Aircraft Landing Gear Actuator Coupling Lever
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Solution Overview
Problem
Aircraft landing gear maneuvering actuators face issues with force feedback compatibility during deployment phases, leading to potential stress on couplings and internal components due to high stiffness in irreversible or reversible electromechanical actuators.
Innovation Solution
A coupling device comprising a lever articulated on the aircraft structure with preloading means to return to a stable rest position and stop means to define working positions, which absorbs undesired forces when inactive and transmits lifting forces when active, reducing stress on the actuator and aircraft structure.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If an irreversible electromechanical actuator or a reversible electromechanical actuator with high internal inertia is used, then the actuator can provide high lifting force and reliable maneuvering capability, but the actuator presents very high stiffness that transmits forces and stresses the couplings and internal components during deployment phases
Solution Approach 1:
A coupling device is introduced as an intermediary between the actuator and the aircraft structure. This coupling device includes a lever articulated on the aircraft structure and the actuator, with preloading means (such as a spring) acting on the lever. The preloading means creates a gap or play that allows the lever to move slightly under force feedback, preventing direct transmission of high forces from the stiff actuator to the couplings and internal components, while still enabling effective lifting when activated.
2Reliability
If the actuator is made rigid to ensure reliable maneuvering, then the actuator can effectively lift the landing gear, but the rigid actuator transmits forces during deployment that strongly stress the couplings and internal components
Solution Approach 1:
The coupling device with preloading means acts as a mediator that decouples the rigid actuator from the aircraft structure during deployment. The preloading means (spring) allows the lever to absorb force feedback through small movements, preventing harmful stress transmission while maintaining actuator reliability for lifting operations.
Solution Approach 2:
The coupling device changes the mechanical parameter of stiffness dynamically. During deployment, the preloading means introduces flexibility by allowing lever movement within a gap, reducing the effective stiffness and force transmission. When the actuator is activated for lifting, the lever is brought into abutment against the preloading means, neutralizing the flexibility and restoring full stiffness for reliable maneuvering.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
The device provides compatibility with force feedback during deployment, reducing stress on the actuator and aircraft structure by introducing flexibility that neutralizes undesired forces and allows efficient lifting when activated.
Implementation Method 1
preloading means acting on the lever to return the latter to a stable rest position
Implementation Method 2
The preloading means comprises two pushers 11 arranged on either side of the lever 10 to act on each side of the lever 10 and preloaded by springs 12
Data Source
Figure 1~2
Figure 3
AI summary
The invention relates to a device for coupling an actuator for controlling the landing gear of an aircraft to an aircraft structure, comprising: a lever (10;110) having a first end (10a;110a) to be pivotably connected onto the structure of the aircraft and a second end (10b;110b) onto which the actuator is pivotably connected; preloading means (11,12;112,122,123) engaging with the lever so as to return the latter toward a stable rest position which is occupied by the lever in the absence of a force passing through the actuator; and an abutment means (13;113) for defining at least one work position of the lever when the actuator is actuated.