Life extension of F/A/18 nacelle using add-on dampers

Wing Kong Chiu; U Siovitz; Steve C Galea; Leonard L Koss

doi:10.1117/12.310674

Life extension of F/A/18 nacelle using add-on dampers

Wing Kong Chiu, U Siovitz, Steve C Galea, Leonard L Koss

Mechanical & Aerospace Engineering

Research output: Contribution to conference › Other

Abstract

Acoustic fatigue is due to very high intensity excitation as a result of pressure waves caused by either engine/or aerodynamic effects. Currently a large portion of the F/A-18 fleet has suffered from acoustic fatigue (high cycle, low strain) cracking in skin panel on the lower external surface of the inlet nacelle. There has been a long history of cracking in this region, which is attributed to fatigue caused by acoustic excitation of the panel during the operation of the aircraft Efforts to alleviate these fatigue crack growth with traditional boron/epoxy patches was not successful. This paper seek to select a set of damping material suitable for the reinforcement/damping treatment to alleviate the acoustic fatigue damage of the nacelle panel of the F/A-18 aircraft. This experimental study will address the relevance of constrained layer damping reducing the incidence of acoustic fatigue problems in the nacelle region.

Original language	English
Pages	71-80
Number of pages	10
DOIs	https://doi.org/10.1117/12.310674
Publication status	Published - Dec 1998
Event	Smart Structures and Materials 1998 Industrial and Commercial Applications of Smart Structures Technologies - San Diego, CA, United States of America Duration: 3 Mar 1998 → 5 Mar 1998

Conference

Conference	Smart Structures and Materials 1998 Industrial and Commercial Applications of Smart Structures Technologies
Country/Territory	United States of America
City	San Diego, CA
Period	3/03/98 → 5/03/98

Access to Document

10.1117/12.310674

Cite this

@conference{cc7cce2cf1f3401e9f6e76f4d8a8753e,

title = "Life extension of F/A/18 nacelle using add-on dampers",

abstract = "Acoustic fatigue is due to very high intensity excitation as a result of pressure waves caused by either engine/or aerodynamic effects. Currently a large portion of the F/A-18 fleet has suffered from acoustic fatigue (high cycle, low strain) cracking in skin panel on the lower external surface of the inlet nacelle. There has been a long history of cracking in this region, which is attributed to fatigue caused by acoustic excitation of the panel during the operation of the aircraft Efforts to alleviate these fatigue crack growth with traditional boron/epoxy patches was not successful. This paper seek to select a set of damping material suitable for the reinforcement/damping treatment to alleviate the acoustic fatigue damage of the nacelle panel of the F/A-18 aircraft. This experimental study will address the relevance of constrained layer damping reducing the incidence of acoustic fatigue problems in the nacelle region.",

author = "Chiu, {Wing Kong} and U Siovitz and Galea, {Steve C} and Koss, {Leonard L}",

year = "1998",

month = dec,

doi = "10.1117/12.310674",

language = "English",

pages = "71--80",

note = "Smart Structures and Materials 1998 Industrial and Commercial Applications of Smart Structures Technologies ; Conference date: 03-03-1998 Through 05-03-1998",

}

TY - CONF

T1 - Life extension of F/A/18 nacelle using add-on dampers

AU - Chiu, Wing Kong

AU - Siovitz, U

AU - Galea, Steve C

AU - Koss, Leonard L

PY - 1998/12

Y1 - 1998/12

N2 - Acoustic fatigue is due to very high intensity excitation as a result of pressure waves caused by either engine/or aerodynamic effects. Currently a large portion of the F/A-18 fleet has suffered from acoustic fatigue (high cycle, low strain) cracking in skin panel on the lower external surface of the inlet nacelle. There has been a long history of cracking in this region, which is attributed to fatigue caused by acoustic excitation of the panel during the operation of the aircraft Efforts to alleviate these fatigue crack growth with traditional boron/epoxy patches was not successful. This paper seek to select a set of damping material suitable for the reinforcement/damping treatment to alleviate the acoustic fatigue damage of the nacelle panel of the F/A-18 aircraft. This experimental study will address the relevance of constrained layer damping reducing the incidence of acoustic fatigue problems in the nacelle region.

AB - Acoustic fatigue is due to very high intensity excitation as a result of pressure waves caused by either engine/or aerodynamic effects. Currently a large portion of the F/A-18 fleet has suffered from acoustic fatigue (high cycle, low strain) cracking in skin panel on the lower external surface of the inlet nacelle. There has been a long history of cracking in this region, which is attributed to fatigue caused by acoustic excitation of the panel during the operation of the aircraft Efforts to alleviate these fatigue crack growth with traditional boron/epoxy patches was not successful. This paper seek to select a set of damping material suitable for the reinforcement/damping treatment to alleviate the acoustic fatigue damage of the nacelle panel of the F/A-18 aircraft. This experimental study will address the relevance of constrained layer damping reducing the incidence of acoustic fatigue problems in the nacelle region.

UR - http://www.scopus.com/inward/record.url?scp=0032401354&partnerID=8YFLogxK

U2 - 10.1117/12.310674

DO - 10.1117/12.310674

M3 - Other

SP - 71

EP - 80

T2 - Smart Structures and Materials 1998 Industrial and Commercial Applications of Smart Structures Technologies

Y2 - 3 March 1998 through 5 March 1998

ER -

Life extension of F/A/18 nacelle using add-on dampers

Abstract

Conference

Access to Document

Other files and links

Cite this