Electric Aircraft Propulsor Cyclic Control for Adverse-Force Compensation
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Propulsors on electric aircraft experience adverse forces such as gusts of wind and force imbalances due to differing lift generated by advancing and retreating blades, which existing solutions are insufficient to address.
Innovation Solution
A system and method for controlling a propulsor assembly using an electric motor, rotor, stator, propeller, cyclic control assembly, actuator, push rod, and flight controller to deflect propeller blades based on sensor data, allowing for compensation of unwanted forces and enhanced pilot control.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If existing propulsor control solutions are used, then the basic propulsion function is maintained, but the aircraft cannot effectively compensate for adverse forces such as gusts and blade force imbalances
Solution Approach 1:
The patent implements dynamic blade angle adjustment through a cyclic control assembly that can independently vary the pitch angle of each propeller blade during rotation. This dynamic control allows the system to adapt to changing aerodynamic conditions, gusts, and force imbalances by continuously adjusting blade angles to optimize performance and maintain stability under varying flight conditions.
Solution Approach 2:
The system incorporates sensors that detect adverse forces, gusts, and blade performance characteristics, feeding this information back to a flight controller. The flight controller processes this feedback and adjusts the cyclic control assembly accordingly to compensate for detected forces, creating a closed-loop control system that enhances reliability and adaptability in response to varying flight conditions.
2Object-affected harmful factors
If blade deflection control is implemented, then compensation for unwanted forces is improved, but the control system complexity increases
Solution Approach 1:
The cyclic control assembly segments the propeller blade control into independent adjustable elements, allowing each blade's angle to be controlled separately. This segmentation enables targeted compensation of adverse forces on specific blades while maintaining a manageable control architecture through modular, independent control units rather than requiring complete system redesign.
3Ease of operation
If cyclic control assembly is added, then pilot control and maneuverability are enhanced, but the device complexity and additional components increase
Solution Approach 1:
The cyclic control assembly is designed to perform multiple functions: it controls blade pitch angles, compensates for adverse forces, enhances pilot maneuverability, and maintains aircraft stability. By integrating these multiple control functions into a single assembly rather than requiring separate systems for each function, the patent reduces overall system complexity while enhancing operational capability.
Data Source
AI summary
A system and a method for controlling a propulsor assembly of an electric aircraft. The system may include an electric motor, wherein the electric motor may include a rotor and a stator, a propulsor driven by the electric motor configured to propel an electric aircraft. The propulsor may include a propeller. The propeller may include a blade. The system may include a cyclic control assembly configured to deflect the blade. The cyclic control assembly may include an actuator and a push rod mechanically connected to the actuator and the propulsor. The system may include a flight controller. The flight controller may be configured to receive sensor datum from at least a sensor communicatively connected to the electric aircraft, generate a deflection command as a function of the sensor datum and actuate the cyclic control assembly as a function of the deflection command.