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Investigation of Lift Offset on Flight Dynamics Characteristics for Coaxial Compound Helicopters

Ye Yuan, Douglas Thomson, Renliang Chen

Journal of Aircraft, Volume: 56, Issue: 6, Pages: 2210 - 2222

Swansea University Author: Ye Yuan

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DOI (Published version): 10.2514/1.c035190

Abstract

The coaxial compound helicopters adopt the Lift-Offset (LOS) strategy to improve the rotor performance in high speed flight, which influences the flight dynamics characteristics of the vehicle. Thus, a flight dynamics model and an inverse simulation method are developed to assess the effect of LOS o...

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Published in: Journal of Aircraft
ISSN: 1533-3868
Published: American Institute of Aeronautics and Astronautics (AIAA) 2019
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URI: https://cronfa.swan.ac.uk/Record/cronfa58279
first_indexed 2021-10-29T13:58:28Z
last_indexed 2023-01-11T14:38:46Z
id cronfa58279
recordtype SURis
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spelling 2022-10-31T19:10:01.9454021 v2 58279 2021-10-08 Investigation of Lift Offset on Flight Dynamics Characteristics for Coaxial Compound Helicopters cdadbd9e334ad914d7968a538d9522a4 Ye Yuan Ye Yuan true false 2021-10-08 ACEM The coaxial compound helicopters adopt the Lift-Offset (LOS) strategy to improve the rotor performance in high speed flight, which influences the flight dynamics characteristics of the vehicle. Thus, a flight dynamics model and an inverse simulation method are developed to assess the effect of LOS on this helicopter. The trim results demonstrate that LOS reduces the collective and the longitudinal cyclic pitch across the flight range, and it also adds the control input of the propeller collective in hover and lower speed forward flight. LOS control strategy reduces the power consumption and increases the maximum flight speed. Also, LOS control strategy is affected by the gross weight. Furthermore, the stability is dependent on LOS due to its effect on the rotor efficiency and flapping motion. From the controllability results, LOS brings about severe coupling between the rolling moment and the collective differential input. Lastly, the Pull-up & Push-over and the Transient Turn Mission-Task-Elements (MTEs) with different LOS control strategies are assessed with inverse simulation. The results show that a reasonable LOS control strategy could not only reduce the power consumption but also have a positive influence on the oscillation in control inputs during the manoeuvre. Journal Article Journal of Aircraft 56 6 2210 2222 American Institute of Aeronautics and Astronautics (AIAA) 1533-3868 Flight Dynamics, Rotor Systems, Propellers, High Speed Flight, Aerodynamic Characteristics, Coaxial Rotor, Flapping Frequency, Aerodynamic Efficiency, Fuselages, Flight Testing 1 11 2019 2019-11-01 10.2514/1.c035190 COLLEGE NANME Aerospace, Civil, Electrical, and Mechanical Engineering COLLEGE CODE ACEM Swansea University 2022-10-31T19:10:01.9454021 2021-10-08T21:52:56.7901022 Faculty of Science and Engineering School of Aerospace, Civil, Electrical, General and Mechanical Engineering - General Engineering Ye Yuan 1 Douglas Thomson 2 Renliang Chen 3
title Investigation of Lift Offset on Flight Dynamics Characteristics for Coaxial Compound Helicopters
spellingShingle Investigation of Lift Offset on Flight Dynamics Characteristics for Coaxial Compound Helicopters
Ye Yuan
title_short Investigation of Lift Offset on Flight Dynamics Characteristics for Coaxial Compound Helicopters
title_full Investigation of Lift Offset on Flight Dynamics Characteristics for Coaxial Compound Helicopters
title_fullStr Investigation of Lift Offset on Flight Dynamics Characteristics for Coaxial Compound Helicopters
title_full_unstemmed Investigation of Lift Offset on Flight Dynamics Characteristics for Coaxial Compound Helicopters
title_sort Investigation of Lift Offset on Flight Dynamics Characteristics for Coaxial Compound Helicopters
author_id_str_mv cdadbd9e334ad914d7968a538d9522a4
author_id_fullname_str_mv cdadbd9e334ad914d7968a538d9522a4_***_Ye Yuan
author Ye Yuan
author2 Ye Yuan
Douglas Thomson
Renliang Chen
format Journal article
container_title Journal of Aircraft
container_volume 56
container_issue 6
container_start_page 2210
publishDate 2019
institution Swansea University
issn 1533-3868
doi_str_mv 10.2514/1.c035190
publisher American Institute of Aeronautics and Astronautics (AIAA)
college_str Faculty of Science and Engineering
hierarchytype
hierarchy_top_id facultyofscienceandengineering
hierarchy_top_title Faculty of Science and Engineering
hierarchy_parent_id facultyofscienceandengineering
hierarchy_parent_title Faculty of Science and Engineering
department_str School of Aerospace, Civil, Electrical, General and Mechanical Engineering - General Engineering{{{_:::_}}}Faculty of Science and Engineering{{{_:::_}}}School of Aerospace, Civil, Electrical, General and Mechanical Engineering - General Engineering
document_store_str 0
active_str 0
description The coaxial compound helicopters adopt the Lift-Offset (LOS) strategy to improve the rotor performance in high speed flight, which influences the flight dynamics characteristics of the vehicle. Thus, a flight dynamics model and an inverse simulation method are developed to assess the effect of LOS on this helicopter. The trim results demonstrate that LOS reduces the collective and the longitudinal cyclic pitch across the flight range, and it also adds the control input of the propeller collective in hover and lower speed forward flight. LOS control strategy reduces the power consumption and increases the maximum flight speed. Also, LOS control strategy is affected by the gross weight. Furthermore, the stability is dependent on LOS due to its effect on the rotor efficiency and flapping motion. From the controllability results, LOS brings about severe coupling between the rolling moment and the collective differential input. Lastly, the Pull-up & Push-over and the Transient Turn Mission-Task-Elements (MTEs) with different LOS control strategies are assessed with inverse simulation. The results show that a reasonable LOS control strategy could not only reduce the power consumption but also have a positive influence on the oscillation in control inputs during the manoeuvre.
published_date 2019-11-01T07:51:52Z
_version_ 1829269261526237184
score 11.0578165

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