Distributed Rotor Edge Computing for Multi-Rotor Flight Reliability
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Solution Overview
Problem
Multi-rotor vehicles face reliability and survivability issues due to their centrally-located flight controller, which increases weight and complexity by requiring redundant control and sensor communication across the vehicle.
Innovation Solution
Implementing distributed modular-based edge computing systems, each integrated with an electric motor and rotor, allowing for independent processing and control, with a primary and secondary system configuration for redundancy and communication with remote stations.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a centrally-located flight controller is used with triple redundant control and sensor communication, then flight worthiness and reliability are improved, but weight and device complexity increase
Solution Approach 1:
The patent divides the centralized flight control system into multiple distributed flight control computers, each responsible for specific control functions. This segmentation eliminates the single point of failure while reducing the complexity of centralized communication routing, as each computer handles local control decisions independently.
Solution Approach 2:
The patent extracts the flight control functionality from a single centralized controller and distributes it across multiple independent computers. This extraction allows each computer to operate autonomously, reducing the need for complex inter-communication routing while maintaining triple redundancy for flight worthiness.
2Reliability
If triple redundant control and sensor communication are implemented through a central flight controller, then reliability is improved, but weight increases
Solution Approach 1:
By segmenting the control system into distributed flight control computers, the patent eliminates the need for extensive communication infrastructure required by centralized redundancy. Each computer operates independently with local sensor processing, reducing the weight of communication buses and routing hardware while maintaining triple redundancy.
Solution Approach 2:
The patent implements local processing of sensor data and control decisions at each flight control computer, rather than centralizing all processing. This local quality approach reduces the weight of communication infrastructure by minimizing data transmission requirements while maintaining system reliability through distributed redundancy.
3Ease of operation
If control forces and actuator communication are routed from a central flight controller to each actuator, then centralized control is achieved, but device complexity and weight increase
Solution Approach 1:
The patent segments the control architecture so that each flight control computer independently manages specific actuators and control forces. This segmentation eliminates the need for complex centralized routing of control forces, as each computer directly controls its assigned actuators without requiring intermediate routing through a central hub.
Solution Approach 2:
The patent combines the flight control computer and motor controller into an integrated unit, eliminating the need for separate communication routing between centralized controllers and actuators. This merging simplifies the system by directly coupling control logic with actuator control, reducing communication infrastructure complexity.
4Ease of operation
If control forces and actuator communication are routed from a central flight controller, then centralized control is achieved, but weight increases
Solution Approach 1:
The patent merges the flight control computer and motor controller into an integrated unit, eliminating the weight of separate communication infrastructure required for centralized control. This integration directly couples control logic with actuator control, removing the need for heavy communication buses and routing hardware while maintaining ease of operation.
Data Source
AI summary
A multi-rotor vehicle includes a plurality of electric motors and edge computing systems (ECSs). The electric motors are operatively coupled to respective rotors, and cause the respective rotors to rotate relative to the airframe. The ECSs are independent, distinct and distributed to the electric motors, each operatively coupled to a respective electric motor and thereby a respective rotor. Each ECS is configured to acquire and process sensor data for the respective rotor to determine rotor status information, and execute motor commands to control the respective electric motor and thereby the respective rotor. Each ECS is configured as an integrated flight computer and motor controller.