Actuating assembly for a thrust reverser of an aircraft engine

Patent metadata

Field	Value
Publication number	US-9874268-B2
Application number	US-201314133327-A
Country	US
Kind code	B2
Filing date	Dec 18, 2013
Priority date	Jun 20, 2011
Publication date	Jan 23, 2018
Grant date	Jan 23, 2018

Abstract

An actuating assembly for an aircraft engine thrust reverser includes a drive shaft bearing a master pinion; a ball screw bearing a slave pinion engaging with the master pinion; a nut capable of translating over the ball screw as a result of the rotation of the ball screw; an extension tube rigidly secured to the nut and a lock assembly to block the rotation of the drive shaft in a so-called direct jet position of the reverser. The extension tube includes, at its free end, a member for connecting to a portion of the reverser prior to being actuated. In particular, the lock assembly includes an abutment secured to the drive shaft, and a cotter moveable between a locking position and an unlocking position. The reduction ratio (R) between the slave and master pinions is even.

First claim

What is claimed is:

1. An actuating assembly for an aircraft engine thrust reverser, comprising:
a drive shaft bearing a master pinion;
a ball screw bearing a slave pinion engaging with said master pinion;
a nut translating over the ball screw as a result of the rotation thereof;
an extension tube secured to said nut, the extension tube comprising, at a free end thereof, an eyelet for connecting to a clevis of said reverser to be actuated; and
locking means for blocking a rotation of said drive shaft, capable of immobilizing said portion in a closed position of the reverser,
wherein said locking means comprise an abutment secured to said drive shaft, and a cotter movable between a locking position in which it prevents a rotation of said abutment, and an unlocking position in which it allows the rotation of said abutment,
wherein a reduction ratio (R) between said slave pinion and said master pinion is even, such that:
when said extension tube is in a fully retracted position and said eyelet is correctly oriented with respect to said clevis, said drive shaft and said abutment are in a reference position in which said abutment is in contact with said cotter in locked position, and
said abutment always reaches said reference position after a full or half rotation of said extension tube during maintenance operations.

2. The actuating assembly according to claim 1 , wherein the locking of said abutment by said cotter is effective including when the portion of said reverser to be actuated is set apart from a direct jet position by a predetermined distance (J).

3. The actuating assembly according to claim 2 , wherein said predetermined distance (J) is of the magnitude of 2 millimeters.

4. The actuating assembly according to claim 2 , wherein features of said actuating assembly are selected such that:
( J/P )* R <(1 −X ),
where: J is the predetermined distance;
P is a pitch of the ball screw;
R is the reduction ratio between said slave pinion and said master pinion; and
X is a positive real number within the interval [0, 1], representing a ratio between a cumulative circumferential length of said abutment and said cotter, and the length of the associated total circumference.

5. A thrust reverser for a turbojet engine, wherein it comprises at least an actuating assembly in accordance with claim 1 .

6. A nacelle for a turbojet engine, wherein it comprises a thrust reverser in accordance with claim 5 .

Assignees

• Aircelle Sa
• Sagem Defense Securite

Inventors

• Moradell-Casellas Pierre
• Delnaud Franck

Classifications

• F16H25/2454

  Brakes; Rotational locks · CPC title

• F02K1/766

  with blocking systems or locking devices; Arrangement of locking devices for thrust reversers · CPC title

• F02K1/76 Primary

  Control or regulation of thrust reversers · CPC title

• Y02T50/671

  Cross-Sectional Technologies · mapped topic

• F16H2025/2084

  Perpendicular arrangement of drive motor to screw axis · CPC title