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Trim investigation for coaxial rigid rotor helicopters using an improved aerodynamic interference model

Ye Yuan Orcid Logo, Renliang Chen, Pan Li

Aerospace Science and Technology, Volume: 85, Pages: 293 - 304

Swansea University Author: Ye Yuan Orcid Logo

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DOI (Published version): 10.1016/j.ast.2018.11.044

Abstract

The coaxial rigid rotor helicopter has been proposed as a future high-performance rotorcraft concept.However, the aerodynamic interference of this helicopter is complicated because it couples with theunique flapping feature of the rigid rotor, which further alters the trim characteristics of coaxial...

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Published in: Aerospace Science and Technology
ISSN: 1270-9638
Published: Elsevier BV 2019
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URI: https://cronfa.swan.ac.uk/Record/cronfa58282
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first_indexed 2021-10-29T13:43:08Z
last_indexed 2023-01-11T14:38:47Z
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spelling 2022-10-31T19:11:44.7304939 v2 58282 2021-10-08 Trim investigation for coaxial rigid rotor helicopters using an improved aerodynamic interference model cdadbd9e334ad914d7968a538d9522a4 0000-0002-7568-0130 Ye Yuan Ye Yuan true false 2021-10-08 GENG The coaxial rigid rotor helicopter has been proposed as a future high-performance rotorcraft concept.However, the aerodynamic interference of this helicopter is complicated because it couples with theunique flapping feature of the rigid rotor, which further alters the trim characteristics of coaxial rigidrotor helicopters. Thus, a multi-point vortex ring element (MVRE) model is developed to simulate theaerodynamic interference between rotors. The method for establishing this MVRE model is illustrated, anda wind tunnel experimental dataset is used to assess its precision hover and forward flight states. Next, a flight dynamics model of the coaxial rigid rotor helicopter is built based on the MVRE aerodynamic interference model and the flapping feature of the rigid rotor. The influence of the rotor wake on the fuselage and the horizontal and vertical tails can also be calculated using this model. The trim characteristics of this helicopter are evaluated with flight test data for speeds ranging from 0 m/s to 80 m/s, and the results confirm that this model can reflect the trim characteristics with satisfactory precision. In addition, the calculation process demonstrates that the MVRE model provides a much faster computing rate. Considering the aerodynamic interference and rigid rotor characteristics, the trim results of the coaxial rigid rotor helicopter present unique features: aerodynamic interference in the coaxial rotor system not only increases the collective pitch and the collective differential but also adds a negative gradient under the forward speed in the longitudinal cyclic pitch in the low-speed forward flight range. Moreover, the rotor wake effect on the other parts of the helicopter is distinct from the corresponding effects on conventional helicopters in terms of the trim characteristics. Journal Article Aerospace Science and Technology 85 293 304 Elsevier BV 1270-9638 Coaxial helicopter; Rigid rotor; Aerodynamic interference; Flight dynamics characteristics; Trim characteristics 1 2 2019 2019-02-01 10.1016/j.ast.2018.11.044 COLLEGE NANME General Engineering COLLEGE CODE GENG Swansea University 2022-10-31T19:11:44.7304939 2021-10-08T21:53:34.2733587 Faculty of Science and Engineering School of Aerospace, Civil, Electrical, General and Mechanical Engineering - General Engineering Ye Yuan 0000-0002-7568-0130 1 Renliang Chen 2 Pan Li 3
title Trim investigation for coaxial rigid rotor helicopters using an improved aerodynamic interference model
spellingShingle Trim investigation for coaxial rigid rotor helicopters using an improved aerodynamic interference model
Ye Yuan
title_short Trim investigation for coaxial rigid rotor helicopters using an improved aerodynamic interference model
title_full Trim investigation for coaxial rigid rotor helicopters using an improved aerodynamic interference model
title_fullStr Trim investigation for coaxial rigid rotor helicopters using an improved aerodynamic interference model
title_full_unstemmed Trim investigation for coaxial rigid rotor helicopters using an improved aerodynamic interference model
title_sort Trim investigation for coaxial rigid rotor helicopters using an improved aerodynamic interference model
author_id_str_mv cdadbd9e334ad914d7968a538d9522a4
author_id_fullname_str_mv cdadbd9e334ad914d7968a538d9522a4_***_Ye Yuan
author Ye Yuan
author2 Ye Yuan
Renliang Chen
Pan Li
format Journal article
container_title Aerospace Science and Technology
container_volume 85
container_start_page 293
publishDate 2019
institution Swansea University
issn 1270-9638
doi_str_mv 10.1016/j.ast.2018.11.044
publisher Elsevier BV
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 rigid rotor helicopter has been proposed as a future high-performance rotorcraft concept.However, the aerodynamic interference of this helicopter is complicated because it couples with theunique flapping feature of the rigid rotor, which further alters the trim characteristics of coaxial rigidrotor helicopters. Thus, a multi-point vortex ring element (MVRE) model is developed to simulate theaerodynamic interference between rotors. The method for establishing this MVRE model is illustrated, anda wind tunnel experimental dataset is used to assess its precision hover and forward flight states. Next, a flight dynamics model of the coaxial rigid rotor helicopter is built based on the MVRE aerodynamic interference model and the flapping feature of the rigid rotor. The influence of the rotor wake on the fuselage and the horizontal and vertical tails can also be calculated using this model. The trim characteristics of this helicopter are evaluated with flight test data for speeds ranging from 0 m/s to 80 m/s, and the results confirm that this model can reflect the trim characteristics with satisfactory precision. In addition, the calculation process demonstrates that the MVRE model provides a much faster computing rate. Considering the aerodynamic interference and rigid rotor characteristics, the trim results of the coaxial rigid rotor helicopter present unique features: aerodynamic interference in the coaxial rotor system not only increases the collective pitch and the collective differential but also adds a negative gradient under the forward speed in the longitudinal cyclic pitch in the low-speed forward flight range. Moreover, the rotor wake effect on the other parts of the helicopter is distinct from the corresponding effects on conventional helicopters in terms of the trim characteristics.
published_date 2019-02-01T04:14:41Z
_version_ 1763753991196377088
score 11.035655

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