Aircraft Fuel Pump Management System for Overheating Prevention
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing fuel pump management systems in aircraft do not effectively prevent fuel pump overheating and ignition hazards when fuel tanks are empty, leading to potential fires, and existing solutions like thermal switches and additional protections add complexity and weight.
Innovation Solution
A fuel pump management system that includes a fuel gauge to electronically read the fuel level and a controller to shut down the fuel pump when the level falls below a predetermined threshold, using components like capacitance probes or ultrasonic transducers, and determines if the aircraft is on the ground before shutting down the pump to prevent overheating and foreign object ignition.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If thermal switches and thermal fuses are imbedded in the fuel pump stator wiring to detect overheating, then the risk of fuel pump ignition is reduced, but the device complexity and weight increase
Solution Approach 1:
The fuel level sensor detects low fuel conditions before the fuel pump can overheat and cause ignition. By taking preliminary action to detect the hazardous condition (low fuel) before it leads to overheating, the system prevents the need for thermal switches and fuses that would only react after overheating occurs.
Solution Approach 2:
The controller receives feedback from the fuel level sensor and automatically shuts down the fuel pump when low fuel is detected. This feedback loop prevents the fuel pump from operating in a dry state, eliminating the overheating risk without requiring additional thermal protection components.
2Reliability
If ground fault interrupters and fast acting arc fault interrupters are imbedded in the fuel pump circuitry to protect against wire arcing, then ignition risk from arcing is reduced, but the device complexity increases
Solution Approach 1:
The fuel level sensor provides preliminary detection of low fuel conditions before arcing can occur. By shutting down the pump proactively based on fuel level feedback, the system prevents the dry running conditions that would lead to wire arcing, making GFIs and FAAFs unnecessary.
3Reliability
If dual fuses are imbedded for each wire in the fuel pump stator wiring to protect against foreign object damage, then ignition risk from FOD is reduced, but the device complexity and weight increase
Solution Approach 1:
The fuel level sensor detects low fuel conditions before foreign objects can lodge in the impeller and cause damage. By preemptively shutting down the pump when fuel level is low, the system prevents FOD incidents without requiring dual fuses for each wire.
4Extent of automation
If fuel pressure monitoring is used to shut off the system when pressure drops below threshold, then automatic shutdown is achieved, but the system cannot detect dry running conditions before pressure drop occurs
Solution Approach 1:
The fuel level sensor provides preliminary detection of low fuel conditions before the fuel pump operates dry and before pressure drops occur. This advance detection allows the controller to shut down the pump proactively, preventing both overheating and the need for pressure-based shutdown systems.
Solution Approach 2:
The controller receives continuous feedback from the fuel level sensor and automatically adjusts pump operation accordingly. This feedback mechanism provides both automatic shutdown capability and early detection of dry running conditions, unlike pressure monitoring which only detects problems after they have already occurred.
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
This solution reduces the risk of fuel pump overheating and ignition hazards by automatically shutting down the fuel pump when the fuel level is low, eliminating the need for additional protections like thermal switches and reducing complexity and weight in the aircraft fuel system.
Implementation Method 1
the fuel gauge comprises at least one of a capacitance probe and a proximity sensing unit
Implementation Method 2
the fuel gauge comprises at least one of an ultrasonic transducer, a magnetoresistive level transmitter, a laser transmitter and a guided wave radar
Data Source
AI summary
A method of and a system for operating a fuel pump management system of an aircraft. The method comprises receiving, from a fuel gauge, an electronic reading of a level of fuel fluid contained in a fuel tank; and analysing the electronic reading of the level of the fuel fluid, the analysing comprising upon determining that the level of fuel fluid is equal or below a predetermined fuel level threshold, causing a fuel pump in communication with the fuel tank to be shut down.