Multi-Rotor Aircraft Control Redundancy Without Inter-Unit Communication
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Aircraft with multiple rotary wings face challenges in maintaining safety during flight when controller malfunctions, as existing systems rely on communication between controllers for redundancy, which can fail if communication breaks down, especially in complex airframes with multiple rotary wings.
Innovation Solution
The aircraft is configured with a network of first and second units, each equipped with sensors, processors, and communicators, allowing for independent operation and shared control laws to ensure continuous flight even if communication between units is disrupted, with processors and controllers capable of switching control sources and generating drive signals to maintain stability.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If multiple independent first units with autonomous control are implemented, then flight safety is improved during communication failures, but device complexity increases
Solution Approach 1:
Each first unit is designed as a universal control node capable of performing all control functions. The units share common control laws and can assume any control role, eliminating the need for specialized hardware for each unit and reducing overall system complexity through functional equivalence.
Solution Approach 2:
The first units are designed with homogeneous structures and capabilities, using the same control algorithms and communication protocols. This homogeneity simplifies system design, maintenance, and scalability while ensuring that any unit can seamlessly replace any other unit without requiring complex integration logic.
Data Source
Figure 1~2
Figure 3~4
Figure 5
AI summary
An aircraft (1) includes first units (100) each including a first sensor (110), a rotary wing (118), a driver (120), and a first drive controller (116). The first drive controller (116) is configured to generate a drive signal of the rotary wing (118) on the basis of a flying route of the aircraft (1) and a control law (f) based on a flying state detected by the first sensor (110), and output the drive signal to the driver (120) configured to drive the rotary wing (118). The control laws (f) of the respective first drive controllers (116) are equal to each other between the first units (100). The first drive controllers (116) are each configured to generate the drive signals (Ya to Yf) that correspond to all of the first units (100). The drivers (120) are each configured to drive the corresponding rotary wing (118) on the basis of corresponding one of the drive signals (Ya to Yf) that correspond to all of the first units (100) and that are generated by the first drive controllers (116).