Tiltrotor Flight Control Reconfiguration After Ruddervator Failure
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Solution Overview
Problem
Rotorcraft face limitations in forward speed due to aerodynamic drag from main rotor systems, and existing control systems lack efficient mechanisms for automatic transition of flight control authority in case of component failure, potentially leading to reduced operational capability.
Innovation Solution
A system and method that automatically transitions flight control authority from a failed flight control device, such as a ruddervator, to propulsion assemblies, using individualized equipment data and sensors to adjust control processes based on flight mode, allowing continued operation even with damaged components.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If flight control authority is manually managed during component failure, then pilot control and flexibility are maintained, but response time is delayed and operational reliability is reduced
Solution Approach 1:
The control system pre-configures backup control pathways and automatically activates them upon detecting component failure. The flight control computer monitors the health status of flight control surfaces and propulsion assemblies, and upon detecting a failure condition, automatically transitions control authority to available components without requiring pilot intervention for the transition process itself.
Solution Approach 2:
The flight control system performs self-diagnosis and self-reconfiguration. The flight control computer continuously monitors the operational status of flight control surfaces and propulsion assemblies, automatically detects failures, and reassigns control authority to functional components without external assistance, enabling the system to service itself during failure conditions.
2Reliability
If flight control authority transitions automatically upon component failure, then response time is reduced and reliability is improved, but control precision may be degraded
Solution Approach 1:
The flight control computer continuously monitors the performance and position of flight control surfaces and propulsion assemblies, comparing actual performance against expected performance parameters. This feedback mechanism allows the system to detect deviations indicating failure conditions and adjust control authority allocation dynamically to maintain optimal control precision during transition and operation with reduced capability.
Data Source
AI summary
In an embodiment, a method includes: adjusting a first flight control device of a rotorcraft to control flight around a first axis of the rotorcraft, the first flight control device exercising flight control authority around the first axis of the rotorcraft; detecting a failure of the first flight control device; transitioning at least a portion of the flight control authority around the first axis of the rotorcraft from the first flight control device to a second flight control device of the rotorcraft, the transitioning being performed automatically in response to detecting the failure of the first flight control device; and adjusting the second flight control device to control flight around the first axis of the rotorcraft, the second flight control device being adjusted by a first control process when the rotorcraft is in a first flight mode, the second flight control device being adjusted by a second control process when the rotorcraft is in a second flight mode.