Aircraft Fuel Boost Pump Electronic Control
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Aircraft fuel boost pumps face challenges in maintaining adequate fuel pressure and flow during extreme maneuvers, as the fuel head and acceleration can cause vaporization and air release, leading to potential engine failure due to insufficient suction pressure.
Innovation Solution
A digital fuel supply system with an electronic controller that receives and processes various aircraft, flight, and fuel information to automatically adjust the boost pump speed and pressure, using a look-up table for vapor pressures and system characteristics, and sensors for real-time data, ensuring continuous monitoring and compensation for maneuvers.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If the fuel tank is located in a lower portion and the engine in an upper portion to accommodate aircraft layout, then the suction pump can draw fuel from the tank, but the fuel head increases resulting in increased suction requirements that may lead to vaporization and fuel flow interruption
Solution Approach 1:
The boost pump is activated in advance before the suction pump to pre-establish adequate fuel pressure in the supply line. This preliminary pressurization prevents vaporization and ensures continuous fuel flow to the engine, especially during extreme maneuvers or when the aircraft is in an inverted position.
Solution Approach 2:
The system maintains a cushion of positive pressure in the fuel supply line through the boost pump, creating a buffer against pressure drops that could cause vaporization. This pressure cushion compensates for the increased suction requirements caused by the fuel head and extreme maneuvers.
2Adaptability or versatility
If the aircraft undertakes extreme maneuvers with high acceleration, then the aircraft can perform required flight operations, but the absolute pressure at the suction pump inlet may approach or fall below the true vapor pressure of the fuel, causing vapor evolution and air release
Solution Approach 1:
The boost pump is activated in advance of extreme maneuvers to pre-establish adequate fuel pressure. The electronic controller detects anticipated high-G maneuvers and activates the boost pump beforehand to maintain pressure above the true vapor pressure of the fuel, preventing vaporization during the maneuver.
Solution Approach 2:
The electronic controller continuously monitors fuel pressure, temperature, and aircraft maneuver data to dynamically control the boost pump operation. This feedback mechanism ensures the boost pump activates in response to detected maneuvers or conditions that could lead to vaporization, maintaining reliable fuel pump operation throughout the maneuver.
3Reliability
If a mechanical fuel pressure control system is used, then the system can maintain fuel pressure, but the system complexity increases and ground testing becomes difficult
Solution Approach 1:
The patent replaces complex mechanical fuel pressure control systems with an electronically controlled boost pump system. The electronic controller uses electrical signals to regulate boost pump operation based on sensor feedback, eliminating the need for complex mechanical linkages, springs, and adjustment mechanisms while simplifying ground testing and calibration.
Data Source
AI summary
A fuel supply system for an aircraft includes a fuel tank configured to supply fuel to an engine of an aircraft, a boost pump in operational communication with the fuel tank, wherein the boost pump is configured to control at least one of a fuel level and a fuel pressure in the fuel tank, and an electronic controller in communication with the boost pump and configured to control the boost pump. The electronic controller is configured to receive received information including (i) fuel information, (ii) flight information, and (iii) aircraft information, and configured to control the boost pump based on the received information.