No Cover Image

Conference Paper/Proceeding/Abstract 686 views

Longitudinal Control Strategy Investigation for Coaxial Compound Helicopters

Ye Yuan Orcid Logo, Douglas Thomson, Renliang Chen

75th Annual Vertical Flight Society Forum and Technology Display (FORUM 75): The Future of Vertical Flight, Volume: 75

Swansea University Author: Ye Yuan Orcid Logo

Full text not available from this repository: check for access using links below.

Check full text

Abstract

The coaxial compound helicopters have obtained a lot of research interest due to their outstanding performance, especially in high speed flight. This rotorcraft could use the longitudinal cyclic pitch and the elevator to control the pitching moment during the flight. In order to investigate the effe...

Full description

Published in: 75th Annual Vertical Flight Society Forum and Technology Display (FORUM 75): The Future of Vertical Flight
ISBN: 9781510887916
ISSN: 2167-1281
Published: Vertical Flight Society (VFS) 2019
Online Access: Check full text

URI: https://cronfa.swan.ac.uk/Record/cronfa58551
Tags: Add Tag
No Tags, Be the first to tag this record!
first_indexed 2021-11-04T15:38:17Z
last_indexed 2021-12-02T04:16:16Z
id cronfa58551
recordtype SURis
fullrecord <?xml version="1.0"?><rfc1807><datestamp>2021-12-01T13:47:35.9342956</datestamp><bib-version>v2</bib-version><id>58551</id><entry>2021-11-04</entry><title>Longitudinal Control Strategy Investigation for Coaxial Compound Helicopters</title><swanseaauthors><author><sid>cdadbd9e334ad914d7968a538d9522a4</sid><ORCID>0000-0002-7568-0130</ORCID><firstname>Ye</firstname><surname>Yuan</surname><name>Ye Yuan</name><active>true</active><ethesisStudent>false</ethesisStudent></author></swanseaauthors><date>2021-11-04</date><deptcode>GENG</deptcode><abstract>The coaxial compound helicopters have obtained a lot of research interest due to their outstanding performance, especially in high speed flight. This rotorcraft could use the longitudinal cyclic pitch and the elevator to control the pitching moment during the flight. In order to investigate the effect of different longitudinal control strategy on the flight dynamics characteristics of this helicopter, a validated flight dynamics model is utilized to calculate the control derivatives, the bandwidth and phase delay, the attitude quickness, and the control inputs and pilot workload during the Pull-up &amp; Push-over manoeuvre. The results indicate that control power of the longitudinal cyclic pitch is higher than that of the elevator, especially in hover and low speed forward flight due to the lack of the dynamic pressure on the elevator. The bandwidth and phase delay results demonstrate that both longitudinal control strategy could attain satisfactory small-amplitude response characteristics, and the attitude quickness results show that the helicopter capability in moderate to large control response is relatively high due to the additional damping provided by the rigid rotor. The manoeuvre simulation results indicate that using reasonable allocation between the longitudinal cyclic pitch and elevator is an efficient method to reduce the pilot workload and the maximum power consumption during manoeuvring flight.</abstract><type>Conference Paper/Proceeding/Abstract</type><journal>75th Annual Vertical Flight Society Forum and Technology Display (FORUM 75): The Future of Vertical Flight</journal><volume>75</volume><journalNumber/><paginationStart/><paginationEnd/><publisher>Vertical Flight Society (VFS)</publisher><placeOfPublication/><isbnPrint>9781510887916</isbnPrint><isbnElectronic/><issnPrint/><issnElectronic>2167-1281</issnElectronic><keywords/><publishedDay>13</publishedDay><publishedMonth>5</publishedMonth><publishedYear>2019</publishedYear><publishedDate>2019-05-13</publishedDate><doi/><url>https://vtol.org/store/department/forum-proceedings-and-special-sessions-809.cfm</url><notes/><college>COLLEGE NANME</college><department>General Engineering</department><CollegeCode>COLLEGE CODE</CollegeCode><DepartmentCode>GENG</DepartmentCode><institution>Swansea University</institution><apcterm>Not Required</apcterm><lastEdited>2021-12-01T13:47:35.9342956</lastEdited><Created>2021-11-04T15:37:23.1360767</Created><path><level id="1">Faculty of Science and Engineering</level><level id="2">School of Aerospace, Civil, Electrical, General and Mechanical Engineering - General Engineering</level></path><authors><author><firstname>Ye</firstname><surname>Yuan</surname><orcid>0000-0002-7568-0130</orcid><order>1</order></author><author><firstname>Douglas</firstname><surname>Thomson</surname><order>2</order></author><author><firstname>Renliang</firstname><surname>Chen</surname><order>3</order></author></authors><documents/><OutputDurs/></rfc1807>
