pollution emissions and enhanced aircraft performance and fuel efficiency. The ability to estimate the performance of an aircraft in any flight situation in which it may operate is essential for aircraft development. In the current study, a simulation model was developed that allows estimating the flight performance and analyzing the mission of a fixed-wing multi-rotor Unmanned Aerial Vehicle (UAV) with a hybrid electric propulsion system (HEPS), with both conventional and Vertical Takeoff and Landing (VTOL) capabilities. The control is based on the continuous specification of pitch angle, propulsion thrust, and lift thrust to achieve the required conditions of a given flight segment. Six different missions were considered to analyze the effect of control parameters exhibiting the most influence on the UAV mission performance. An appropriate set of control parameters was selected through a multidimensional parametric study. The results show that the control parameters, if not well tuned, affect the mission performance: for example, in the deceleration transition, a longer time to reduce the cruise speed to stand still may be the result because the controller struggles to adjust the pitch angle. In addition, the implemented methodology captures the effects of transient maneuvers, unlike typical quasi-static analysis without the complexity of full simulation models.

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Sizing and Mission Profile Analysis of the Hybrid-Electric Propulsion System for Retrofitting a Fixed Wing VTOL Aircraft

Cited by 4 publications

References 21 publications

Flight Simulation of a Hybrid Electric Propulsion VTOL UAV for Mission Performance Assessment

Flight Simulation of a Hybrid Electric Propulsion VTOL UAV for Mission Performance Assessment

Design, Modeling, and Testing of Hybrid-Electric Fixed-Wing VTOL Aircraft Propulsion System

Effect of Control Parameters on Hybrid Electric Propulsion UAV Performance for Various Flight Conditions: Parametric Study

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