Aircraft Power Restriction System for Circuit Protection Avoidance
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Electric aircraft face challenges in preventing the engagement of circuit protection devices, which can lead to disconnection of critical power sources during flight, causing safety and functionality issues due to varying levels of efficiency, weight, and external control requirements.
Innovation Solution
A system and method that utilize sensors and an aircraft controller to monitor electrical parameters and reduce power output to loads when approaching a threshold, preventing the engagement of circuit protection devices by calculating and implementing a power reduction, thereby ensuring continuous operation of electrical circuits during flight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If multiple loads operate simultaneously on an electric aircraft, then the aircraft can perform various functions, but the stress on the energy source increases and may cause circuit protection devices to engage
Solution Approach 1:
The controller proactively monitors electrical parameters and detects when loads are approaching the circuit protection threshold before the circuit protection device actually engages. By taking preliminary action to reduce power to specific loads, the system prevents circuit protection engagement while maintaining overall system functionality.
Solution Approach 2:
The system dynamically adjusts power allocation to loads based on real-time monitoring of electrical parameters. The controller continuously evaluates the stress on the energy source and modifies power distribution accordingly, enabling the system to adapt to changing conditions and prevent circuit protection engagement while maintaining operational versatility.
2Reliability
If power is reduced to loads to prevent circuit protection engagement, then circuit reliability is improved, but the functional output of the loads is diminished
Solution Approach 1:
The controller applies power reduction selectively to specific loads that are contributing most to the stress on the energy source, rather than uniformly reducing power to all loads. This localized approach maintains the functional output of critical loads while preventing circuit protection engagement through targeted power management.
Solution Approach 2:
The system implements partial power reduction to loads rather than complete shutdown, maintaining sufficient functional output to perform essential functions while reducing stress on the energy source enough to prevent circuit protection engagement. The controller calculates the precise power reduction needed to stay below the engagement threshold.
3Reliability
If traditional circuit protection methods are used, then circuit safety is improved, but external control requirements and device complexity increase
Solution Approach 1:
The controller autonomously monitors electrical parameters, detects potential circuit protection engagement scenarios, and automatically adjusts power allocation to prevent engagement. This self-service approach eliminates the need for external control systems or manual intervention, reducing device complexity while maintaining circuit safety.
Data Source
AI summary
A system for restricting power to a load to prevent engaging circuit protection device for an aircraft. The system includes an energy source of an aircraft. The system further includes a plurality of sensors configured to sense at least an electrical parameter of a load of the plurality of loads. The system further includes an aircraft controller configured to receive electrical parameter of a load of the plurality of loads from the plurality of sensors, compare the electrical parameter to at least a current allocation threshold, detect that the electrical parameter has reached the current allocation threshold, calculate a power reduction to the load, and reduce power from the at least an energy source to each load of the plurality of loads by the power reduction. The system further includes at least an electrical circuit of an aircraft, wherein the electrical circuit comprises a circuit protection device.