Tiltrotor Flight Control Authority Transfer After Device Failure
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Solution Overview
Problem
Rotorcrafts face limitations in forward speed due to aerodynamic drag from main rotor systems, and existing control systems lack efficient mechanisms for transitioning flight control authority in case of component failure, particularly during mode changes from vertical to forward flight.
Innovation Solution
A system and method that automatically transitions flight control authority from a primary flight control device, such as a ruddervator, to a propulsion assembly in response to failure detection, using individualized equipment data and control processes tailored for vertical and forward flight modes, allowing continued operation even with damaged components.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If flight control authority is concentrated in a single primary flight control device, then control precision is improved, but system reliability deteriorates due to single point of failure
Solution Approach 1:
The patent segments flight control authority across multiple independent devices (primary flight control device, secondary flight control devices, and propulsion assemblies). Each device can independently exercise control authority, allowing the system to maintain functionality even when one device fails. The flight control computer dynamically distributes control commands across these segmented components based on their operational status.
Solution Approach 2:
The patent implements preliminary action by pre-configuring multiple flight control devices and propulsion assemblies with the capability to exercise flight control authority. The system proactively prepares backup control paths before failures occur, so that when a primary device fails, the transition to secondary devices or propulsion assemblies can happen immediately without delay.
2Reliability
If flight control authority is automatically transitioned to backup devices upon failure detection, then system reliability is improved, but device complexity increases
Solution Approach 1:
The patent applies universality by designing propulsion assemblies that serve dual functions: primary propulsion and backup flight control. The same propulsion assemblies that provide thrust also can exercise flight control authority when primary flight control devices fail. This multi-functionality reduces the need for entirely separate backup systems, thereby limiting the increase in complexity.
Solution Approach 2:
The flight control system implements self-service through automatic failure detection and autonomous authority transition. The system continuously monitors the operational status of flight control devices and automatically redistributes control authority without requiring pilot intervention. This automation manages the complexity by making the system self-regulating rather than requiring complex manual override procedures.
3Measurement precision
If multiple flight control devices are configured with individualized equipment data, then detection precision is improved, but data management complexity increases
Solution Approach 1:
The patent implements feedback by continuously comparing actual performance measurements from flight control devices against expected performance derived from individualized equipment data. The flight control computer receives real-time data from sensors and actuators, compares it to the stored individualized parameters (such as actuator characteristics, sensor calibration data, and performance thresholds), and automatically detects deviations indicating potential failures. This closed-loop feedback system enables precise failure detection while managing data complexity through automated comparison algorithms.
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.