spelling 2021-12-01T13:47:35.9342956 v2 58551 2021-11-04 Longitudinal Control Strategy Investigation for Coaxial Compound Helicopters cdadbd9e334ad914d7968a538d9522a4 0000-0002-7568-0130 Ye Yuan Ye Yuan true false 2021-11-04 GENG The coaxial compound helicopters have obtained a lot of research interest due to their outstanding performance, especially in high speed flight. This rotorcraft could use the longitudinal cyclic pitch and the elevator to control the pitching moment during the flight. In order to investigate the effect of different longitudinal control strategy on the flight dynamics characteristics of this helicopter, a validated flight dynamics model is utilized to calculate the control derivatives, the bandwidth and phase delay, the attitude quickness, and the control inputs and pilot workload during the Pull-up & Push-over manoeuvre. The results indicate that control power of the longitudinal cyclic pitch is higher than that of the elevator, especially in hover and low speed forward flight due to the lack of the dynamic pressure on the elevator. The bandwidth and phase delay results demonstrate that both longitudinal control strategy could attain satisfactory small-amplitude response characteristics, and the attitude quickness results show that the helicopter capability in moderate to large control response is relatively high due to the additional damping provided by the rigid rotor. The manoeuvre simulation results indicate that using reasonable allocation between the longitudinal cyclic pitch and elevator is an efficient method to reduce the pilot workload and the maximum power consumption during manoeuvring flight. Conference Paper/Proceeding/Abstract 75th Annual Vertical Flight Society Forum and Technology Display (FORUM 75): The Future of Vertical Flight 75 Vertical Flight Society (VFS) 9781510887916 2167-1281 13 5 2019 2019-05-13 https://vtol.org/store/department/forum-proceedings-and-special-sessions-809.cfm COLLEGE NANME General Engineering COLLEGE CODE GENG Swansea University Not Required 2021-12-01T13:47:35.9342956 2021-11-04T15:37:23.1360767 Faculty of Science and Engineering School of Aerospace, Civil, Electrical, General and Mechanical Engineering - General Engineering Ye Yuan 0000-0002-7568-0130 1 Douglas Thomson 2 Renliang Chen 3
title Longitudinal Control Strategy Investigation for Coaxial Compound Helicopters
spellingShingle Longitudinal Control Strategy Investigation for Coaxial Compound Helicopters
Ye Yuan
title_short Longitudinal Control Strategy Investigation for Coaxial Compound Helicopters
title_full Longitudinal Control Strategy Investigation for Coaxial Compound Helicopters
title_fullStr Longitudinal Control Strategy Investigation for Coaxial Compound Helicopters
title_full_unstemmed Longitudinal Control Strategy Investigation for Coaxial Compound Helicopters
title_sort Longitudinal Control Strategy Investigation 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 Conference Paper/Proceeding/Abstract
container_title 75th Annual Vertical Flight Society Forum and Technology Display (FORUM 75): The Future of Vertical Flight
container_volume 75
publishDate 2019
institution Swansea University
isbn 9781510887916
issn 2167-1281
publisher Vertical Flight Society (VFS)
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
url https://vtol.org/store/department/forum-proceedings-and-special-sessions-809.cfm
document_store_str 0
active_str 0
description The coaxial compound helicopters have obtained a lot of research interest due to their outstanding performance, especially in high speed flight. This rotorcraft could use the longitudinal cyclic pitch and the elevator to control the pitching moment during the flight. In order to investigate the effect of different longitudinal control strategy on the flight dynamics characteristics of this helicopter, a validated flight dynamics model is utilized to calculate the control derivatives, the bandwidth and phase delay, the attitude quickness, and the control inputs and pilot workload during the Pull-up & Push-over manoeuvre. The results indicate that control power of the longitudinal cyclic pitch is higher than that of the elevator, especially in hover and low speed forward flight due to the lack of the dynamic pressure on the elevator. The bandwidth and phase delay results demonstrate that both longitudinal control strategy could attain satisfactory small-amplitude response characteristics, and the attitude quickness results show that the helicopter capability in moderate to large control response is relatively high due to the additional damping provided by the rigid rotor. The manoeuvre simulation results indicate that using reasonable allocation between the longitudinal cyclic pitch and elevator is an efficient method to reduce the pilot workload and the maximum power consumption during manoeuvring flight.
published_date 2019-05-13T04:15:10Z
_version_ 1763754020990615552
score 11.024221

Similar Items