Slat of aircraft, method for adjusting attachment position of slat, and aircraft

Patent metadata

Field	Value
Publication number	US-9415859-B2
Application number	US-201414166411-A
Country	US
Kind code	B2
Filing date	Jan 28, 2014
Priority date	Jan 29, 2013
Publication date	Aug 16, 2016
Grant date	Aug 16, 2016

Abstract

The present invention includes: a slat 3 ; and a position adjustment mechanism that adjusts an attachment position of the slat 3 to a main wing 1 by causing the slat 3 to swing, the position adjustment mechanism including: a pivot shaft S 1 as a center of the swing motion of the slat 3 ; and a driving shaft S 2 that is rotatably supported on a rail 12 , and induces the swing motion of the slat 3 . The driving shaft S 2 includes: a main shaft 30 that causes the slat 3 to swing by acting thereon; an inner-side eccentric bushing 31 that is fixed to the main shaft 30 , and eccentric with respect to the main shaft 30 ; and an outer-side eccentric bushing 32 that is eccentric with respect to the inner-side eccentric bushing 31 , rotatably arranged therearound, and supported rotatably with respect to the rail 12.

First claim

What is claimed is:

1. A slat of an aircraft comprising:
a slat body that is attached to a bracket capable of reciprocating with respect to a main wing of the aircraft so as to be movable between a deployed position and a retracted position; and
a position adjustment mechanism that adjusts an attachment position of the slat to the main wing by causing the slat body to swing,
wherein the position adjustment mechanism includes:
a pivot shaft as a center of the swing motion of the slat body; and
a driving shaft that is rotatably supported on the bracket, and induces the swing motion of the slat body,
wherein the driving shaft includes:
a main shaft that causes the slat body to swing by acting thereon; and
an eccentric body that is supported rotatably with respect to the bracket, and rotates integrally with the main shaft, wherein the eccentric body includes:
a cylindrical inner-side eccentric body that is fixed to the main shaft, and eccentric with respect to the main shaft, and
a cylindrical outer-side eccentric body that is eccentric with respect to the inner-side eccentric body, rotatably arranged around the inner-side eccentric body, and supported rotatably with respect to the bracket.

2. The slat of an aircraft according to claim 1 , wherein the pivot shaft is arranged on a side closer to the slat body than the driving shaft.

3. The slat of an aircraft according to claim 1 , wherein an eccentricity δ 1 of the inner-side eccentric body from the main shaft and an eccentricity δ 2 of the outer-side eccentric body from the inner-side eccentric body correspond to each other.

4. The slat of an aircraft according to claim 1 , wherein the inner-side eccentric body is an inner-side eccentric bushing that is fixed to the main shaft, and
the outer-side eccentric body is an outer-side eccentric bushing that is arranged around the inner-side eccentric body.

5. A method for adjusting a position of the slat of an aircraft according to claim 1 , comprising
reversely rotating the inner-side eccentric body and the outer-side eccentric body by a same rotation angle.

6. An aircraft comprising a main wing where the slat according to claim 1 is arranged on a leading edge side as a high-lift device.

Assignees

• Mitsubishi Aircraft Corp

Inventors

• Okabe Yoshinori
• Ishihara Kenya

Classifications

• B64C9/22 Primary

  at the front of the wing · CPC title