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Tertiary locking assembly for a thrust reverser

A technology of thrust reverser and locking components, which is applied in the direction of blade support components, electrical components, engine components, etc., which can solve the problems of less use and difficulty

Inactive Publication Date: 2014-01-01
AIRCELLE
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The third lock is often in the form of a locking hook capable of engaging with a shaft fixed to the cover, preventing its withdrawal along the rail
Thus relatively seldom used, and thus the manual mode is considered acceptable although difficult

Method used

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  • Tertiary locking assembly for a thrust reverser
  • Tertiary locking assembly for a thrust reverser
  • Tertiary locking assembly for a thrust reverser

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0055] Such as figure 1 As shown in , the so-called third locking assembly of the thrust reverser comprises a third lock 1 associated with a primary control line 2 .

[0056] Said control circuit 2 comprises a solenoid 3 constituting the electromechanical control means of the third lock 1 . Of course, according to the type of the third lock 1, other electromechanical control devices are also applicable, and the present invention is not limited thereto.

[0057] This solenoid 3 is powered by a power supply line 4 from a junction box 100 between the turbojet engine nacelle and the pylon connected to it. The power supply line comes from the electrical grid of the aircraft.

[0058] In normal operation, during manipulation of the thrust reverser, commands from the aircraft activate the supply line 4 of the solenoid 3 so that it can drive the third lock 1 towards its withdrawn position, which then allows manipulation of the device as explained previously. At idle, the solenoid 3...

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PUM

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Abstract

The invention relates to a so-called tertiary locking assembly for a thrust reverser with which a turbojet engine nacelle is provided, said locking assembly including at least one so-called tertiary lock associated with at least one primary control line (2) comprising at least one electromechanical control means (3), as well as a power supply (4) connected to said electromechanical control means, characterized in that it includes at least one secondary control line (20) comprising at least one electromechanical control means (30), as well as a power supply (40) which is connected to the electromechanical control means and which is separate from the electrical power supply of the primary control line, said secondary control line being further provided with at least one manually controlled switch (50).

Description

technical field [0001] The invention relates to a so-called third locking assembly of a thrust reverser equipped on a turbojet nacelle, and to a switch of such an assembly. [0002] The invention relates in particular to the system for opening the engine cowling of the nacelle and its integration into the third bolt of the "O-tube" nacelle. Background technique [0003] The aircraft is propelled by a number of turbojet engines, each located in an engine nacelle, which also houses an associated set of drives associated with its operation when said jet turbine engines are running or stopped, and performing various functions. These associated drives include in particular mechanical thrust reverser drive systems. [0004] The nacelle generally has a tubular structure: the structure includes the upstream air intake of the jet turbine engine, the middle section intended to enclose the fan of the turbojet engine, the downstream section housing the thrust reverser and intended to e...

Claims

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Application Information

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IPC IPC(8): F01D5/00F02K1/76H01H9/32H01H3/16
CPCF01D5/005F02K1/766H01H3/40F05D2270/62F05D2270/52H01H3/42F05D2230/80F05D2240/14
Inventor 科朗汀·休马蒂厄·勒鲁维尔
Owner AIRCELLE
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