Adjustable Aircraft Pedal Linkage for Precision Control
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Solution Overview
Problem
Current aircraft flight control systems, particularly in rotorcraft, face challenges in pilot control precision, comfort, and installation complexity, especially regarding cyclic and collective control assemblies, which can lead to reduced pilot visibility and increased risk of inadvertent control inputs.
Innovation Solution
The design of adjustable cyclic and collective control assemblies with a 'floating' grip mechanism and compact gimbal systems allows for reduced range of motion, improved pilot visibility, and simplified installation by positioning these assemblies to the right of the pilot seat, eliminating the need for macroscopic openings and enhancing comfort through adjustable arm rests and hand rests.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Illumination intensity
If cyclic and collective control assemblies are positioned in traditional locations, then control functionality is maintained, but pilot visibility is reduced and inadvertent control inputs increase
Solution Approach 1:
The control assemblies are repositioned from the conventional footwell area to the right side of the pilot seat, utilizing previously underutilized space. This spatial relocation in a different dimension allows the pilot to maintain visibility while accessing controls through a modified pathway that reduces inadvertent inputs.
Solution Approach 2:
A custom linkage mechanism serves as an intermediary between the repositioned control assemblies and the rotor control systems. This intermediary linkage transmits control inputs accurately while accommodating the changed spatial arrangement, ensuring control precision is maintained despite the non-traditional positioning.
2Ease of manufacture
If traditional control assembly configurations are used, then control functionality is maintained, but installation complexity increases due to macroscopic openings
Solution Approach 1:
The control assemblies are extracted from the footwell area and repositioned to the right side of the pilot seat. This extraction eliminates the need for large macroscopic openings in the floor structure, as the controls are installed in a different location that requires minimal structural modification.
Solution Approach 2:
The control system is segmented into modular assemblies that can be independently positioned and installed. The cyclic and collective control assemblies are separate modules that can be mounted on the right side of the seat without requiring integrated structural modifications throughout the aircraft structure.
3Ease of operation
If control assemblies are repositioned to improve visibility, then pilot comfort improves, but control input range of motion must be reduced
Solution Approach 1:
The linkage mechanism incorporates dynamic elements that allow the control assemblies to move through a optimized arc of motion. The geometry of the linkage is designed to provide sufficient range of motion for effective rotor control while keeping the control inputs within a compact space that improves pilot comfort.
Solution Approach 2:
The mechanical parameters of the linkage system, including arm lengths and joint angles, are optimized to transform the pilot's foot movements into the required rotor control inputs. By adjusting these parameters, the system achieves the necessary control authority within a reduced range of motion that enhances pilot comfort.
Data Source
AI summary
According to one embodiment, a method of adjusting an aircraft pedal assembly includes providing a pedal linkage coupled between a pedal and an attachment assembly situated proximate to an aircraft instrument panel. A brake cylinder is provided coupled between the pedal and the attachment assembly. The pedal linkage is rotated in response to an adjustment input. The pedal linkage is maintained approximately parallel to the brake cylinder during rotation of the pedal linkage.