TY - GEN
T1 - Design and testing of an in-flight thrust measurement system for a pylon-mounted miniature jet engine
AU - Bartasevicius, Julius
AU - Fleig, Pedro Alexandre Tonet
AU - Metzner, Annina
AU - Hornung, Mirko
N1 - Publisher Copyright:
© 2022, American Institute of Aeronautics and Astronautics Inc.. All rights reserved.
PY - 2022
Y1 - 2022
N2 - Optimization of aircraft’s performance often requires careful consideration of aerodynamic drag. However, direct measurement of drag of a flying vehicle is not feasible. Therefore, in order to measure the change in drag for different configurations of a flying aircraft, in-flight thrust measurement is necessary, which can consequently be used to derive drag. For this reason, the design of an in-flight thrust measurement system for a pylon-mounted jet engine is presented. The system is based on the trunnion thrust method. The design process is described, including a review of state of the art as well as measurement error consideration. Calibration methods are presented. During the calibration, the thrust root-mean-square error of 0.64 N was observed. The system was flight tested and proved to work reliably in real-life conditions. Finally, the flight test data was used to generate a thrust model based on engine parameters.
AB - Optimization of aircraft’s performance often requires careful consideration of aerodynamic drag. However, direct measurement of drag of a flying vehicle is not feasible. Therefore, in order to measure the change in drag for different configurations of a flying aircraft, in-flight thrust measurement is necessary, which can consequently be used to derive drag. For this reason, the design of an in-flight thrust measurement system for a pylon-mounted jet engine is presented. The system is based on the trunnion thrust method. The design process is described, including a review of state of the art as well as measurement error consideration. Calibration methods are presented. During the calibration, the thrust root-mean-square error of 0.64 N was observed. The system was flight tested and proved to work reliably in real-life conditions. Finally, the flight test data was used to generate a thrust model based on engine parameters.
UR - http://www.scopus.com/inward/record.url?scp=85123630797&partnerID=8YFLogxK
U2 - 10.2514/6.2022-1827
DO - 10.2514/6.2022-1827
M3 - Conference contribution
AN - SCOPUS:85123630797
SN - 9781624106316
T3 - AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022
BT - AIAA SciTech Forum 2022
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022
Y2 - 3 January 2022 through 7 January 2022
ER -