Aircraft Flight Control for Real-Time Load Alleviation
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Aircrafts with electric propulsion systems face challenges in load management, particularly in reducing aerodynamic stresses and structural loads, which can impact fuel efficiency, passenger comfort, and safety.
Innovation Solution
A flight control system that uses sensors to determine flight conditions and calculates loads on the aircraft, allowing for the generation of effector commands to optimize flight configurations and alleviate loads on aircraft components.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If conventional aircraft adjust control surfaces to address aerodynamic stresses, then aerodynamic control is maintained, but load alleviation is insufficient for architecturally complex aircraft
Solution Approach 1:
The system continuously monitors flight conditions using sensors and adjusts effector commands in real-time based on calculated loads and optimized flight configurations, creating a closed-loop feedback mechanism that adapts to changing aerodynamic stresses and structural loads
Solution Approach 2:
The system dynamically changes flight parameters by determining optimized flight configurations that alter thrust distribution and control surface positions, thereby modifying aerodynamic forces and moments to alleviate structural loads on aircraft components
2Adaptability or versatility
If aircraft with distributed propulsion systems use more actuators to improve control, then flight maneuverability increases, but load management complexity increases
Solution Approach 1:
The flight control system integrates multiple actuators and effectors into a unified control architecture where each actuator can serve multiple functions depending on flight phase and load conditions, allowing coordinated thrust distribution across distributed propulsion systems to achieve both maneuverability and load alleviation
Solution Approach 2:
The system dynamically allocates control authority among multiple actuators based on real-time flight conditions and load calculations, continuously adjusting effector commands to optimize the balance between flight maneuverability and structural load management
3Adaptability or versatility
If aircraft operate through various maneuvers, then operational versatility is improved, but structural loads increase affecting safety
Solution Approach 1:
The system calculates anticipated structural loads based on planned maneuvers and pre-adjusts effector commands to counteract harmful aerodynamic stresses before they fully develop, reducing peak loads on aircraft components while maintaining maneuver execution
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, wherein the at least one flight condition includes at least a phase of flight, calculate at least one or more loads associated with the aircraft based on the determined at least one flight condition; determine an optimized flight configuration to alleviate loads on one or more components of the aircraft based on the received one or more signals and the calculated loads, generate one or more effector commands based on the optimized flight configuration; and actuate one or more aircraft effectors based on the one or more effector commands.