Redundant Aircraft Flight Control Across Segmented Low-Voltage Buses
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Solution Overview
Problem
Aircraft components may malfunction during flight, compromising safety, and existing systems do not adequately address the impact of failures in redundant low voltage buses on aircraft operability.
Innovation Solution
A redundant flight control system with multiple control surfaces and low voltage buses, where a failure in one bus does not affect the aircraft's operability, utilizing actuators, battery packs, and sensors to ensure continuous flight control.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If redundant low voltage buses are implemented, then reliability is improved, but device complexity increases
Solution Approach 1:
The electrical power distribution system is segmented into multiple independent low voltage buses (e.g., bus 112A, 112B, 112C) that can operate autonomously. Each bus serves specific flight components, creating isolated segments that prevent failure propagation. This segmentation allows the system to maintain reliability through redundancy while managing complexity by organizing buses into distinct, manageable groups with dedicated functions.
2Reliability
If multiple redundant control surfaces are used, then reliability is improved, but weight increases
Solution Approach 1:
The redundant control surfaces (e.g., ailerons 106A-106D, elevators 108A-108D, rudders 110A-110D) are designed to perform identical flight control functions across different aircraft configurations. Each control surface can serve multiple operational modes and can be substituted based on failure conditions, maintaining universal functionality. This multi-functionality approach allows the system to achieve reliability through redundancy while optimizing weight by using standardized, interchangeable components rather than specialized redundant elements.
Data Source
AI summary
A system and method for flight control of an aircraft, the flight control system including a plurality of flight components coupled to an aircraft, wherein the plurality of flight components includes a plurality of redundant control surfaces, a plurality of redundant low voltage buses communicatively connected to the plurality of flight components, wherein a failure in a redundant low voltage bus of the plurality of redundant low voltage busses does not impact the operability of the aircraft.