Quantification of Rotorcraft Blade Dynamic Inertial Imbalance

Wesley Viall; Jason Mayeur; Babak Shotorban; Farbob Fahimi

doi:10.2514/6.2022-3593

Quantification of Rotorcraft Blade Dynamic Inertial Imbalance

Wesley Viall
, Jason Mayeur
, Babak Shotorban
, Farbob Fahimi

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › peer-review

2 Scopus citations

Abstract

The sensitivity of main rotor blade relative dynamic pitching moment and rotorcraft control system, hub, and damper loads to changes in blade tip weights is evaluated using Rotorcraft Comprehensive Analysis System as a comprehensive analysis solver. A fixed and rigid hub is evaluated in a collective input sweep of 0° to 00° for eight different combinations of chordwise tip mass adjustments, and separately, two different combinations of spanwise tip weight adjustments. Once the sensitivity is determined in the form of a relative pitching moment slope, two thrust coefficient cases for a speed sweep of μ = 0 to 0. 338 are studied. Results indicate that the inertial imbalances are quantifiable by a linear regression of the relative dynamic pitching moment. Hub, push rod, and damper loads show an increasing sensitivity to blade imbalances as the relative imbalance increases as well as thrust increases. In general, the load differences are greatest at lower speeds and decrease as speed increases.

Original language	English
Title of host publication	AIAA AVIATION 2022 Forum
Publisher	American Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)	9781624106354
DOIs	https://doi.org/10.2514/6.2022-3593
State	Published - 2022
Externally published	Yes
Event	AIAA AVIATION 2022 Forum - Chicago, United States Duration: Jun 27 2022 → Jul 1 2022

Publication series

Name	AIAA AVIATION 2022 Forum

Conference

Conference	AIAA AVIATION 2022 Forum
Country/Territory	United States
City	Chicago
Period	06/27/22 → 07/1/22

Funding

Dr. Dave O’Brien and Dr. Chris Brackbill of DEVCOM Aviation & Missile Center (AvMC) System Readiness Directorate (SRD) Aeromechanics Division provided significant resource, logistical, and technical support of this work. It would not have been accomplished without their help. Ms. Kit Fry of DEVCOM AvMC SRD Structures and Materials Division provided subject matter expertise in the area of rotor smoothing and the significance of it to the Army’s aircraft fleet.

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10.2514/6.2022-3593

Cite this

@inproceedings{8592b4e62b6346f3a986836cdfa5a972,

title = "Quantification of Rotorcraft Blade Dynamic Inertial Imbalance",

abstract = "The sensitivity of main rotor blade relative dynamic pitching moment and rotorcraft control system, hub, and damper loads to changes in blade tip weights is evaluated using Rotorcraft Comprehensive Analysis System as a comprehensive analysis solver. A fixed and rigid hub is evaluated in a collective input sweep of 0° to 00° for eight different combinations of chordwise tip mass adjustments, and separately, two different combinations of spanwise tip weight adjustments. Once the sensitivity is determined in the form of a relative pitching moment slope, two thrust coefficient cases for a speed sweep of μ = 0 to 0. 338 are studied. Results indicate that the inertial imbalances are quantifiable by a linear regression of the relative dynamic pitching moment. Hub, push rod, and damper loads show an increasing sensitivity to blade imbalances as the relative imbalance increases as well as thrust increases. In general, the load differences are greatest at lower speeds and decrease as speed increases.",

author = "Wesley Viall and Jason Mayeur and Babak Shotorban and Farbob Fahimi",

note = "Publisher Copyright: {\textcopyright} 2022, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.; AIAA AVIATION 2022 Forum ; Conference date: 27-06-2022 Through 01-07-2022",

year = "2022",

doi = "10.2514/6.2022-3593",

language = "English",

isbn = "9781624106354",

series = "AIAA AVIATION 2022 Forum",

publisher = "American Institute of Aeronautics and Astronautics Inc, AIAA",

booktitle = "AIAA AVIATION 2022 Forum",

}

TY - GEN

T1 - Quantification of Rotorcraft Blade Dynamic Inertial Imbalance

AU - Viall, Wesley

AU - Mayeur, Jason

AU - Shotorban, Babak

AU - Fahimi, Farbob

PY - 2022

Y1 - 2022

N2 - The sensitivity of main rotor blade relative dynamic pitching moment and rotorcraft control system, hub, and damper loads to changes in blade tip weights is evaluated using Rotorcraft Comprehensive Analysis System as a comprehensive analysis solver. A fixed and rigid hub is evaluated in a collective input sweep of 0° to 00° for eight different combinations of chordwise tip mass adjustments, and separately, two different combinations of spanwise tip weight adjustments. Once the sensitivity is determined in the form of a relative pitching moment slope, two thrust coefficient cases for a speed sweep of μ = 0 to 0. 338 are studied. Results indicate that the inertial imbalances are quantifiable by a linear regression of the relative dynamic pitching moment. Hub, push rod, and damper loads show an increasing sensitivity to blade imbalances as the relative imbalance increases as well as thrust increases. In general, the load differences are greatest at lower speeds and decrease as speed increases.

AB - The sensitivity of main rotor blade relative dynamic pitching moment and rotorcraft control system, hub, and damper loads to changes in blade tip weights is evaluated using Rotorcraft Comprehensive Analysis System as a comprehensive analysis solver. A fixed and rigid hub is evaluated in a collective input sweep of 0° to 00° for eight different combinations of chordwise tip mass adjustments, and separately, two different combinations of spanwise tip weight adjustments. Once the sensitivity is determined in the form of a relative pitching moment slope, two thrust coefficient cases for a speed sweep of μ = 0 to 0. 338 are studied. Results indicate that the inertial imbalances are quantifiable by a linear regression of the relative dynamic pitching moment. Hub, push rod, and damper loads show an increasing sensitivity to blade imbalances as the relative imbalance increases as well as thrust increases. In general, the load differences are greatest at lower speeds and decrease as speed increases.

UR - https://www.scopus.com/pages/publications/85135072536

U2 - 10.2514/6.2022-3593

DO - 10.2514/6.2022-3593

M3 - Conference contribution

AN - SCOPUS:85135072536

SN - 9781624106354

T3 - AIAA AVIATION 2022 Forum

BT - AIAA AVIATION 2022 Forum

PB - American Institute of Aeronautics and Astronautics Inc, AIAA

T2 - AIAA AVIATION 2022 Forum

Y2 - 27 June 2022 through 1 July 2022

ER -

Quantification of Rotorcraft Blade Dynamic Inertial Imbalance

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