Unified Flight Control Stick for Thrust and Yaw
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Solution Overview
Problem
Traditional aircraft flight control systems require separate inceptors for thrust and yaw control, which are heavy, difficult to install, and maintain, and lack intuitive control mechanisms.
Innovation Solution
A unified thrust lever configured as a control stick that can be moved along a first direction to control thrust magnitude and twisted to control yaw, incorporating a finger-operated stick for braking, allowing integrated control of thrust, yaw, and braking during flight and taxiing.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If separate inceptors are used for thrust and yaw control, then control precision is improved, but device complexity and weight increase
Solution Approach 1:
The patent combines the thrust lever and yaw control functions into a single unified control stick. The thrust lever is configured to both control thrust magnitude through forward/backward movement and control yaw through twisting motion, eliminating the need for separate rudder pedals and reducing overall system complexity while maintaining precise control capabilities.
Solution Approach 2:
The unified control stick serves multiple functions: it controls thrust magnitude, controls yaw during flight, and controls steering during taxiing. This multi-functional design reduces the number of separate inceptors needed and simplifies the cockpit control system while preserving the precision required for each individual control function.
2Adaptability or versatility
If separate inceptors are used for thrust and yaw control, then control functionality is improved, but weight increases
Solution Approach 1:
The patent merges the thrust lever and yaw control mechanisms into a single control stick assembly, eliminating the need for separate rudder pedals. This consolidation reduces the total weight of the control system while maintaining full control functionality for both thrust and yaw operations.
Solution Approach 2:
The unified control stick provides universal control capability for multiple functions (thrust, yaw during flight, steering during taxiing) through a single inceptor, reducing the cumulative weight that would result from having separate dedicated controls for each function.
3Reliability
If traditional separate inceptors are used, then control reliability is maintained, but ease of repair deteriorates
Solution Approach 1:
The unified control stick is designed with segmented functionality where thrust control and yaw control are distinct operational modes achieved through different movements of the same physical component. This segmentation allows for targeted maintenance of specific control functions while maintaining the integrated structure, improving ease of repair compared to multiple separate inceptors.
Solution Approach 2:
By combining thrust and yaw control into a single control stick, the patent reduces the number of separate components that require maintenance and repair. The integrated design means fewer connection points, actuators, and mechanical interfaces to fail or require service, thereby improving ease of repair while maintaining control reliability.
4Adaptability or versatility
If rudder pedals are used for yaw control, then yaw control capability is improved, but ease of operation deteriorates due to heavy and inaccessible location
Solution Approach 1:
The patent merges yaw control with the thrust lever, positioning the yaw control function in the easily accessible location of the thrust lever on the central pedestal. This eliminates the need for separate rudder pedals that are located at the pilot's feet, significantly improving ease of operation while maintaining full yaw control capability through twisting motion of the control stick.
Data Source
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AI summary
A flight control system for an aircraft, the flight control system comprising a thrust lever configured to control a thrust magnitude for the aircraft during flight, the thrust lever in the form of a control stick that can be moved along a first direction to control the thrust magnitude, and wherein the thrust lever is also configured to control a yaw angle of the aircraft during flight, whereby the control stick, or at least a portion of the control stick, can be twisted to control the yaw angle of the aircraft.