Tiltrotor Flight Control Reconfiguration After Tail Assembly Failure
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Solution Overview
Problem
Rotorcraft systems face challenges in efficiently transitioning flight control authority from damaged components to backup systems during flight, particularly in maintaining stable flight characteristics and reducing pilot workload, especially when the tail assembly is compromised.
Innovation Solution
Implementing a system that automatically transitions flight control authority from the tail assembly to the propulsion assemblies and proprotor assemblies using individualized equipment data and health monitoring systems, allowing for seamless control adjustments and continued operation even with damaged components.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If flight control authority is manually transferred from damaged components to backup systems, then pilot workload increases and response time is delayed, but system reliability is maintained through backup systems
Solution Approach 1:
The flight control system automatically detects component failures and transfers control authority to backup systems without pilot intervention. The system monitors its own health status and autonomously reconfigures control pathways, eliminating the need for manual pilot actions during failure conditions.
Solution Approach 2:
The system continuously monitors the health status of flight control components and uses this feedback to automatically determine when and how to transfer control authority. Health monitoring systems provide real-time data on component status, enabling the flight control computer to make informed decisions about control reconfiguration.
2Ease of operation
If automatic transition of flight control authority is implemented, then pilot workload is reduced and response time is improved, but system complexity increases
Solution Approach 1:
The health monitoring system and flight control system are integrated into a unified architecture. The flight control computer receives health status data and automatically performs control authority transitions, combining multiple functions into a single coordinated system that reduces overall complexity despite adding automatic capabilities.
Solution Approach 2:
The flight control computer serves multiple functions: normal flight control, health status monitoring, failure detection, and automatic control authority transition. This multi-functional approach eliminates the need for separate dedicated systems for each function, reducing overall system complexity while maintaining automatic transition capabilities.
3Duration of action of moving object
If control authority is transferred during flight, then continued operation is enabled with damaged components, but transient conditions and instability may occur
Solution Approach 1:
The system prepares backup control pathways in advance and pre-configures alternative control authority routes. When a failure is detected, the transition to backup systems occurs smoothly because the alternative pathways are already established and ready, minimizing transient conditions and maintaining flight stability.
Solution Approach 2:
The system implements gradual control authority transfer rather than abrupt switching. By transitioning control smoothly over time and using intermediate transition states, the system cushions the impact of the failure and prevents sudden instability or transient conditions that would occur with immediate hard switching.
Data Source
Figure 1A~1B
Figure 2
Figure 3A~3B
AI summary
In an embodiment, a method includes: adjusting (902) a first flight control device of a rotorcraft (10) to control flight around a first axis of the rotorcraft (10), the first flight control device exercising flight control authority around the first axis of the rotorcraft (10); detecting (904) a failure of the first flight control device; transitioning (906) at least a portion of the flight control authority around the first axis of the rotorcraft (10) from the first flight control device to a second flight control device of the rotorcraft (10), the transitioning (906) being performed automatically in response to detecting the failure of the first flight control device; and adjusting (908) the second flight control device to control flight around the first axis of the rotorcraft (10), the second flight control device being adjusted by a first control process when the rotorcraft (10) is in a first flight mode, the second flight control device being adjusted by a second control process when the rotorcraft (10) is in a second flight mode.