Aircraft Aileron Actuator Reducing Stress via Common Connection Fitting
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Solution Overview
Problem
Hydraulically-operated actuators in aircraft flight control surfaces generate stress on the control surfaces due to the operation of redundant actuators, leading to accelerated fatigue and potential damage when one actuator is engaged.
Innovation Solution
An actuator device with two actuators connected via a common connection fitting, forming a slider clank mechanism that exchanges forces within the fitting, reducing stress on the flight control surface and preventing direct force application to the surface.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If two actuators are connected to the flight control surface via separate connection fittings, then redundancy is ensured, but stress is generated on the flight control surface when one actuator operates
Solution Approach 1:
The patent merges the connection fittings of two actuators into a single common connection fitting. Both actuators connect to the same fitting point on the flight control surface, allowing force exchange between actuators without generating stress on the control surface structure. This resolving the contradiction by combining separate connections into a unified connection point.
2Reliability
If one actuator stands by while the other operates, then redundancy is maintained, but the standing by actuator generates shear stress or torsional stress on the connection fittings
Solution Approach 1:
By combining both actuator connections into a single common connection fitting, the patent eliminates the relative motion between separate connection fittings that causes shear and torsional stresses. The unified fitting structure allows both actuators to share the same connection point, preventing differential forces from damaging the control surface during standby operation.
Data Source
AI summary
To provide an actuator device for a flight control surface which can reduce a stress applied to the flight control surface when one of two actuators is operated. The present invention relates to a hydraulically-operated actuator device 30 which drives a flight control surface of an aircraft 1, including a first actuator 31A that is provided with a first piston rod 39A, and drives an aileron body 11; a second actuator 31B that is provided with a second piston rod 39B, and drives the aileron body 11 when the function of the first actuator 31A is lost or reduced; and a single second connection fitting 41 to which the first piston rod 39A and the second piston rod 39B are both connected, wherein the first actuator 31A and the second actuator 31B are connected to the aileron body 11 via the second connection fitting 41.