The NederDrone: A hybrid lift, hybrid energy hydrogen UAV

Wagter, Christophe De; Remes, B. D. W.; Smeur, E.J.J.; Tienen, F. van; Ruijsink, R.; Hecke, Kevin van; Horst, E. van der

doi:10.1016/j.ijhydene.2021.02.053

Cited by 31 publications

(5 citation statements)

References 42 publications

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“…The passive EMS has the advantages of simplicity, weight reduction, and power loss reduction associated with the power converter, and it has been applied in fuel cell UAVs. For example, the passive EMS is applied to a tail-sitter hybrid lift UAV, which is powered by the fuel cell and lithium battery [49]. Although passive EMS is easy to be implemented, it cannot utilize the different characteristics of the power sources, which results in low efficiency.…”

Section: Energy Management Strategies For Fuel Cell Uavsmentioning

confidence: 99%

A Comprehensive Review on Fuel Cell UAV Key Technologies: Propulsion System, Management Strategy, and Design Procedure

Huangfu

et al. 2022

IEEE Trans. Transp. Electrific.

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Unmanned aerial vehicles (UAVs) can be regarded as one of the most emerging technologies. Compared with piloted aerial vehicles, UAVs qualify for higher safety and lower cost, and they are more suitable for dangerous missions. Recently, fuel cell UAVs have obtained more and more attention due to their relatively higher energy density. However, their propulsion system still needs to be further improved to meet different requirements of performing difficult tasks. This article aims to give a comprehensive review of the key technologies of fuel cell UAVs. Firstly, various architectures of the propulsion system and corresponding advantages and disadvantages are introduced. Then, three kinds of management strategies for fuel cell UAVs are reviewed. Next, some special applications and considered design procedures are summarized. Compared with other review papers, this paper tries to cover more aspects of fuel cell UAVs. Since these aspects have a tight relationship with each other, giving a comprehensive review can be more beneficial to us to understand the state-of-the-art development of propulsion systems for fuel cell UAVs. The conclusions show that advanced propulsion architectures, efficient online energy management strategies, and professional design procedures are still in urgent demand in the commercial process of fuel cell UAVs.

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Section: Energy Management Strategies For Fuel Cell Uavsmentioning

confidence: 99%

A Comprehensive Review on Fuel Cell UAV Key Technologies: Propulsion System, Management Strategy, and Design Procedure

Huangfu

et al. 2022

IEEE Trans. Transp. Electrific.

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“…At each airspeed, the wing was rotated 360∘ at a speed of 2∘ per second, such that all possible AoA are covered. Based on experience with the Nederdrone, 19 equipped with wings of this kind, a throttle setting of around 60% is typical during the hover and transition phase. To investigate the effect of the throttle, the experiment was performed with 50% throttle, 70% throttle and once without propellers mounted.…”

Section: Experiments Setup and Measurementsmentioning

confidence: 99%

Wind tunnel tests of a wing at all angles of attack

Smeur

Croon

2022

International Journal of Micro Air Vehicles

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Tailsitters have complex aerodynamics that make them hard to control throughout the entire flight envelope, especially at very high angle of attack (AoA) and reverse flow conditions. The development of controllers for these vehicles is hampered by the absence of publicly available data on forces and moments experienced in such conditions. In this paper, wind tunnel experiments are performed under different flap deflections and throttle settings at all possible AoA. The dataset is made open access. Our analysis of the data shows for the tested wing, flap deflections greatly affect the lift coefficient and stall occurs at [Formula: see text] AoA as well as [Formula: see text]. Wing-propeller interaction is studied by analyzing the propeller induced force in the axis orthogonal to the thrust axis, which is dependent on AoA, airspeed, flap deflections and thrust in a nonlinear and coupled manner. The influence of inverse flow on the wing is also discussed: The data confirm that when the airflow over the wing is reversed, flap deflections will affect the pitch moment in an opposite way compared to the non-reversed case, but this opposite effect can be avoided by increasing the throttle setting. The data show the exact relationship between flap deflections and forces in this condition. Moreover, it is found that the flap control effectiveness for a wing with or without spinning propellers is usually higher around zero degrees AoA than at [Formula: see text] and it is more effective to change the flaps from [Formula: see text] to [Formula: see text] than from [Formula: see text] to the respective [Formula: see text].

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“…Flight testing of Unmanned Aerial Vehicles (UAVs) has increased with advancements in microcontroller hardware and sensors, and the ease of integration with tools such as MATLAB/Simulink. Recent UAV flight test campaigns include [89][90][91][92][93][94][95][96][97][98][99], which also include flight testing with incremental type control laws in [100][101][102][103][104]. Subscale flight testing and system identification was performed in [105][106][107][108][109].…”

Section: Introductionmentioning

confidence: 99%

Practical System Identification and Incremental Control Design for a Subscale Fixed-Wing Aircraft

Steffensen,

Ginnell,

Holzapfel

2024

Actuators

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An incremental differential proportional integral (iDPI) control law using eigenstructure assignment gain design is tested in flight on a subscale platform to validate its suitability for fixed-wing flight control. A kinematic relation for the aerodynamic side-slip angle rate is developed to apply a pseudo full state feedback. In order to perform the gain design and assessment, a plant model is estimated using flight test data from gyro, accelerometer, airspeed and surface deflection measurements during sine-sweep excitations. Transfer function models for the actuators and surface deflections are identified both in-flight and on the ground for several different actuators and control surfaces using hall sensor surface deflection measurements. The analysis reveals a large variation in bandwidth between the different types of servo motors. Flight test results are presented which demonstrates that the plant model estimates based on tests with good frequency excitation, high bandwidth actuators and surface deflection measurements can be used to reasonably predict the closed-loop dynamic behavior of the aircraft. The closed-loop flight test results of the iDPi control law show good performance and lays the groundwork for further development.

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The NederDrone: A hybrid lift, hybrid energy hydrogen UAV

Cited by 31 publications

References 42 publications

A Comprehensive Review on Fuel Cell UAV Key Technologies: Propulsion System, Management Strategy, and Design Procedure

A Comprehensive Review on Fuel Cell UAV Key Technologies: Propulsion System, Management Strategy, and Design Procedure

Wind tunnel tests of a wing at all angles of attack

Practical System Identification and Incremental Control Design for a Subscale Fixed-Wing Aircraft

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