Distributed Flap Actuation for Non-Responsive Component Isolation
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Solution Overview
Problem
In aircraft actuation systems, when motors operating control surfaces at transonic speeds turn at different rates due to non-responsive components, it leads to flap skew, necessitating the disabling of entire flap systems to prevent damage, resulting in increased approach speeds and potential diversions.
Innovation Solution
A distributed aircraft actuation system with an actuator system manager that monitors control surfaces, detects non-responsive components, and deactivates affected sets while keeping others active, reducing undesired aerodynamic effects and maintaining system functionality.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the entire flap system is disabled to prevent damage from non-responsive components, then aircraft safety is improved, but approach speeds increase and diversions may be required
Solution Approach 1:
The patent divides the flap system into independent controllable segments (first set of control surfaces and second set of control surfaces). When a non-responsive component is detected in one segment, only that specific segment is deactivated while other segments remain operational. This segmentation allows partial system operation rather than complete shutdown, maintaining lower approach speeds while ensuring safety by isolating the problematic component.
2Productivity
If motors are monitored and affected sets are selectively deactivated, then system functionality is maintained, but device complexity increases
Solution Approach 1:
The patent implements a feedback mechanism where the actuator system manager continuously monitors motor performance and control surface responsiveness. When a non-responsive component is detected through this feedback loop, the system automatically deactivates only the affected set of control surfaces. This feedback-based approach maintains system functionality through intelligent monitoring while managing complexity by focusing surveillance only on critical operational parameters rather than comprehensive system oversight.
3Strength
If complete flap system disablement is used to prevent damage, then component protection is improved, but aerodynamic performance deteriorates
Solution Approach 1:
The patent extracts and isolates the problematic non-responsive component or set of control surfaces from the overall flap system. By deactivating only the affected set while keeping other sets operational, the system removes the harmful element (non-responsive component causing potential damage) while preserving the functional aerodynamic surfaces. This selective extraction protects components from damage while maintaining optimal aerodynamic performance by keeping working flaps active.
Data Source
AI summary
Methods, apparatus, and articles of manufacture for a distributed aircraft actuation system are disclosed. An example apparatus includes a non-responsive component detector to determine a position difference between a first position of a first control surface of an aircraft and a second position of a second control surface of the aircraft, the first position lagging the second position, and a command generator, in response to determining that the position difference satisfies a threshold, the command generator is to cease movement of the second control surface at the second position, attempt to move the first control surface to the second position, and cease movement of the first control surface when moved to the second position.