eVTOL Flight Control Bus Layout for Distributed Propulsion Redundancy
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Solution Overview
Problem
Conventional aircraft driven by electric propulsion systems face challenges in frequent, short-duration flights over densely populated areas, requiring components that minimize noise, vibration, and heat generation while ensuring safety and efficiency, with a need for distributed propulsion systems to avoid single points of failure and enable vertical takeoff and landing in restricted spaces.
Innovation Solution
The design incorporates a distributed electric propulsion system with tiltable propellers, a flight control computer, and electrical buses to manage propeller operations, optimizing energy density and reducing weight and noise, while ensuring redundancy to prevent single-point failures and enabling both vertical and conventional takeoff and landing capabilities.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a distributed propulsion system with multiple propellers is used, then reliability is improved by avoiding single points of failure, but device complexity increases due to multiple actuators and control systems
Solution Approach 1:
The propulsion system is divided into multiple independent propeller units (tilt propellers and lift propellers) distributed across the aircraft structure. Each propeller can be independently controlled and failed individually without compromising the entire system, thereby improving reliability through segmentation while managing complexity through modular design
Solution Approach 2:
The tilt propellers are equipped with actuators that enable dynamic reconfiguration between horizontal and vertical orientations. This dynamic capability allows the same hardware to serve multiple functions (forward propulsion and vertical lift), improving reliability by providing operational flexibility without proportionally increasing device complexity
2Adaptability or versatility
If tilt propellers with actuators are used for reconfiguration, then adaptability is improved by enabling vertical takeoff and landing, but weight increases due to additional actuators and structural components
Solution Approach 1:
The tilt propellers serve dual functions: providing forward propulsion when in horizontal orientation and providing vertical lift when tilted vertically. This multi-functionality enables the aircraft to perform both conventional flight and vertical takeoff/landing operations using the same propeller units, improving adaptability without requiring separate dedicated systems that would increase weight
Solution Approach 2:
The system uses lift propellers positioned aft of the wings that remain fixed in vertical orientation to provide dedicated lift capability, while tilt propellers provide partial lift and forward thrust. This distribution of functions allows the aircraft to achieve vertical flight capability without requiring all propellers to be heavy tilting units, thereby managing overall weight while maintaining adaptability
3Object-generated harmful factors
If electric propulsion systems are used to minimize noise and vibration, then object-generated harmful factors are reduced, but power density decreases compared to conventional propulsion systems
Solution Approach 1:
The propulsion power is distributed across multiple independent electric motor units rather than concentrated in a single engine. This segmentation allows each motor to be optimized for efficient electric operation at lower power levels, reducing noise and vibration while the collective system provides sufficient total power for the aircraft
Solution Approach 2:
The system operates electric motors at optimized power parameters that maximize efficiency and minimize noise/vibration generation. By distributing the total power requirement across multiple units and operating each at optimal points, the system achieves acceptable power density while maintaining the noise and vibration advantages of electric propulsion
Data Source
AI summary
Aspects of this present disclosure relate to flight control of electric aircrafts and other vehicles. In one embodiment, an aircraft is disclosed comprising: a fuselage; two wings; a plurality of lift propellers, the lift propellers disposed aft of the wings during forward flight; plurality of tilt propellers that are tiltable between vertical lift and forward propulsion configurations, the tilt propellers disposed forward of the wings during forward flight; a plurality of tilt propellor actuators that tilt propellers between vertical lift and forward propulsion configurations, the tilt propellor actuators on opposite sides of the fuselage; and a plurality of electrical buses coupled to a flight control computer; wherein the flight control computer is configured to provide control signals for at least one of the lift propellers mounted to one of the wings and one of the tilt propellers mounted to the other wing via the same electrical bus.