Aircraft Control Stick Force Coupling for Fault-Tolerant Haptic Feedback
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Solution Overview
Problem
Aircraft control sticks with active force feedback systems are prone to malfunction in case of electrical or mechanical faults, leading to loss of feedback, and existing systems are bulky, expensive, and difficult to integrate, necessitating a mechanical backup channel to prevent free pivoting and provide variable resistive force during malfunctions.
Innovation Solution
A force application device with a mechanical backup channel using an electromagnet, actuator, and clamping mechanism that alternates between operational and locking configurations to provide resistive torque and prevent complete immobilization of the control stick, allowing reversible operation and damping of pivoting movements.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If active electromechanical force feedback systems are used in control sticks, then haptic feedback and flight safety are improved, but system complexity and cost increase
Solution Approach 1:
The force feedback system is segmented into independent functional modules: an electromagnet generating unit, a movable armature, and a mechanical coupling system. This modular segmentation allows each component to perform a specific function, simplifying the overall system design while maintaining reliability through functional independence.
Solution Approach 2:
The patent replaces complex electromechanical transmission systems (motors, gears, clutches) with a direct electromechanical actuation system where an electromagnet directly moves an armature that couples to the control lever. This substitution eliminates intermediate mechanical components, reducing system complexity while preserving force feedback functionality.
2Reliability
If active force feedback motors are used, then haptic feedback is provided, but weight and power consumption increase
Solution Approach 1:
The system replaces heavy electromechanical motors with a lightweight electromagnet-armature actuation mechanism. The electromagnet generates magnetic force to move the armature, which directly couples to the control lever, eliminating the need for motors, gearboxes, and associated heavy mechanical components while maintaining force feedback capability.
Solution Approach 2:
The system changes the actuation mechanism from rotational motor output to linear electromagnetic force generation. The electromagnet converts electrical energy directly to linear motion of the armature, which then translates to rotational motion of the control lever through mechanical coupling, achieving weight reduction while preserving the essential haptic feedback function.
3Reliability
If mechanical backup channel is added to prevent free pivoting during faults, then reliability is improved, but device complexity increases
Solution Approach 1:
The mechanical backup function is merged with the normal force feedback mechanism. The same electromagnet, armature, and coupling components serve dual purposes: providing active force feedback during normal operation and providing passive mechanical constraint through the coupling geometry itself during faults, eliminating the need for separate backup components.
Solution Approach 2:
The coupling device between the armature and control lever is designed to automatically provide mechanical constraint in the event of electromagnet failure. The geometric configuration of the coupling mechanism itself serves as the backup constraint, requiring no additional components or active control systems to detect or respond to faults.
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 solution ensures continuous haptic feedback during faults, prevents complete free pivoting, and maintains aircraft control safety while being lighter, more compact, and reducing power consumption compared to existing systems.
Implementation Method 1
an electromagnet (5a), an actuator (6a) movable relative to the casing (4), the actuator (6a) comprising a magnetic material
Data Source
AI summary
The invention relates to a force application device for a control stick of an aircraft, said control stick comprising a control lever that is connected to at least one motor comprising a drive shaft that can be rotated about an axis, the force application device comprising: a first pin connected to the shaft, a housing, an electromagnet, a movable actuator comprising a magnetic material, a coupling device comprising an input gear connected to the housing and an output gear comprising a second pin, and means for clamping the first pin and the second pin which comprise a first tooth and a second tooth, said device having an operating configuration in which the electromagnet is active and the output gear is positioned at a distance from the input gear, and a blocking configuration in which the electromagnet is inactive and the gears are meshed.