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A Study of Hybrid Airfoil Design Method Read chapter Read first chapter

2019 | OriginalPaper | Chapter

PIO Engineering Prediction Methods and Verification of Airworthiness Compliance for Civil Aircraft

Authors : Jun Liu, Nanbo Xu

Published in: The Proceedings of the 2018 Asia-Pacific International Symposium on Aerospace Technology (APISAT 2018)

Publisher: Springer Singapore

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Abstract

PIO (Pilot-Induced-Oscillation) is due to the mutual influence between abnormal aircraft response and pilot’s dynamic characteristic which causes the phenomenon that aircraft-pilot closed loop is instable. Therefore, airworthiness regulations (FAA25 CS25 CCAR25) 143 (a) (b) have given specific requirements for these. At the preliminary design stage of control law design, PIO tendency shall be analyzed by engineering prediction methods which will confirm whether the design of the FBW control law is suitable. In the detailed design stage, PIO tendency will be analyzed by means of simulator test with pilot in loop. During verification of worthiness compliance, evaluation criteria of PIO shall be determined according to recommended methods of AC25-7C and verify airworthiness compliance through MOC6 and MOC8. Finally, the data of flight test and/or simulator test with pilot comments show that there is no PIO tendency which meets the requirements of airworthiness regulations.

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previous chapter Optimal Linear-Quadratic Guidance Law Considering Autopilot First-Order Lag with Terminal Acceleration Constraint
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Metadata
Title
PIO Engineering Prediction Methods and Verification of Airworthiness Compliance for Civil Aircraft
Authors
Jun Liu
Nanbo Xu
Copyright Year
2019
Publisher
Springer Singapore
Book
The Proceedings of the 2018 Asia-Pacific International Symposium on Aerospace Technology (APISAT 2018)

Print ISBN: 978-981-13-3304-0

Electronic ISBN: 978-981-13-3305-7

Copyright Year: 2019

DOI
https://doi.org/10.1007/978-981-13-3305-7_188

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