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WADC-TR-53-106

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  • 169 Downloads
  • 5.75 MB File Size
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  • March 7, 2017 Create Date
  • March 7, 2017 Last Updated
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Wright Air Development Center - Tensile and Tensile Fatigue Properties of Transparent Enclosure Attachments for Aircraft

Fifteen types of edge attachments, eight for monolithic acrylic 
material and seven for laminated acrylic material were desigled, fab— 
ricated and tested for tensile strength at temperature and -650F, 
and in tensile—fatigue at room temperature. Thirteen of these types 
were desi.5ied using acrylic material and two were desißled 
using acrylic material. 
Though ultimate t,ensile strengths vary widely depending on 
and materials used in the attaching edge, it appears that the tensile— 
fatigue limit in all cases where good engineering desigi practices are 
maintained approaches one pound per nül thickness per inch of width 
of transparent acrylic material at. 500,000 cycles. Although 
acrylic material appears to have a slightly greater endurance 
limit, insufficient data are available to definitely draw such a con— 
clusion.
Late In World War Il it beca.me apparent that transparent enclosures for air— 
craft could no longer be attached by the sinle means previously used in unpress— 
urized craft. This realization induced a general reaction toward edge reinforce— 
ment in the technical sections of all concerns involved. Solutions to the prob— 
lem were in many cases Independently evolved and consequently types Of att— 
aching edges appeared. 
The basic purposes for this attaching edge were threefold: 
1. TO Increage bearing strength. 
2. To prevent the inception of fracture in the body 
of the transparent material. 
3. To prevent propogation of fracture from the attach— 
ing edge into the body of the transparent material. 
The direction of attack to achieve these has been universally giml— 
lar in that some attaching edge has been cemented to the transparent enclosure. 
The materials used for this punose have varied widely and include cast acrylic 
reinforcing strips, rubber extrusions. stainlegg vire screen — acrylic laminates, 
square woven Fiberglas cloth—acrylic laminates, and free mon loops. More recent 
{novatlons have Included nev veaveg of glass cloth as gatin weaves and unidirect— 
ional weaves built into acrylic laminates and synthetic fiber acrylic lam— 
inates, most no Orlon and Dacron.

 

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WADC-TR-53-106

  • Version
  • 169 Downloads
  • 5.75 MB File Size
  • 1 File Count
  • March 7, 2017 Create Date
  • March 7, 2017 Last Updated
Scroll for Details

Wright Air Development Center - Tensile and Tensile Fatigue Properties of Transparent Enclosure Attachments for Aircraft

Fifteen types of edge attachments, eight for monolithic acrylic 
material and seven for laminated acrylic material were desigled, fab— 
ricated and tested for tensile strength at temperature and -650F, 
and in tensile—fatigue at room temperature. Thirteen of these types 
were desi.5ied using acrylic material and two were desißled 
using acrylic material. 
Though ultimate t,ensile strengths vary widely depending on 
and materials used in the attaching edge, it appears that the tensile— 
fatigue limit in all cases where good engineering desigi practices are 
maintained approaches one pound per nül thickness per inch of width 
of transparent acrylic material at. 500,000 cycles. Although 
acrylic material appears to have a slightly greater endurance 
limit, insufficient data are available to definitely draw such a con— 
clusion.
Late In World War Il it beca.me apparent that transparent enclosures for air— 
craft could no longer be attached by the sinle means previously used in unpress— 
urized craft. This realization induced a general reaction toward edge reinforce— 
ment in the technical sections of all concerns involved. Solutions to the prob— 
lem were in many cases Independently evolved and consequently types Of att— 
aching edges appeared. 
The basic purposes for this attaching edge were threefold: 
1. TO Increage bearing strength. 
2. To prevent the inception of fracture in the body 
of the transparent material. 
3. To prevent propogation of fracture from the attach— 
ing edge into the body of the transparent material. 
The direction of attack to achieve these has been universally giml— 
lar in that some attaching edge has been cemented to the transparent enclosure. 
The materials used for this punose have varied widely and include cast acrylic 
reinforcing strips, rubber extrusions. stainlegg vire screen — acrylic laminates, 
square woven Fiberglas cloth—acrylic laminates, and free mon loops. More recent 
{novatlons have Included nev veaveg of glass cloth as gatin weaves and unidirect— 
ional weaves built into acrylic laminates and synthetic fiber acrylic lam— 
inates, most no Orlon and Dacron.

 

FileAction
WADC-TR-53-106 Tensile and Tensile Fatigue Properties of Transparent Enclosure Attachments for Aircraft.pdfDownload 
17,005 Documents in our Technical Library
2466639 Total Downloads

Search The Technical Library

Newest Additions

NASA-RP-1060 Subsonic Aircraft: Evolution and the Matching of Size to Performance
NASA-RP-1060 Subsonic Aircraft: Evolution and the Matching of Size to Performance
AA-CP-20212-001
AA-CP-20212-001
ADPO10769 Occurrence of Corrosion in Airframes
The purpose of this lecture is to provide an overview ...
MIL-STD-1759 Rivets and Rivet Type Fasteners Preferred for Design
The purpose of this book form standard is to provide ...
MIL-STD-810G Environmental Engineering Considerations and Laboratory Tests
This standard contains materiel acquisition program planning and engineering direction ...