Electric Propulsion Flight Control for Fast Thrust Response
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Solution Overview
Problem
Aircrafts using electric propulsion systems face challenges in achieving fast engine response, leading to decreased stability and safety due to low bandwidth in propeller speed changes, making them slow to reject exogenous disturbances.
Innovation Solution
The implementation of a flight control system that dynamically varies torque commands to electric propulsion units based on aircraft conditions, utilizing sensors and a flight control computer to stabilize and maneuver the aircraft, with a propulsion unit dynamics compensation protection and stabilization function to achieve fast, predictable responses.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If propeller speed is changed to control aircraft dynamics, then thrust control is achieved, but the response bandwidth is too low causing slow rejection of disturbances
Solution Approach 1:
The patent replaces mechanical propeller pitch control systems with electric propulsion units that use electrical torque control. The electric motor directly controls propeller speed through electrical commands, eliminating mechanical linkages and enabling faster response bandwidth while maintaining thrust control capability.
Solution Approach 2:
The patent changes the control parameter from mechanical pitch angle to electrical torque, allowing for much faster adjustment rates. The electric propulsion system can modulate torque rapidly through electrical signals, achieving high bandwidth propeller speed changes that improve disturbance rejection and aircraft stability.
2Reliability
If fast engine response is achieved through dynamic torque variation, then aircraft stability improves, but control system complexity increases
Solution Approach 1:
The flight control computer performs multiple functions: it controls propeller speed, manages torque commands to electric propulsion units, monitors aircraft conditions through sensors, and coordinates overall aircraft dynamics. This multi-functionality consolidates control complexity into a single integrated system rather than requiring separate specialized systems.
Solution Approach 2:
The electric propulsion units inherently provide fast response characteristics through their electrical control architecture. The system leverages the natural properties of electric motors to achieve rapid torque variation and propeller speed adjustment, reducing the need for additional complex mechanical response-enhancement mechanisms.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
Enhances aircraft stability and safety by enabling fast thrust response and compensation for errors, disturbances, and changing conditions, ensuring stable flight dynamics.
Implementation Method 1
one or more electric propulsion units; wherein the one or more electric propulsion units are configured to generate thrust
Implementation Method 2
one or more sensors configured to measure one or more aircraft conditions
Implementation Method 3
at least one flight control computer configured to dynamically vary one or more torque commands to the one or more electric propulsion units
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, an aircraft is disclosed, comprising: at least one electric propulsion unit; at least one sensor configured to measure at least one aircraft condition; and at least one flight control computer configured to dynamically vary at least one torque command to the at least one electric propulsion unit based at least on the at least one aircraft condition; wherein the at least one electric propulsion unit is configured to generate thrust based on the at least one dynamically varied torque command.