Compact Gimbal Mechanism for Aircraft Pilot 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 due to the design of cyclic and collective control assemblies, which often require intricate mechanical linkages and openings that can lead to dirt ingress and limited motion ranges.
Innovation Solution
The implementation of a compact gimbal mechanism and floating grip designs in cyclic and collective control assemblies, allowing for reduced mechanical complexity, improved pilot comfort, and enhanced control precision by eliminating the need for top openings and enabling precise control inputs without compromising motion range.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional mechanical linkages with top openings are used in cyclic and collective control assemblies, then the structural integrity is maintained, but dirt ingress occurs and motion range is limited
Solution Approach 1:
The patent removes the top opening from the traditional control assembly structure, extracting the harmful element that allows dirt ingress while maintaining the functional integrity of the control system through alternative linkage designs
Solution Approach 2:
The patent replaces complex mechanical linkages with a gimbal-based mechanism that achieves the same control functions through rotational joints, simplifying the structure and eliminating openings that would allow contamination
2Strength
If complex mechanical linkages are used in control assemblies, then structural strength is maintained, but device complexity increases and installation becomes difficult
Solution Approach 1:
The patent divides the control assembly into modular components including cyclic control, collective control, and gimbal mechanisms that can be independently manufactured and assembled, reducing overall complexity while maintaining structural integrity
Solution Approach 2:
Instead of using rigid mechanical linkages to transmit control forces, the patent inverts the approach by using gimbal joints that allow rotational movement, achieving control through angular displacement rather than direct mechanical coupling
3Stability of the object's composition
If traditional control assemblies with fixed motion ranges are used, then structural stability is maintained, but pilot comfort and control precision deteriorate
Solution Approach 1:
The patent implements dynamic motion ranges through gimbal joints that can rotate through optimized angular ranges, allowing the control assembly to adapt its motion characteristics while maintaining structural stability during flight operations
Solution Approach 2:
The patent optimizes the rotational parameters of the gimbal joints to provide ideal motion ranges that enhance pilot comfort and control precision, adjusting the angular displacement parameters to match human ergonomic requirements
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
This solution enhances pilot control precision and comfort by reducing pilot-induced oscillations and allowing for precise control inputs while simplifying installation and reducing the risk of dirt ingress, thereby improving overall aircraft handling and maintenance efficiency.
Implementation Method 1
a first gimbal of the cyclic control assembly and a second gimbal of the cyclic control assembly
Data Source
AI summary
According to one embodiment, a control assembly includes a first gimbal and a second gimbal. The first gimbal is rotatable about a first axis of rotation. The first gimbal comprises a first linkage attachment point offset from the first axis of rotation. The second gimbal is rotatably coupled to the first gimbal and rotatable relative to the first gimbal about a second axis of rotation. The second gimbal comprises a second linkage attachment point offset from the second axis of rotation and a control shaft attachment point.