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Process for protection from shocks that could affect aircraft landing gear

A technology for landing gear and aircraft, applied to aircraft, chassis, belts/chains/gears, etc., can solve problems such as damage to actuators

Active Publication Date: 2020-06-26
SAFRAN LANDING SYSTEMS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

These shocks may cause sudden stress returns to the operating actuator, which may damage the actuator

Method used

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  • Process for protection from shocks that could affect aircraft landing gear
  • Process for protection from shocks that could affect aircraft landing gear
  • Process for protection from shocks that could affect aircraft landing gear

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0015] first reference figure 1 , the undercarriage has legs 1 (see here at the ends) articulated to the aircraft structure along an articulation axis X in a known manner, to be movable between the deployed and retracted positions shown here, the undercarriage on landing The retracted position is the position of the landing gear in flight before being brought into the deployed position.

[0016] The frangible strut 2 is hinged on one side to the leg 1 and on the other side to the aircraft structure. The frangible strut 2 comprises two links 2 a , 2 b hinged to each other at a joint 3 . Link 2a is also hinged to the aircraft, while link 2b is hinged to leg 1 . The frangible strut 2 is stabilized in a generally aligned position by means of a stabilizing member 4 comprising two links 4a, 4b also hinged to each other. The link 4a is hinged on the leg 1 and the link 4b is hinged on the strut 2 . The couplings 4a, 4b are held in a substantially aligned position by means of a loc...

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PUM

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Abstract

The invention provides a method for protecting the landing gear of an aircraft against stroke-end shocks, the landing gear is manoeuvrable between a retracted position and a deployed position by meansof a single electromechanical operating actuator (10) between these two positions. According to the invention, the method involves the step of equipping the electromechanical operating actuator withan internal damping device (17) arranged between an output shaft (18) of the electromechanical actuator coupled to the landing gear and a motor shaft (13) with a motor (12) of the electromechanical actuator.

Description

technical field [0001] The invention relates to a method for protecting the landing gear of an aircraft against end-of-travel impacts. In addition, the invention relates to an aircraft landing gear steerable between a retracted position and a deployed position. Background technique [0002] There is known a landing gear movable between a retracted position and a deployed position, equipped with an electromechanical rotary actuator, as shown in document FR2946319. [0003] In some situations, such as a power failure, the landing gear is released from its retracted position and is free to move to the deployed position under the influence of gravity and relative wind. During such deployment, the electromechanically operated actuator does not regulate the speed of travel of the landing gear, and the landing gear may reach the deployed position at high speed, causing the landing gear to stop suddenly. Other impacts may occur, such as when the landing gear hits the ground during...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C25/24
CPCB64C25/24F16H49/001B64C25/20F16C41/004F16C2326/43
Inventor F·弗蒂尔S·杜波依斯F·道芬
Owner SAFRAN LANDING SYSTEMS