scholarly journals Acoustic emission control of welding seams of the bench longevity testing unit of the heavy plane landing gear

2021 ◽  
Author(s):  
A. N. Ser’eznov ◽  
L. N. Stepanova ◽  
S. I. Kabanov ◽  
I. S. Ramazanov ◽  
V. V. Chernova
Keyword(s):  
Acoustic Emission ◽  
Emission Control ◽  
Landing Gear ◽  
Testing Unit

scholarly journals A Principal Component Analysis of Acoustic Emission Signals from a Landing Gear Component

2008 ◽  
Vol 13-14 ◽  
pp. 41-47 ◽  
Author(s):  
Rhys Pullin ◽  
Mark J. Eaton ◽  
James J. Hensman ◽  
Karen M. Holford ◽  
Keith Worden ◽  
...  
Keyword(s):  
Principal Component Analysis ◽  
Acoustic Emission ◽  
Background Noise ◽  
Principal Component ◽  
Component Analysis ◽  
Landing Gear ◽  
Fracture Detection ◽  
Artificial Fracture ◽  
High Level ◽  
Ae Signals

This work forms part of a larger investigation into fracture detection using acoustic emission (AE) during landing gear airworthiness testing. It focuses on the use of principal component analysis (PCA) to differentiate between fracture signals and high levels of background noise. An artificial acoustic emission (AE) fracture source was developed and additionally five sources were used to generate differing AE signals. Signals were recorded from all six artificial sources in a real landing gear component subject to no load. Further to this, artificial fracture signals were recorded in the same component under airworthiness test load conditions. Principal component analysis (PCA) was used to automatically differentiate between AE signals from different source types. Furthermore, successful separation of artificial fracture signals from a very high level of background noise was achieved. The presence of a load was observed to affect the ultrasonic propagation of AE signals.

scholarly journals A Principal Component Analysis of Acoustic Emission Signals from a Landing Gear Component

2007 ◽  
Vol 347 ◽  
pp. 139-144 ◽  
Author(s):  
Rhys Pullin ◽  
James J. Hensman ◽  
Karen M. Holford ◽  
Keith Worden ◽  
S.L. Evans
Keyword(s):  
Principal Component Analysis ◽  
Acoustic Emission ◽  
Principal Component ◽  
Fatigue Loading ◽  
Component Analysis ◽  
High Amplitude ◽  
Paint Layer ◽  
Landing Gear ◽  
Post Test ◽  
Group A

Acoustic emission monitoring was completed on a painted aerospace grade steel landing gear component undergoing fatigue loading until rupture. A post-test linear location analysis of the collected signals revealed eleven groups where high activity (greater than 2000 hits) occurred within a defined location, three of which corresponded in location to the position of fracture and final rupture of the specimen. Feature data, such as amplitude, rise-time, energy etc. were used to describe the identified signals in each group. A dimension reduction through principal component analysis of the feature data of all groups was performed. Results showed that high amplitude signals associated with four groups of signals arising from noise could be separated from the fracture groups. However four groups not associated with noise or the known positions of the fracture groups were not separable from the signals attributed to fractures. The paint layer of the specimen was removed and a magnetic particle investigation was completed that showed these four groups coincided with regions of additional fracture in the component.

Acoustic Emission Testing of a Landing Gear Component

2006 ◽  
Vol 13-14 ◽  
pp. 29-34
Author(s):  
Rhys Pullin ◽  
Karen M. Holford ◽  
S.L. Evans ◽  
M.G. Baxter
Keyword(s):  
Acoustic Emission ◽  
Fatigue Testing ◽  
Fe Analysis ◽  
Landing Gear ◽  
Emission Testing ◽  
Acoustic Emission Testing ◽  
Fretting Damage ◽  
Planar Location

Acoustic emission (AE) monitoring was performed on an aluminium landing gear component that was undergoing testing to investigate its fracture resilience. The type of component was identified from FE analysis and previous fatigue testing. The component was loaded in fatigue for 500 flight cycles before re-greasing of the bearings. After 2,000 cycles the component was removed for NDT inspection. The AE investigations were implemented after 83,000 flight cycles had been completed. NDT at this point had shown that the component contained no damage. This paper presents the findings of the final 2,000 cycles monitored. The AE investigation detected and located, using both linear and planar location approaches, one region of activity around the grease pin. Fretting damage at this location was confirmed using dye pentrant testing. It was also shown that the increase in rate of detected activity is a significant tool in the identification of damage in landing gear components.

Acoustic emission control avoids fluence shifts caused by target runaway during laser synthesis of colloids

2019 ◽  
Vol 479 ◽  
pp. 887-895 ◽  
Author(s):  
Marc Labusch ◽  
Adauto P.A. Cunha ◽  
Sebastian F. Wirtz ◽  
Sven Reichenberger ◽  
Ernst Cleve ◽  
...  
Keyword(s):  
Acoustic Emission ◽  
Emission Control ◽  
Laser Synthesis

Acoustic Emission Testing of a Landing Gear Component

2006 ◽  
pp. 29-34
Author(s):  
Rhys Pullin ◽  
Karen M. Holford ◽  
Sam L. Evans ◽  
M.G. Baxter
Keyword(s):  
Acoustic Emission ◽  
Landing Gear ◽  
Emission Testing ◽  
Acoustic Emission Testing

ACOUSTIC EMISSION CONTROL OF THE PROCESS OF DESTRUCTION OF CARBON FIBER SAMPLES AND THE WING BOX UNDER SHOCK LOADS

2020 ◽  
pp. 4-11
Author(s):  
L. N. Stepanova ◽  
V. V Chernova ◽  
M. A. Miloserdova
Keyword(s):  
Acoustic Emission ◽  
Carbon Fiber ◽  
Impact Damage ◽  
Emission Control ◽  
Shock Load ◽  
Shock Loads ◽  
The Impact ◽  
Ae Signals ◽  
Composite Wing ◽  
Wing Box

Investigations of three groups of samples from carbon fiber T 700 and the composite wing box of the aircraft were carried out. Samples with monolayers laying 0; 90; –45 were subjected to shock loads, which were applied at their center with a load in the form of a blunt tip weighing 0.53 kg. Loads were dumped from a height of 0,3; 0,5; 1 m per sample. Impact damage with an energy of 15 J was also applied to the upper surface of the carbon fiber wing box. Acoustic emission (AE) signals were recorded from the piezoelectric antenna sensors mounted on the wing samples and box both during the impact of the weight with the object under study and during rebounds. The locations where the shock load were applied were located and the parameters of the AE signals were analyzed. The influence of the type of monolayer laying on the process of cracking in the material of the samples arising at different energy of shock loads was determined.

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