Aircraft Control Allocation with Priority Weighting Under Actuator Saturation
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Solution Overview
Problem
Conventional flight control systems for over-actuated aircraft, such as tilt-rotor aircraft with electric propulsion, face challenges in control complexity and require computationally intensive real-time command calculations due to numerous execution possibilities, making pre-calculated look-up tables impractical.
Innovation Solution
A computer-implemented method for command prioritization in aircraft that analyzes pilot commands, determines characteristics related to airspeed and climb, assigns weights, calculates correction factors, and generates actuator commands based on priority, with saturation checks and optimization algorithms to ensure efficient and safe flight control.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If conventional look-up tables are used for flight control, then control implementation is simplified, but control accuracy and adaptability deteriorate due to the large number of alternative execution ways in over-actuated aircraft
Solution Approach 1:
The patent implements a dynamic control allocation system that continuously calculates optimal actuator commands based on current flight conditions, replacing static look-up tables. The system dynamically determines the best way to distribute control commands among multiple actuators in real-time, ensuring both ease of operation and control accuracy for over-actuated aircraft.
Solution Approach 2:
The system changes control parameters dynamically by adjusting actuator commands based on saturation checks and priority weighting. When certain actuators reach saturation limits, the system automatically redistributes control authority to other actuators, maintaining control accuracy while simplifying the operational complexity through automated parameter adjustment.
2Adaptability or versatility
If real-time command calculations and optimization are performed, then control adaptability improves, but computational complexity and processing time increase
Solution Approach 1:
The control system is segmented into hierarchical layers: an outer loop for high-level control decisions and an inner loop for real-time actuator command generation. This segmentation allows complex optimization problems to be broken down into manageable sub-tasks, reducing computational complexity while maintaining adaptability through coordinated operation of multiple control layers.
Solution Approach 2:
The system performs preliminary saturation checks and priority assignments before final command calculation. By pre-processing control demands and identifying potential saturation issues in advance, the system reduces the computational burden during critical real-time execution, balancing adaptability with computational efficiency.
3Productivity
If multiple actuators are used for enhanced maneuverability, then flight performance improves, but control system complexity increases making conventional methods impractical
Solution Approach 1:
The patent implements a universal control allocation framework that can handle multiple actuators and various flight conditions through a single integrated system. The control allocation matrix and priority weighting mechanism provide a multi-functional approach that adapts to different actuator configurations and flight regimes, improving flight performance while managing complexity through unified control logic.
Solution Approach 2:
The system incorporates feedback mechanisms that continuously monitor actuator saturation and performance, automatically adjusting command distribution among multiple actuators. This feedback-driven approach enables the system to manage the complexity of multiple actuators while maintaining enhanced flight performance through real-time optimization of control authority allocation.
Data Source
AI summary
Aspects of the present disclosure generally relate to systems and methods for flight control of aircrafts driven by electric propulsion systems and in other types of vehicles. In some embodiments, a computer-implemented method for command prioritization in an aircraft is disclosed. The method comprises receiving a pilot command, analyzing the pilot command to determine characteristics associated with the pilot command, wherein the characteristics to airspeed and climb of an aircraft, assigning weights to characteristics associated with the pilot command based on constraint data, determining priority of execution between airspeed and climb based on the weights assigned to the characteristics associated with the pilot command, calculating a correction factor to be applied to the characteristics associated with the pilot command based on determined priority and generating at least one actuator command to control the aircraft based on determined priority of execution.