Aircraft Flight Control for Predictive Load Alleviation
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Solution Overview
Problem
Conventional aircraft, particularly those with electric propulsion systems, face challenges in managing dynamic aerodynamic loads during various flight phases, which affect fuel efficiency, passenger comfort, structural integrity, and safety, especially in complex architectures like eVTOLs with distributed propulsion systems.
Innovation Solution
A flight control system that determines optimized flight configurations based on sensor data to alleviate loads by generating effector commands for aircraft components, actively managing aerodynamic forces to minimize structural loads and improve stability.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If conventional aircraft adjust control surfaces to address aerodynamic stresses, then structural integrity is maintained, but fuel efficiency deteriorates due to increased drag and energy consumption
Solution Approach 1:
The patent implements dynamic load alleviation by continuously adjusting control surfaces based on real-time flight conditions and predicted loads. The system dynamically optimizes the balance between structural integrity and fuel efficiency by adapting control surface positions to minimize drag while maintaining necessary structural strength throughout the flight phases.
Solution Approach 2:
The system performs preliminary load prediction using flight phase detection and load estimation algorithms before actual high-load maneuvers occur. By anticipating upcoming loads based on current flight conditions and trajectory, the system can proactively adjust control surfaces to reduce peak loads and associated drag, thereby improving fuel efficiency while maintaining structural integrity.
2Measurement precision
If aircraft with distributed propulsion systems use more actuators to manage complex flight phases, then flight control precision is improved, but device complexity increases
Solution Approach 1:
The patent implements a unified flight control system that integrates multiple functions into a single architecture. The control system simultaneously manages thrust distribution across multiple propellers, adjusts control surfaces, detects flight phases, and predicts loads all through one coordinated system, reducing overall device complexity while maintaining high flight control precision for eVTOL operations.
Solution Approach 2:
The system merges several independent subsystems (thrust control, control surface actuation, flight phase detection, and load prediction) into an integrated flight control architecture. This consolidation reduces the number of separate control loops and simplifies the overall system while preserving the precision benefits of having multiple actuators for distributed propulsion management.
3Speed
If aircraft undergo frequent maneuvers to respond to flight conditions, then responsiveness is improved, but structural loads increase compromising safety
Solution Approach 1:
The system applies preliminary anti-action by predicting upcoming structural loads based on detected flight phases and anticipated maneuvers. Before high-load maneuvers occur, the system pre-adjusts control surfaces and thrust distribution to counteract predicted peak loads, thereby maintaining rapid responsiveness to flight conditions while preventing excessive structural stresses that would compromise safety.
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 flight control system of an aircraft is disclosed, configured to receive one or more signals to control movement of the aircraft, determine at least one flight condition of the aircraft, calculate at least one or more loads associated with the aircraft based on the determined at least one flight condition; determine a flight configuration to alleviate loads on one or more components of the aircraft based on the received one or more signals and the calculated one or more loads by predicting a distribution of loads associated with the aircraft, generate one or more effector commands based on the flight configuration; and actuate one or more aircraft effectors based on the one or more effector commands.