| 摘要 |
An integrated aerodynamic panel—e.g., for a trailing edge or leading edge of an aircraft aerodynamic surface—includes a first panel region defining inner and outer mold lines, and a second panel region contiguous with and extending from the first panel region in a tapering fashion. A splice plate region extends from the second panel region and includes an edge band region configured to accept a fastener. A filler region (e.g., a SYNCORE or fiberglass structure) adjacent the second panel region has an exposed surface substantially flush with the outer mold line.
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