Variable Pitch Propeller for UAV-Experimental Tests

被引:18
作者
Podsedkowski, Maciej [1 ]
Konopinski, Rafal [1 ]
Obidowski, Damian [2 ]
Koter, Katarzyna [1 ]
机构
[1] Lodz Univ Technol, Inst Machine Tools & Prod Engn, PL-90924 Lodz, Poland
[2] Lodz Univ Technol, Inst Turbomachinery, PL-90924 Lodz, Poland
关键词
UAV; variable pitch propeller; drone rotor; energy optimization; drone; experimental aerodynamics; HOVER PERFORMANCE; DESIGN; FLIGHT; ROTOR; CHALLENGES; SYSTEM;
D O I
10.3390/en13205264
中图分类号
TE [石油、天然气工业]; TK [能源与动力工程];
学科分类号
0807 ; 0820 ;
摘要
Growth in application fields of unmanned aerial vehicles (UAVs) and an increase in their total number are followed by higher and higher expectations imposed on improvements in UAV propulsion and energy management systems. Most commercial vertical takeoff and landing (VTOL) UAVs employ a constant pitch propeller that forces a mission execution tradeoff in the majority of cases. An alternative solution, presented here, consists of the use of a variable pitch propeller. The paper summarizes experimental measurements of the propulsion system equipped with an innovative variable pitch rotor. The investigations incorporated characteristics of the rotor for no wind conditions and a new approach to optimize pitch settings in hover flight as a function of UAV weight and energy consumption. As UAV battery capacity is always limited, efficient energy management is the only way to increase UAV mission performance. The study shows that use of a variable pitch propeller can increase the maximal takeoff weight of the aircraft and improve power efficiency in hover, especially if load varies for different missions. The maximal thrust measured was 31% higher with respect to the original blade settings. The coefficient of thrust during hover showed an increase of 2.6% up to 7.5% for various pitch angles with respect to the original fixed propeller.
引用
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页数:16
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