Integrated Aircraft Flight Control Trim Assembly
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Solution Overview
Problem
Current aircraft flight control systems can be complex and cumbersome, making pilot control less efficient and more difficult to install, which can affect pilot comfort and control precision.
Innovation Solution
The design of integrated cyclic and collective control assemblies with compact gimbal mechanisms and adjustable arm rests, allowing for reduced range of motion and improved pilot visibility, along with a fly-by-wire system that simplifies installation and enhances control precision.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If conventional parallel actuator manner is used with separate actuators secured directly to the airframe, then control authority and reliability are maintained, but device complexity and installation difficulty increase
Solution Approach 1:
The patent combines multiple separate actuators (cyclic actuator, collective actuator, and trim actuator) into a single integrated flight control unit. This integration reduces the number of separate components and mounting points while maintaining all necessary control functions, thereby reducing device complexity without compromising control authority or reliability.
Solution Approach 2:
The integrated flight control unit performs multiple functions that were previously handled by separate actuators: cyclic control, collective control, and trim functions. This multi-functionality allows a single device to replace multiple separate components, simplifying the overall control system architecture while maintaining comprehensive control capability.
2Ease of manufacture
If conventional separate actuator installation is used, then control functions are maintained, but installation time and complexity increase
Solution Approach 1:
By integrating multiple actuators into a single unit with a common mounting structure, the patent reduces the number of installation steps. Instead of securing multiple separate actuators to different airframe locations, the integrated unit requires a single mounting operation, significantly reducing installation time and simplifying the manufacturing process.
3Ease of operation
If full range of motion is provided in flight controls, then pilot control authority is maintained, but pilot comfort and visibility are reduced
Solution Approach 1:
The patent modifies the range of motion parameters of the flight controls by providing stops that limit the travel distance of control linkages. This parameter change reduces the angular displacement required for full control authority, allowing the control sticks to be positioned higher and improving pilot visibility and comfort while maintaining complete control capability through the modified range.
Data Source
Figure 1
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Figure 3A
AI summary
According to one embodiment, an integrated aircraft trim assembly (500) features a shaft (590), a mechanical stop (580), a trim motor (510), a clutch (515), and a measurement device (530, 570). The mechanical stop device (580) is operable to at least partially prevent rotation of the shaft (590) outside of an allowable range of motion. The trim motor (510) has an output component in mechanical communication with the shaft (590). The clutch (515) separates the trim motor (510) from the shaft (590). The measurement device (530, 570) is proximate to the shaft (590) and operable to measure a position of the shaft (590) and communicate the measured position to a flight control computer operable to change a position of a flight control device.