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Flight Testing Small, Electric Powered Unmanned Aerial Vehicles

Record Type:	Language materials, printed : Monograph/item
Title/Author:	Flight Testing Small, Electric Powered Unmanned Aerial Vehicles/ Jon Neal Ostler.
Author:	Ostler, Jon Neal,
Description:	1 electronic resource (53 pages)
Notes:	Source: Masters Abstracts International, Volume: 82-04.
Contained By:	Masters Abstracts International82-04.
Subject:	Mechanical engineering. -
Online resource:	http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=28108940
ISBN:	9798662541511

Flight Testing Small, Electric Powered Unmanned Aerial Vehicles
Ostler, Jon Neal,

Flight Testing Small, Electric Powered Unmanned Aerial Vehicles [electronic resource] /Jon Neal Ostler. - 1 electronic resource (53 pages)

Source: Masters Abstracts International, Volume: 82-04.

Flight testing methods are developed to find the drag polar for small UAVs powered by electric motors with fixed-pitch propellers. Wind tunnel testing was used to characterize the propeller-motor efficiency. The drag polar was constructed using data from flight tests. The proposed methods were implemented for a small UAV. A drag polar was found for this aircraft with CDo equal to 0.021, K1 equal to 0.229, and K2 equal to -0.056. This drag polar was then used to find the following performance parameters; maximum velocity, minimum velocity, velocity for maximum range, velocity for maximum endurance, maximum rate of climb, maximum climb angle, minimum turn radius, maximum turn rate, and maximum bank angle. Applications in UAV control and mission planning are also proposed.

English

ISBN: 9798662541511Subjects--Topical Terms:

557493
Mechanical engineering.
Subjects--Index Terms:

Unmanned aerial Vehicles

Flight Testing Small, Electric Powered Unmanned Aerial Vehicles
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520 # $a Flight testing methods are developed to find the drag polar for small UAVs powered by electric motors with fixed-pitch propellers. Wind tunnel testing was used to characterize the propeller-motor efficiency. The drag polar was constructed using data from flight tests. The proposed methods were implemented for a small UAV. A drag polar was found for this aircraft with CDo equal to 0.021, K1 equal to 0.229, and K2 equal to -0.056. This drag polar was then used to find the following performance parameters; maximum velocity, minimum velocity, velocity for maximum range, velocity for maximum endurance, maximum rate of climb, maximum climb angle, minimum turn radius, maximum turn rate, and maximum bank angle. Applications in UAV control and mission planning are also proposed.
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653 # # $a Unmanned aerial Vehicles
653 # # $a Propeller-motor efficiency
653 # # $a Drag polar
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