Electric Aircraft Propulsor Cyclic Control Assembly
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Solution Overview
Problem
Propulsors on electric aircraft experience adverse forces during flight, such as gusts of wind and force imbalances, which existing solutions are insufficient to address effectively.
Innovation Solution
A propulsor assembly for electric aircraft that includes an electric motor with a stator and rotor, a propulsor mechanically connected to the rotor, and a cyclic control assembly with an electric actuator and push rod. The cyclic control assembly adjusts the blade angle of the propulsor to compensate for unwanted forces.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If existing control solutions are used, then the propulsor assembly structure is simple, but the ability to compensate for adverse forces (wind gusts, force imbalances) is insufficient
Solution Approach 1:
The patent implements dynamic blade angle adjustment through a cyclic control assembly that actively modifies propulsor blade angles in response to adverse forces. The control assembly includes actuators that dynamically change blade pitch angles to compensate for wind gusts and force imbalances, transforming a static propulsor system into a dynamically adaptive one that maintains optimal performance under varying flight conditions
Solution Approach 2:
The cyclic control assembly incorporates feedback mechanisms that monitor propulsor performance and adverse forces, then automatically adjust blade angles accordingly. The system continuously detects force imbalances and wind gust effects, processes this information, and implements corrective blade angle changes to maintain stable propulsor operation, creating a closed-loop control system that enhances reliability
2Stability of the object's composition
If blade angle adjustment is implemented, then stability and control are enhanced, but the control mechanism complexity increases
Solution Approach 1:
The control assembly is segmented into distinct functional components including multiple actuators, blade pitch control mechanisms, and structural elements distributed throughout the propulsor assembly. This segmentation allows each component to perform its specific function independently while contributing to overall stability, making the complex system more manageable and maintainable
Solution Approach 2:
The cyclic control assembly is designed to perform multiple functions: it adjusts blade angles for stability, compensates for various types of adverse forces (wind gusts, force imbalances), and maintains optimal propulsor performance across different flight conditions. This multi-functionality reduces the need for separate specialized systems, managing complexity through consolidated design
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
The proposed solution effectively compensates for adverse forces experienced by propulsors during flight, enhancing the stability and control of electric aircraft.
Implementation Method 1
The cyclic control assembly includes an actuator, wherein the actuator is an electric actuator
Implementation Method 2
a push rod, wherein the push rod is mechanically connected to the actuator and the propulsor, the push rod is configured to increase a blade angle of the propulsor when the push rod is displaced in a first direction
Data Source
AI summary
A propulsor assembly of an electric aircraft is described. The propulsor assembly includes an electric motor, where the electric motor includes a stator and a rotor. The assembly further includes a propulsor mechanically connected to the rotor of the electric motor. The assembly also includes a cyclic control assembly including an electric actuator and a push rod, wherein the push rod is mechanically connected to the actuator and the propulsor, the push rod is configured to increase a blade angle of the propulsor when the push rod is displaced in a first direction, and the push rod is configured to decrease the blade angle of the propulsor when the push rod is displaced in a second direction.