Self-Aligning Retractable Aircraft Strut Stabilizer
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Solution Overview
Problem
Retractable strut stabilization systems for aircraft are prone to misalignment during loading/unloading operations, leading to jamming issues when attempting to retract the strut, which can hinder aircraft operation.
Innovation Solution
A self-aligning retractable strut stabilization assembly with pivotally connected main struts, telescopically extendible strut members, and double-acting spring-biased centering mechanisms that automatically realign the strut when displaced, ensuring proper retraction into the strut bay.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a retractable strut stabilization system is deployed during aircraft loading/unloading operations, then the aircraft tail can be stabilized, but side loads can cause the strut to become off-centered or misaligned with the strut bay, leading to jamming during retraction
Solution Approach 1:
The strut assembly incorporates a self-aligning mechanism with spring-biased centering features that automatically correct misalignment during retraction. The springs apply centering forces to the strut, causing it to self-align with the strut bay without external intervention, thereby preventing jamming and ensuring reliable retraction operation.
2Reliability
If fixed support stabilization assemblies are manually placed under the aircraft, then tail stabilization is achieved, but pre-positioning and installation time are required, prolonging loading/unloading operations
Solution Approach 1:
The stabilization system is extracted from external fixed supports and integrated into the aircraft itself as an on-board retractable strut assembly. The strut stores within the aircraft fuselage and deploys only when needed, eliminating the need for external equipment placement and removal, thereby reducing installation time while maintaining stabilization reliability.
Solution Approach 2:
The stabilization system transitions from a static fixed support to a dynamic retractable strut that can deploy and retract as needed. The strut moves between stowed and extended positions, allowing rapid deployment during loading/unloading operations and automatic retraction when no longer needed, eliminating time-consuming manual installation and removal of fixed supports.
3Adaptability or versatility
If telescopic strut stabilization systems with integrated actuators are used, then on-board stabilization is achieved, but the strut cannot be physically disconnected and stored remotely when not in use
Solution Approach 1:
The telescopic strut is designed with nested components where the extension member fits within the main strut body. When retracted, the entire assembly nests within a dedicated strut bay in the aircraft fuselage, providing compact storage without requiring external equipment or complex disconnection procedures. The nested design allows the strut to maintain its integrated actuator while achieving space-efficient storage.
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
Ensures safe and reliable aircraft stabilization and operation by preventing strut jamming through automatic self-alignment, facilitating efficient loading/unloading operations even in dynamic environments.
Implementation Method 1
double-acting spring-biased centering mechanisms each having one end pivotally attached to the supporting structure of the aircraft and an opposite end attached to the main strut. The centering mechanisms define a zero-spring bias load state corresponding to an aligned condition of the main strut such that a displacement of the main strut out of the aligned condition responsively causes at least one centering mechanism to exert a spring-biased load in an opposite direction of the displacement
Data Source
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AI summary
Self-aligning retractable strut stabilization assemblies that are ground engageable in use are provided to stabilize a vehicle, e.g., a cargo aircraft during loading/unloading operations. The strut stabilization assembly may be on-board equipment associated with an aircraft that may be actuated (e.g., via on-board hydraulic and/or electric actuation systems) by the aircraft operator so as to stabilize the aircraft during certain ground operations, e.g., cargo and/or personnel loading/unloading operations. A laterally separated pair of centering mechanisms are attached to the main strut and define a zero-spring bias load state corresponding to an aligned condition of the main strut. Displacement of the main strut out of the aligned condition responsively causes at least one centering mechanism to exert a spring-biased load in an opposite direction of the displacement causing the at least one centering mechanism to return to the zero-spring bias load state thereby returning the main strut to the aligned condition thereof.