Flight Test Results for a Fuel Cell Unmanned Aerial Vehicle

2007 ◽  
Author(s):  
Thomas Bradley ◽  
Blake Moffitt ◽  
David Parekh ◽  
Dimitri Mavris
Keyword(s):  
Fuel Cell ◽  
Unmanned Aerial Vehicle ◽  
Flight Test ◽  
Test Results ◽  
Aerial Vehicle

scholarly journals Integrated Process Control‐Power Management System Design and Flight Performance Tests for Fuel Cell Powered Mini‐Unmanned Aerial Vehicle

2021 ◽  
Vol 9 (3) ◽  
pp. 2170031
Author(s):  
Betül Erdör Türk ◽  
Mustafa Hadi Sarul ◽  
Ekrem Çengelci ◽  
Çiğdem İyigün Karadağ ◽  
Fatma Gül Boyacı San ◽  
...  
Keyword(s):  
Fuel Cell ◽  
System Design ◽  
Power Management ◽  
Unmanned Aerial Vehicle ◽  
Flight Performance ◽  
Performance Tests ◽  
Integrated Process ◽  
Control Power ◽  
Aerial Vehicle ◽  
Power Management System

Stepdown Converter of a Fuel-Cell-Based Power Plant for an Unmanned Aerial Vehicle

2021 ◽  
Vol 92 (10) ◽  
pp. 618-622
Author(s):  
Yu. A. Burtsev ◽  
A. V. Pavlenko ◽  
I. V. Vasyukov ◽  
V. S. Puzin ◽  
A. V. Zhivodernikov
Keyword(s):  
Fuel Cell ◽  
Power Plant ◽  
Unmanned Aerial Vehicle ◽  
Aerial Vehicle

scholarly journals Aerodynamic Analysis of Blended Wing Body - Unmanned Aerial Vehicle (BWB-UAV) Equipped with Horizontal Stabilizers

2019 ◽  
Vol 256 ◽  
pp. 02004
Author(s):  
Nornashiha Mohd Saad ◽  
Wirachman Wisnoe ◽  
Rizal Effendy Mohd Nasir ◽  
Zurriati Mohd Ali ◽  
Ehan Sabah Shukri Askari
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Cfd Simulation ◽  
Lift Coefficient ◽  
Angle Of Attack ◽  
Flight Test ◽  
Longitudinal Direction ◽  
Static Stability ◽  
Pitching Moment ◽  
Aerial Vehicle ◽  
Blended Wing Body

This paper presents an aerodynamic characteristic study in longitudinal direction of UiTM Blended Wing Body-Unmanned Aerial Vehicle Prototype (BWB-UAV Prototype) equipped with horizontal stabilizers. Flight tests have been conducted and as the result, BWB experienced overturning condition at certain angle of attack. Horizontal stabilizer was added at different location and size to overcome the issue during the flight test. Therefore, Computational Fluid Dynamics (CFD) analysis is performed at different configuration of horizontal stabilizer using Spalart - Allmaras as a turbulence model. CFD simulation of the aircraft is conducted at Mach number 0.06 or v = 20 m/s at various angle of attack, α. The data of lift coefficient (CL), drag coefficient (CD), and pitching moment coefficient (CM) is obtained from the simulations. The data is represented in curves against angle of attack to measure the performance of BWB prototype with horizontal stabilizer. From the simulation, configuration with far distance and large horizontal stabilizer gives steeper negative pitching moment slope indicating better static stability of the aircraft.

scholarly journals Design of a Low-Cost Fixed Wing UAV

2018 ◽  
Vol 159 ◽  
pp. 02045
Author(s):  
Mochammad Ariyanto ◽  
Joga D. Setiawan ◽  
Teguh Prabowo ◽  
Ismoyo Haryanto ◽  
Munadi
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Low Cost ◽  
Flight Test ◽  
Body Part ◽  
Aerial Vehicle ◽  
Straight Wing

This research will try to design a low cost of fixed-wing unmanned aerial vehicle (UAV) using low-cost material that able to fly autonomously. Six parameters of UAV’s structure will be optimized based on basic airframe configuration, wing configuration, straight wing, tail configuration, fuselage material, and propeller location. The resulted and manufactured prototype of fixed-wing UAV will be tested in autonomous fight tests. Based on the flight test, the developed UAV can successfully fly autonomously following the trajectory command. The result shows that low-cost material can be used as a body part of fixed-wing UAV.

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