Damage protection device for aircraft structure
An apparatus to protect exposed structures on an aircraft which includes a core; a securing mechanism coupled to the core; and an outer coating applied to the core to encapsulate the core and facilitate the attachment of the securing mechanism. A thermal protection layer may be applied to the apparatus for high temperature applications.
1. An apparatus configured to protect exposed structures on an aircraft comprising:
a core having a J-shaped cross-section including a straight length and a crook, the crook being configured to wrap around an edge of the aircraft to protect the edge from maintenance-induced damage;
an outer coating encapsulating the core;
a flap secured to a portion of the outer coating covering the straight length, on a side of the straight length opposite the crook, the flap extending from the apparatus away from the crook; and
a securing mechanism coupled to the flap at a location spaced from the core, the securing mechanism being configured to releasably secure the apparatus to the aircraft.
2. The apparatus of claim 1 , wherein the core comprises an impact absorbing elastomeric foam body.
3. The apparatus of claim 2 , wherein the impact absorbing elastomeric foam body comprises a thermoformed ethelyne vinyl acetate (EVA).
4. The apparatus of claim 1 , wherein the core comprises a thickness of between about 0.25″ and about 2.″
5. The apparatus of claim 1 , wherein the securing mechanism comprises a suction cup.
6. The apparatus of claim 1 , wherein the securing mechanism comprises a magnetic material.
7. The apparatus of claim 1 , wherein the outer coating comprises an impact resistant flexible material.
8. The apparatus of claim 1 , wherein the outer coating comprises urethane.
9. The apparatus of claim 1 , wherein the outer coating comprises a thickness of between about 0.01″ and about 0.2 ″.
10. The apparatus of claim 1 , further comprising a thermal protective layer applied over the outer coating.
11. An apparatus configured to protect exposed structures on an aircraft comprising:
an impact absorbing elastomeric foam body having a J-shaped cross-section including a straight length and a crook, the crook being configured to wrap around an edge of the aircraft to protect the edge from maintenance-induced damage;
an outer coating encapsulating the impact absorbing elastomeric foam body;
a tab extending from the straight length away from the crook; and
a suction cup coupled to the flap at a location spaced from the core, the suction cup being configured to releasably secure the apparatus to the aircraft.
12. The apparatus of claim 11 , wherein the impact absorbing elastomeric foam body comprises a thermoformed ethelyne vinyl acetate (EVA).
13. The apparatus of claim 11 , wherein the impact absorbing elastomeric foam body comprises a thickness of between about 0.25″ and about 2.″
14. The apparatus of claim 11 , wherein the outer coating comprises urethane.
15. The apparatus of claim 11 , wherein the outer coating comprises a thickness of between about 0.01″ and about 0.2.″
16. The apparatus of claim 11 , further comprising a thermal protective layer applied over the outer coating.
17. The apparatus of claim 11 , wherein the impact absorbing elastomeric foam body comprises a thickness of between about 0.25″ and about 2″ and the outer coating comprises a thickness of between about 0.01″ and about 0.2.″