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1. A closing member for an opening that is formed in a panel constituting an outer surface of an airframe of an aircraft and being made of a composite material including a carbon fiber, the closing member comprising:
a closing member body configured to be disposed on one surface side of the panel to close the opening such that at least a side thereof faces and is exposed to an exterior of the airframe, the closing member body being made of one of titanium alloy, a stainless alloy, and a composite material including a carbon fiber, the closing member body having an external diameter larger than that of the opening; a ring-shaped clamp member configured to be disposed on the other surface side of the panel such that at least a surface side of the clamp member faces an exterior of the airframe, the clamp member being made of the composite material including the carbon fiber, the clamp member having an external diameter larger than that of the opening; and a fastener configured to tighten the closing member body and the clamp member while the panel is held between an outer circumferential portion of the closing member body and an outer circumferential portion of the clamp member, wherein the closing member body and the clamp member are configured to be disposed such that the closing member body and an inner circumferential portion of the clamp member abut on each other, and the outer circumferential portion of the clamp member and an inner edge portion of the opening abut on each other, whereby the closing member is electrically connected to the panel through the clamp member.
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