Aircraft Flight Control Logic for Exclusive Pilot Authority
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Solution Overview
Problem
Existing aircraft control systems with mechanically uncoupled flight controls lack exclusive control authority for pilots during dual operating modes, leading to potential safety issues, especially in urgent situations where quick trajectory corrections are necessary.
Innovation Solution
A control method and system that ensures exclusive control authority for one pilot over the aircraft's aerodynamic means by alternately activating and deactivating control members, with sensory feedback to indicate active control, and a mechanism to temporarily inhibit reactivation of deactivated members to prevent simultaneous control.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If algebraic summation logic is used for control commands from two control members, then the system allows simultaneous dual control operation, but the resulting control setpoint can cancel out and no control authority is available for urgent corrections
Solution Approach 1:
The system dynamically switches between instruction mode (summation logic) and priority mode (exclusive control) based on operational needs. The operational logic alternates between modes where one control member has total authority or both contribute equally, resolving the contradiction between dual operation versatility and reliable control authority.
Solution Approach 2:
The control system changes the parameter of control authority distribution by switching between two operational modes: in instruction mode both control members contribute with summation logic, while in priority mode one control member gains exclusive total authority, ensuring adequate control response in urgent situations.
2Ease of operation
If priority button is used to activate one control member, then one control member can control the aircraft, but the control member does not have total authority over the aerodynamic means
Solution Approach 1:
When a priority button is activated, the system dynamically transitions to a state where the associated control member gains total authority over the aerodynamic means through exclusive control logic, ensuring both ease of operation and complete control versatility when needed.
3Adaptability or versatility
If mechanically coupled flight controls are used, then pilots can manually pilot the aircraft simultaneously or alternately, but the mechanical coupling is useless for mini-sticks with very little travel
Solution Approach 1:
The patent extracts and removes the mechanical coupling between control members, retaining only the electrical signal transmission. This eliminates the complexity of mechanical linkages while preserving the capability for simultaneous or alternate piloting through electronic control signal management.
Solution Approach 2:
The mechanical coupling system is replaced with an electrical signal-based control system. Control commands from mini-sticks or other control members are transmitted as electrical signals to the flight control computer, eliminating the need for mechanical linkages while maintaining full control functionality.
4Adaptability or versatility
If algebraic summation of control commands is used, then dual mode operation is enabled, but the control member having priority does not have total authority over the aerodynamic means
Solution Approach 1:
The system dynamically adjusts control authority distribution based on the operational mode. In instruction mode, algebraic summation enables dual operation versatility, while in priority mode the system switches to exclusive control logic that grants total authority to the priority control member, resolving the contradiction between dual mode operation and total control authority.
Data Source
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AI summary
The present invention relates to a control method (1) for controlling the aerodynamic means of an aircraft with mechanically uncoupled flight controls, enabling the aircraft to be piloted by at least two pilots, said aircraft comprising at least two control elements (22 - 23) intended to be operated respectively by one of said at least two pilots and enabling each of the control commands to carry out a displacement of said aerodynamic means relative to an incident airflow, said control method (1) comprising a piloting logic, referred to as operational logic (2), said operational logic (2) comprising a dual operating mode (3) where each control element (22 - 23) can control said aerodynamic means (20).Such a control method (1) is characterized in that, in said dual operating mode (3), only one of said at least two control elements, said activated element (22), exclusively controls said aerodynamic means over a total range of movement, the other control element, said deactivated element (23), being then temporarily inoperative on said aerodynamic means.