Aircraft Flight Control Column Dual Torque Emergency Clutch
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Solution Overview
Problem
Current helicopter flight control systems lack dynamic force feedback systems that can adapt to flight conditions, and existing active systems pose motor failure hazards, potentially leading to catastrophic stick blockages.
Innovation Solution
A flight control stick device with a dual torque-generating system and a clutch mechanism that selectively connects a primary path with a secondary friction-based path, ensuring continuous operation even if the primary path fails, without requiring electrical power for the secondary path.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If active force feedback systems with motors are implemented, then dynamic reconfiguration of force law is achieved, but motor failure causes stick blockage
Solution Approach 1:
The force feedback system is segmented into two independent paths: a primary active path with motors for dynamic force law reconfiguration, and a secondary passive friction-based path for emergency operation. The clutch mechanism segments the power transmission, allowing selective engagement of either path based on operational needs or failure conditions.
Solution Approach 2:
The system incorporates a secondary emergency path with friction-based torque generation that is prepared in advance to take over if the primary motorized path fails. The clutch mechanism is pre-configured to automatically or manually engage the secondary path, cushioning against the catastrophic failure mode of stick blockage.
2Reliability
If passive mechanical force feedback systems are used, then reliability is maintained, but dynamic reconfiguration capability is lost
Solution Approach 1:
The system merges the advantages of both passive and active force feedback systems into a single hybrid architecture. The secondary passive friction-based path provides reliable fail-safe operation, while the primary active motorized path enables dynamic reconfiguration of force laws. Both paths are combined through the clutch mechanism that allows selective operation.
Solution Approach 2:
The force feedback system achieves multi-functionality by incorporating two distinct torque generation mechanisms: motorized torque for adaptive control and friction-based torque for passive resistance. The clutch mechanism enables the system to universally operate in either mode or both modes simultaneously, depending on flight conditions and system state.
3Reliability
If a dual-path system with clutch is implemented, then redundancy is achieved, but device complexity increases
Solution Approach 1:
The clutch mechanism serves as an intermediary component that manages the complexity of the dual-path system. It acts as a mediator between the primary motorized path and the secondary friction-based path, controlling torque transmission and path selection without requiring complex control electronics or multiple clutch mechanisms.
Solution Approach 2:
The friction-based secondary path is designed to be self-regulating, using friction between a drum and cable to automatically generate appropriate torque without requiring external power or complex control systems. This self-service characteristic reduces the overall system complexity while maintaining operational continuity.
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 system provides adaptive force feedback to the pilot, preventing dangerous stick movements while maintaining stick functionality in case of primary path failures, without the risk of motor-induced blockages.
Implementation Method 1
the second torque being generated by friction between the cable and the drum when the drum is driven in rotation with respect to the cable
Implementation Method 2
the clutch comprises an electromagnet which, when it is energized, biases the clutch part toward the first position
Data Source
AI summary
The invention relates to an aircraft flight control column device (1) comprising: a casing (2) for attaching to an aircraft structure; an output shaft (3) for connecting to a flight control column (56), the output shaft (3) being mounted such that it rotates in relation to the casing (2); a primary group (4) comprising a first torque-generating body (7, 8) for applying a first torque to the output shaft (3); a secondary group (5) comprising a second torque-generating body (7, 8) for applying a second torque to the output shaft (3); and a clutch for selectively connecting the primary group (4) and the secondary group (5) to the output shaft (3).