TRAILING EDGE SPLIT FLAP WITH PNEUMATIC ACTUATION

Title:

TRAILING EDGE SPLIT FLAP WITH PNEUMATIC ACTUATION

Document Type and Number:

Japanese Patent JP2013023217

Kind Code:

A

Abstract:

To provide a split flap which lessens flutter concerns.

A system for pneumatically actuating a split flap hingedly mounted near or at a trailing edge of an airfoil. The system includes a bladder system disposed between the split flap 14 and the upper surface 18 of the airfoil 10. The split flap is a small-chord (usually 1-3% of total wing chord) long-span lower panel which separates from the airfoil trailing edge by means of a hinge 16 or a flexible lower skin. Deployment of the split flap is actuated pneumatically by the inflatable bladder system. The split flap may exist at a fixed wing trailing edge, a moving flap trailing edge, or an empennage trailing edge. The pneumatic bladder 22 provides distributed force to extend and retract the split flap. This pneumatic approach eliminates extra drag, reduces cost and weight, and lessens flutter concerns.

Inventors:

BALZER MICHAEL A
SANTINI GREGORY M
KLEIN MICHAEL K

Application Number:

JP2012156414A

Publication Date:

February 04, 2013

Filing Date:

July 12, 2012

Export Citation:

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Assignee:

BOEING CO

International Classes:

B64C3/50

Foreign References:

GB563319A	1944-08-09
US3711039A	1973-01-16
US20020074459A1	2002-06-20

Attorney, Agent or Firm:

Sonoda Yoshitaka
Kobayashi Yoshinori

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