eVTOL Flight Control Bus Layout for Redundant Propeller Control
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Solution Overview
Problem
Conventional aircraft driven by electric propulsion systems face challenges in frequent use, noise reduction, vibration management, and safety in densely populated areas, with a need for efficient energy use and redundancy to avoid single points of failure.
Innovation Solution
The design incorporates a distributed electric propulsion system with tiltable propellers, a flight control computer that provides control signals via a single electrical bus for both lift and tilt propellers, and a configuration that allows for vertical and conventional takeoff and landing, optimizing energy density and reducing weight and noise.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a conventional electrical bus configuration is used where each wing has its own dedicated electrical bus, then system redundancy and safety are improved, but device complexity and weight increase
Solution Approach 1:
The patent combines the electrical bus system into a single shared bus that serves both wings and all propellers (both lift and tilt propellers). This merging of previously separate electrical systems reduces the overall complexity of the electrical architecture while maintaining the ability to independently control each propeller through individual control signals from the flight control computer.
Solution Approach 2:
The single electrical bus is designed to universally serve multiple functions: it provides power to both lift propellers and tilt propellers on opposite sides of the fuselage, replacing the need for separate dedicated buses for each wing and each propeller type. This multi-functional approach reduces redundancy in the electrical system architecture.
2Reliability
If more electrical buses and redundant systems are implemented, then safety and fault tolerance are improved, but weight and energy consumption increase
Solution Approach 1:
The patent merges multiple separate electrical bus systems into a single shared electrical bus that distributes power to all propellers. This consolidation eliminates redundant wiring, connectors, and electrical components that would otherwise be required for separate buses, thereby reducing overall system weight while maintaining operational safety through the flight control computer's ability to manage power distribution.
3Measurement precision
If separate control systems are used for lift propellers and tilt propellers, then control precision is improved, but device complexity increases
Solution Approach 1:
The flight control computer is designed as a universal control system that manages both lift propellers and tilt propellers through a single integrated architecture. It generates appropriate control signals for each propeller type based on flight conditions, eliminating the need for separate dedicated control systems while maintaining the precision required for different propeller functions.
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
This configuration enables efficient, safe, and quiet operation of electric aircraft with reduced noise and vibration, capable of frequent use and safe operation in densely populated areas, while minimizing the risk of single points of failure.
Implementation Method 1
a plurality of tilt propellor actuators that tilt propellers between vertical lift and forward propulsion configurations
Implementation Method 2
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 and one of the tilt propellers via the same electrical bus
Implementation Method 3
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
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.