Geometry-Based Flight Control for Dynamic Actuator Allocation
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing flight control systems struggle to determine the optimal combination of actuators and associated parameters to achieve desired aircraft motion, especially in dynamic conditions and for aircraft with varying geometry.
Innovation Solution
A geometry-based flight control system that receives inputs for desired forces and moments, computes the optimal mix of actuators and parameters, and accounts for dynamically varying actuator effectiveness and aircraft geometry, such as tiltwing angles.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If pre-computed offline combinations of actuators are used to respond to inceptor inputs, then the control system can be simplified, but it cannot determine every required actuator combination under all possible conditions and circumstances
Solution Approach 1:
The patent implements a dynamic geometry-based flight control system that continuously computes actuator commands based on real-time aircraft state and geometry. Unlike static pre-computed tables, the system adapts to changing flight conditions by dynamically determining optimal actuator combinations, resolving the contradiction between system simplicity and adaptability.
Solution Approach 2:
The system changes control parameters dynamically based on aircraft geometry and flight conditions. By using geometry-based computations that adapt to varying aircraft configurations (such as variable sweep wings or movable control surfaces), the system achieves versatility without requiring complex pre-computed lookup tables for every possible condition.
2Measurement precision
If the flight control system accounts for dynamically varying actuator effectiveness and aircraft geometry, then the control accuracy is improved, but the computational complexity increases
Solution Approach 1:
The system performs preliminary computations of geometry-based control parameters and stores them for rapid retrieval during flight. By pre-calculating geometry relationships and actuator effectiveness maps for various flight conditions, the system achieves high control accuracy without requiring complex real-time computations, thus balancing accuracy with computational feasibility.
Solution Approach 2:
The patent replaces complex mechanical control systems with geometry-based computational methods. By using mathematical models that relate aircraft geometry directly to control commands, the system achieves high precision control while reducing the need for complex mechanical sensing and actuation systems, thereby managing computational complexity.
Data Source
AI summary
A geometry-based flight control system is disclosed. In various embodiments, a set of inceptor inputs associated with a requested set of forces and moments to be applied to the aircraft is received. An optimal mix of actuators and associated actuator parameters to achieve to an extent practical the requested forces and moments is computed, including by taking into consideration dynamically varying effectiveness of one or more actuators based on a current dynamic state of the aircraft. An output comprising for each actuator in the optimal mix a corresponding set of one or more control signals associated with the set of actuator parameters computed for that actuator is provided.