Aircraft Flight Control Blending Across Copter and Jet Modes
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Solution Overview
Problem
Existing aircraft control systems face challenges in managing conflicts between different actuators during mode transitions, leading to 'fight of control' issues, which affect comfort and efficiency, especially when switching between 'copter mode' and 'jet mode'.
Innovation Solution
A method of controlling aircraft by dynamically adjusting the maximum and minimum limit values of control volumes defined by parameter ranges for each mode, allowing for smooth and continuous transitions between control laws, enabling multiple control methods to be active simultaneously without discrete switching.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If discrete switching between control laws is used for mode transitions, then control clarity is improved, but discontinuous and potentially dangerous behavior occurs
Solution Approach 1:
The patent applies dynamics by making the control volume limits adjustable and mode-dependent. Different control volumes are defined for different flight modes (e.g., landing vs. take-off), and the system dynamically switches between these predefined control volumes based on the current flight mode, enabling continuous and safe control transitions without discrete jumps
Solution Approach 2:
The patent changes the parameter ranges of control volumes based on flight mode. Each flight mode has associated maximum and minimum limit values for control parameters (such as thrust, speed, altitude rates). When transitioning between modes, the system adjusts these parameter limits smoothly, preventing discontinuous behavior while maintaining control clarity through mode-appropriate constraints
2Adaptability or versatility
If control parameter ranges are expanded for mode transition, then adaptability is improved, but control precision is reduced
Solution Approach 1:
The system dynamically adjusts control volume limits based on the current flight mode. During mode transitions, the control volumes are expanded to allow greater parameter ranges for flexibility. Once the transition is complete and the new mode is established, the control volumes are reduced to tighter ranges appropriate for that mode, thereby maintaining precision while enabling adaptability during transitions
Solution Approach 2:
The patent implements periodic adjustment of control volume limits synchronized with flight mode transitions. The control system periodically evaluates the current mode and adjusts the parameter ranges accordingly - expanding ranges during transition periods and maintaining reduced ranges during stable mode operation, creating a rhythmic pattern of adaptability and precision
Data Source
AI summary
A method of controlling an aircraft having multiple configurations is provided, wherein each configuration is controlled by a different control law implemented by a flight control device and transition from one configuration to another configuration is achieved by gradually blending out a control law for one configuration and by gradually increasing an impact of a control law for another configuration in the flight control device based on an estimated flight condition of the aircraft by dynamically adjusting, in the flight control device, respective maximum and minimum limit values of control volumes, which control volumes are defined by parameter ranges of control parameters in connection with a corresponding control law for the one configuration and for the other configuration, respectively.