Drag reduction device for exposed landing gear cavities
US10745114B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Aug 7, 2017 |
| Grant date | Aug 18, 2020 |
| Priority date | — |
| Expiry date | Feb 26, 2039 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64C2025/125
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
An exposed main landing gear cavity in a bottom wall of an aircraft fuselage may include a main landing gear cavity outer ring recessed within the fuselage and having an inner surface encircling the main landing gear cavity, first baffle extending inward from the outer ring inner surface at an aft and inboard position on the inner surface, and a second baffle extending inward from the outer ring inner surface at an aft and outboard position on the outer ring inner surface. The main landing gear cavity may further include an aft fairing disposed proximate the outer ring bottom edge of the outer ring and connected to the fuselage at an aft side of the main landing gear cavity. An aft fairing top surface may have curvature causing the top surface to extend downward away from the outer ring as the top surface extends inward away from the outer ring.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.