Horizontal Control Column Transfer Assembly for Aircraft Pitch
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Solution Overview
Problem
Current aircraft control yokes, especially those in flight simulators and single-engine planes, are not suitable for large commercial aircraft as they extend into the cockpit, occupy valuable space, and use unsupported structures prone to backlash and friction, lacking the redundancy required by regulations.
Innovation Solution
A horizontal control column extending from a control wheel to the front wall of the cockpit, using a transfer assembly with idler links and coupler links to translate horizontal forces into pitch control mechanisms without relying on sliding structures or bearings, allowing for efficient pitch control without occupying floor space.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Area of stationary object
If a horizontal control column is used to avoid occupying floor space, then cockpit space is improved, but the control mechanism becomes prone to backlash and friction due to unsupported structures
Solution Approach 1:
The patent introduces a transfer assembly as an intermediary mechanism between the horizontal control column and the pitch control mechanism. This transfer assembly includes a coupler link and idler links that mechanically couple the control column to the pitch control without requiring the control column to extend through the floor or be supported by sliding structures, thereby maintaining reliability while preserving cockpit space.
Solution Approach 2:
The control system is segmented into distinct functional components: the horizontal control column, the transfer assembly (with coupler link and idler links), and the pitch control mechanism. This segmentation allows each component to be optimized independently - the control column remains horizontal for space efficiency, while the transfer assembly handles the force transmission without requiring floor penetration or sliding supports.
2Ease of operation
If wire rope cables or roller chains are used in critical control paths, then control transmission is achieved, but the system becomes labor-intensive, costly, and prone to undesirable tactile sensation
Solution Approach 1:
The patent replaces flexible mechanical elements like wire rope cables and roller chains with a rigid linkages system consisting of the coupler link and idler links. This substitution eliminates the tactile inconsistencies and maintenance issues associated with flexible cables while providing direct, positive mechanical coupling between the control column and pitch control mechanism.
3Ease of operation
If a control column extends through the floor with sliding structures, then pitch control is achieved, but the system becomes prone to friction and contamination
Solution Approach 1:
The patent extracts the control column from the traditional floor-extended configuration and repositions it as a horizontal column within the cockpit. By taking out the column from its conventional vertical floor-penetrating position, the design eliminates the need for sliding structures and bearings that would be required to support a horizontal column extending through the floor, thereby eliminating friction and contamination risks.
4Ease of operation
If traditional vertically mounted control columns are used, then pilot familiarity is maintained, but the control column occupies space between pilot's legs and requires floor mechanisms
Solution Approach 1:
The patent inverts the conventional vertical control column orientation by implementing a horizontal control column. Instead of extending vertically through the floor, the control column extends horizontally within the cockpit, allowing pilots to maintain familiar push-pull control motions while freeing up cockpit floor space and eliminating the need for floor-mounted mechanisms.
Data Source
Figure 1
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Figure 2b
AI summary
An apparatus for controlling the pitch of an aircraft. The apparatus includes a horizontal control column extending from a control wheel horizontally towards a front wall of a cockpit. A pitch output link is connected to a downstream pitch control mechanism to transfer a force applied at the pitch output link to the downstream pitch control mechanism. A transfer assembly is connected to the horizontal control column and to the pitch output link. The transfer assembly translates a horizontal force applied to the horizontal control column to the pitch output link to provide the force applied to the downstream pitch control mechanism.