TY - JOUR
T1 - Design and implementation of an innovative airborne electric propulsion measure system of fixed-wing UAV
AU - Zhao, Anmin
AU - Zhang, Jun
AU - Li, Ke
AU - Wen, Dongsheng
N1 - Publisher Copyright:
© 2020 Elsevier Masson SAS
PY - 2021/2
Y1 - 2021/2
N2 - The electric propulsion system combination of unmanned aerial vehicles (UAVs) plays a vital role in improving the endurance time for newly designed aircraft. To realize the measurement of the parameters of the electric propulsion system in an actual flight, a novel airborne powered test scheme is proposed and developed in this work. Both the flight test and wind tunnel experimental study are performed to estimate the accuracy of the test approach by discussing the effect of the airspeed on the electric aircraft powered system. Additionally, the thrust, torque, and efficiency curves are also studied as the increase of revolutions per minute (RPM) in flight tests. The results suggest that the innovatively designed electric-powered test system is capable of measuring the aircraft propulsion efficiency parameters within 4% when compared to a wind tunnel experiment. Compared with the wind tunnel experiment, the uncertainty of the airborne test is 0.32% (motor speed), 0.83% (voltage), 1.17% (current), 0.93% (thrust), and 2.0% (torque). This kind of airborne test method can replace the high cost of wind tunnel test, which is more suitable for fixed-wing aircraft, has high application potential for the propulsion system optimization, and real-time state monitoring of power equipment.
AB - The electric propulsion system combination of unmanned aerial vehicles (UAVs) plays a vital role in improving the endurance time for newly designed aircraft. To realize the measurement of the parameters of the electric propulsion system in an actual flight, a novel airborne powered test scheme is proposed and developed in this work. Both the flight test and wind tunnel experimental study are performed to estimate the accuracy of the test approach by discussing the effect of the airspeed on the electric aircraft powered system. Additionally, the thrust, torque, and efficiency curves are also studied as the increase of revolutions per minute (RPM) in flight tests. The results suggest that the innovatively designed electric-powered test system is capable of measuring the aircraft propulsion efficiency parameters within 4% when compared to a wind tunnel experiment. Compared with the wind tunnel experiment, the uncertainty of the airborne test is 0.32% (motor speed), 0.83% (voltage), 1.17% (current), 0.93% (thrust), and 2.0% (torque). This kind of airborne test method can replace the high cost of wind tunnel test, which is more suitable for fixed-wing aircraft, has high application potential for the propulsion system optimization, and real-time state monitoring of power equipment.
KW - Airborne electric propulsion test system
KW - Efficiency parameters
KW - Fixed-wing unmanned aerial vehicle (UAV)
KW - Flight test
KW - Wind tunnel experiment
UR - https://www.scopus.com/pages/publications/85097717397
U2 - 10.1016/j.ast.2020.106357
DO - 10.1016/j.ast.2020.106357
M3 - 文章
AN - SCOPUS:85097717397
SN - 1270-9638
VL - 109
JO - Aerospace Science and Technology
JF - Aerospace Science and Technology
M1 - 106357
ER -