Isolated Aircraft Power Circuits for Balanced Propulsion Failure
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Solution Overview
Problem
Existing power distribution systems for electrically powered aircraft lack sufficient redundancy and stability in the event of failure, which can lead to unbalanced forces and instability in flight.
Innovation Solution
A power distribution circuit with multiple isolated circuits, each coupling a battery to two or more electric propulsion systems positioned to apply balanced forces relative to the aircraft's center of gravity, along with redundant controllers and windings, and fuses for electrical coupling.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If multiple isolated power distribution circuits are used to provide redundancy, then reliability is improved, but device complexity increases
Solution Approach 1:
The power distribution system is divided into multiple isolated power distribution circuits, where each circuit independently couples a battery to two or more electric propulsion systems. This segmentation provides redundancy such that if one circuit fails, other circuits continue to supply power to propulsion systems, thereby improving reliability without requiring a completely redundant system.
Solution Approach 2:
Each isolated power distribution circuit is designed to be multi-functional, capable of coupling to multiple electric propulsion systems simultaneously. This universality allows a single circuit to serve multiple functions, reducing the overall number of components needed while maintaining redundancy, thus improving reliability without proportionally increasing complexity.
2Stability of the object's composition
If propulsion systems are positioned to apply balanced forces relative to center of gravity, then stability is improved, but device complexity increases
Solution Approach 1:
The electric propulsion systems are positioned asymmetrically relative to the aircraft body, but their force application points are strategically located to create balanced moments about the center of gravity. This asymmetric positioning with balanced force application provides stability while allowing for more flexible and potentially simpler structural integration compared to perfectly symmetric arrangements.
Solution Approach 2:
The positioning of propulsion systems is designed so that forces applied by motors on opposite sides of the center of gravity create counterbalancing moments. This counterweight principle ensures that when motors operate, they generate balanced forces that prevent unwanted rotation or instability, maintaining aircraft stability without requiring additional active control mechanisms.
3Reliability
If redundant controllers and windings are implemented, then reliability is improved, but device complexity increases
Solution Approach 1:
Redundant controllers and windings are implemented as simplified copies of the primary components. Each propulsion system has a primary controller and a redundant controller, along with primary and redundant windings. These redundant components are designed to be functional copies that can take over in case of failure, providing reliability through duplication without requiring complex adaptive control systems.
Solution Approach 2:
The redundant controllers and windings are pre-configured and positioned before any failure occurs. The system is designed with these redundant components ready to activate immediately upon detection of a primary component failure, eliminating the need for complex real-time decision-making or reconfiguration during emergency situations, thus improving reliability without proportionally increasing operational complexity.
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
The system ensures stable operation by maintaining balanced forces even in the event of battery failure or other power distribution issues, preventing rotation and ensuring safe changes in altitude or speed.
Implementation Method 1
at least one electric propulsion system of the plurality of electric propulsion systems includes a primary controller coupled to a primary winding and a redundant controller coupled to a redundant winding
Data Source
AI summary
A power distribution circuit for an electrically powered aircraft includes a plurality of batteries and a plurality of electric propulsion systems. A plurality of isolated power distribution circuits each couple a battery of the plurality of batteries to two or more electric propulsion systems. The plurality of electric propulsion systems are positioned on the aircraft to apply balanced forces to the aircraft such that in the event of a failure, the aircraft remains stable and only experiences a loss in altitude or speed.