Aircraft Inceptor Control Mechanism with Differential Motion Conversion
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Solution Overview
Problem
Current aircraft control mechanisms are compromised by the need to limit size and weight, leading to non-linear inceptor trajectories and inefficient use of space, which affects pilot comfort and control precision.
Innovation Solution
A control mechanism featuring a conversion mechanism with a translatable and rotatable part, a differential device, and adjustment members that allow for reversible translation to rotation conversion, ensuring the motion of control and adjustment members are disconnected, enabling a compact and ergonomic design that maintains feel force consistency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Manufacturing precision
If long arms are used in control mechanisms to limit curving of the inceptor motion, then the inceptor trajectory becomes more linear, but the size and weight of the control mechanism increases
Solution Approach 1:
The patent employs a differential device that dynamically adjusts the mechanical linkage during operation. The differential mechanism allows the control system to maintain linear inceptor trajectory through variable geometric relationships rather than fixed long arms, enabling the same functional outcome with shorter, lighter components.
Solution Approach 2:
The differential device acts as an intermediary mechanism between the inceptor and the control surfaces. It mediates the motion transmission by converting and adjusting the inceptor's linear motion into appropriate control surface movements, eliminating the need for long direct linkage arms while maintaining trajectory linearity.
2Manufacturing precision
If long arms are used in control mechanisms to limit curving of the inceptor motion, then the inceptor trajectory becomes more linear, but the space occupied by the control mechanism increases
Solution Approach 1:
The dynamic differential mechanism enables compact packaging by allowing motion transformation within a confined space. The variable geometry of the differential device achieves linear trajectory control without requiring the extensive spatial envelope that fixed long arms would demand.
Solution Approach 2:
The differential device utilizes multi-dimensional motion transformation, converting linear inceptor motion into rotational control surface movement through a complex spatial mechanism. This dimensional transformation allows compact arrangement of components while maintaining the functional requirement for linear trajectory.
3Weight of moving object
If the control mechanism is made compact to reduce size and weight, then the space and weight are reduced, but the inceptor trajectory curvature increases
Solution Approach 1:
The differential device serves as a mediating mechanism that compensates for the curvature introduced by compact dimensions. It adjusts the motion transmission ratios dynamically to counteract trajectory deviations, maintaining linearity despite the reduced physical size of the control mechanism.
4Weight of moving object
If the control mechanism is made compact to reduce size and weight, then the space and weight are reduced, but the adjustment process affects the feel force for aircraft control
Solution Approach 1:
The patent segments the control system into distinct functional modules: the inceptor, the differential device, and the control surface linkage. This segmentation isolates the adjustment mechanisms from the feel force transmission path, allowing adjustments to be made without compromising the consistency of pilot feedback during normal aircraft control operations.
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 mechanism provides a compact and ergonomic control system that maintains feel force consistency, allowing pilots of different statures to operate with the same precision and comfort, while accommodating long strokes without increasing size or weight.
Implementation Method 1
the conversion mechanism being configured to reversibly convert translational motion of the inceptor connector to rotational motion of the differential device
Implementation Method 2
The elastic member may be configured to bias the locking member to, during a control process, engage one of the plurality of notches
Data Source
AI summary
A control mechanism for an aircraft includes: a conversion mechanism having a translatable part and a rotatable part, the translatable part being reversibly translatable and being connectable to an inceptor; an inceptor connector connected to the translatable part of the conversion mechanism; a differential device connected to the rotatable part of the conversion mechanism, the conversion mechanism being configured to reversibly convert translational motion of the inceptor connector to rotational motion of the differential device; an adjustment member connected to the differential device; and a control member connected to the differential device; wherein the differential device is configured such that the adjustment member is maintainable in position during an aircraft control process to permit: translation of the inceptor connector from a translational neutral position; and corresponding movement of the control member, to control the aircraft through the differential device.