Capacitive transducer for condition based maintenance after harsh landing events

Oliver Tivadar Sagi, David Maynard, Eniko T Enikov

Research output: Chapter in Book/Report/Conference proceedingConference contribution

3 Citations (Scopus)

Abstract

The objective of this work is to identify design parameters for a capacitive sensor designed to recognize and record helicopter harsh landing events. Harsh landing events are typically associated with landing speeds exceeding 2.5 m/s [1] and require mandatory structural inspection resulting in down-times that could last a week or longer. In cases where no visible damage occurs, harsh-landing events might be difficult to identify and record. This paper presents a finite element analysis of the acceleration profile at different locations of the skid of a Bell 206 L4 helicopter which is then used to design and test a low-cost capacitive sensor for monitoring harsh landing events. Time history and histograms of the acceleration signal during normal and harsh landings are presented. The capacitive accelerometer is designed to operate in the 10g to 360g range. The sensor is integrated directly on a wiring board and is readout by a micro-controller with a capacitive ASIC. Details of the sensor design, fabrication, and testing are presented. The presented material also provides hard-to-find design data on the structural accelerations which can occur during harsh landing.

Original languageEnglish (US)
Title of host publicationAUTOTESTCON (Proceedings)
Pages286-291
Number of pages6
DOIs
StatePublished - 2011
EventSystems Readiness Technology Conference: "Transforming Maintenance through Advanced Test, Diagnosis and Prognosis", IEEE AUTOTESTCON 2011 - Baltimore, MD, United States
Duration: Sep 12 2011Sep 15 2011

Other

OtherSystems Readiness Technology Conference: "Transforming Maintenance through Advanced Test, Diagnosis and Prognosis", IEEE AUTOTESTCON 2011
CountryUnited States
CityBaltimore, MD
Period9/12/119/15/11

Fingerprint

Landing
Transducers
Capacitive sensors
Helicopters
Sensors
Electric wiring
Application specific integrated circuits
Accelerometers
Printed circuit boards
Inspection
Finite element method
Fabrication
Controllers
Monitoring
Testing
Costs

Keywords

  • accelerometer
  • condition based maintenance
  • drop test
  • hard landing
  • harsh landing

ASJC Scopus subject areas

  • Electrical and Electronic Engineering
  • Computer Science Applications

Cite this

Capacitive transducer for condition based maintenance after harsh landing events. / Sagi, Oliver Tivadar; Maynard, David; Enikov, Eniko T.

AUTOTESTCON (Proceedings). 2011. p. 286-291 6058792.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Sagi, OT, Maynard, D & Enikov, ET 2011, Capacitive transducer for condition based maintenance after harsh landing events. in AUTOTESTCON (Proceedings)., 6058792, pp. 286-291, Systems Readiness Technology Conference: "Transforming Maintenance through Advanced Test, Diagnosis and Prognosis", IEEE AUTOTESTCON 2011, Baltimore, MD, United States, 9/12/11. https://doi.org/10.1109/AUTEST.2011.6058792
Sagi, Oliver Tivadar ; Maynard, David ; Enikov, Eniko T. / Capacitive transducer for condition based maintenance after harsh landing events. AUTOTESTCON (Proceedings). 2011. pp. 286-291
@inproceedings{4ac3554287994f13aa2f1f92a8672853,
title = "Capacitive transducer for condition based maintenance after harsh landing events",
abstract = "The objective of this work is to identify design parameters for a capacitive sensor designed to recognize and record helicopter harsh landing events. Harsh landing events are typically associated with landing speeds exceeding 2.5 m/s [1] and require mandatory structural inspection resulting in down-times that could last a week or longer. In cases where no visible damage occurs, harsh-landing events might be difficult to identify and record. This paper presents a finite element analysis of the acceleration profile at different locations of the skid of a Bell 206 L4 helicopter which is then used to design and test a low-cost capacitive sensor for monitoring harsh landing events. Time history and histograms of the acceleration signal during normal and harsh landings are presented. The capacitive accelerometer is designed to operate in the 10g to 360g range. The sensor is integrated directly on a wiring board and is readout by a micro-controller with a capacitive ASIC. Details of the sensor design, fabrication, and testing are presented. The presented material also provides hard-to-find design data on the structural accelerations which can occur during harsh landing.",
keywords = "accelerometer, condition based maintenance, drop test, hard landing, harsh landing",
author = "Sagi, {Oliver Tivadar} and David Maynard and Enikov, {Eniko T}",
year = "2011",
doi = "10.1109/AUTEST.2011.6058792",
language = "English (US)",
isbn = "9781424493616",
pages = "286--291",
booktitle = "AUTOTESTCON (Proceedings)",

}

TY - GEN

T1 - Capacitive transducer for condition based maintenance after harsh landing events

AU - Sagi, Oliver Tivadar

AU - Maynard, David

AU - Enikov, Eniko T

PY - 2011

Y1 - 2011

N2 - The objective of this work is to identify design parameters for a capacitive sensor designed to recognize and record helicopter harsh landing events. Harsh landing events are typically associated with landing speeds exceeding 2.5 m/s [1] and require mandatory structural inspection resulting in down-times that could last a week or longer. In cases where no visible damage occurs, harsh-landing events might be difficult to identify and record. This paper presents a finite element analysis of the acceleration profile at different locations of the skid of a Bell 206 L4 helicopter which is then used to design and test a low-cost capacitive sensor for monitoring harsh landing events. Time history and histograms of the acceleration signal during normal and harsh landings are presented. The capacitive accelerometer is designed to operate in the 10g to 360g range. The sensor is integrated directly on a wiring board and is readout by a micro-controller with a capacitive ASIC. Details of the sensor design, fabrication, and testing are presented. The presented material also provides hard-to-find design data on the structural accelerations which can occur during harsh landing.

AB - The objective of this work is to identify design parameters for a capacitive sensor designed to recognize and record helicopter harsh landing events. Harsh landing events are typically associated with landing speeds exceeding 2.5 m/s [1] and require mandatory structural inspection resulting in down-times that could last a week or longer. In cases where no visible damage occurs, harsh-landing events might be difficult to identify and record. This paper presents a finite element analysis of the acceleration profile at different locations of the skid of a Bell 206 L4 helicopter which is then used to design and test a low-cost capacitive sensor for monitoring harsh landing events. Time history and histograms of the acceleration signal during normal and harsh landings are presented. The capacitive accelerometer is designed to operate in the 10g to 360g range. The sensor is integrated directly on a wiring board and is readout by a micro-controller with a capacitive ASIC. Details of the sensor design, fabrication, and testing are presented. The presented material also provides hard-to-find design data on the structural accelerations which can occur during harsh landing.

KW - accelerometer

KW - condition based maintenance

KW - drop test

KW - hard landing

KW - harsh landing

UR - http://www.scopus.com/inward/record.url?scp=81055134823&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=81055134823&partnerID=8YFLogxK

U2 - 10.1109/AUTEST.2011.6058792

DO - 10.1109/AUTEST.2011.6058792

M3 - Conference contribution

AN - SCOPUS:81055134823

SN - 9781424493616

SP - 286

EP - 291

BT - AUTOTESTCON (Proceedings)

ER -