Electric Fuel Control Closed Loop Aircraft System
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Solution Overview
Problem
Traditional aircraft fuel control systems are complex and require separate control units for pump motor control and engine control, leading to inefficiencies and increased system complexity.
Innovation Solution
A fuel control system that integrates a full authority digital engine control (FADEC) with electric motor controlled fuel pumps and sensor systems at each fuel nozzle, eliminating the need for positive displacement pumping and valving, and simplifying the fuel line architecture.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If traditional separate control units are used for pump motor control and engine control, then functional separation is maintained, but system complexity increases
Solution Approach 1:
The patent combines separate control units (pump motor controller and engine controller) into a single integrated controller that manages both fuel pump operation and engine control functions. This consolidation reduces the number of discrete components and interconnections, directly addressing the technical contradiction by lowering system complexity while maintaining the necessary automation levels for both control functions.
2Device complexity
If positive displacement pumping and valving are used, then fuel flow control is achieved, but system complexity and weight increase
Solution Approach 1:
The patent replaces traditional mechanical positive displacement pumps and valving systems with an electric motor controlled pump system. The electric motor allows for precise control of fuel delivery through electronic regulation of motor speed and torque, eliminating the need for complex mechanical displacement mechanisms and valving components while maintaining accurate fuel flow control.
3Reliability
If multiple pumps and valves are installed in the fuel line, then fuel delivery reliability is improved, but system weight increases
Solution Approach 1:
The patent extracts and removes unnecessary components (valves and bypass lines) from the fuel system architecture. By using an electric motor controlled pump, the system achieves reliable fuel delivery without requiring multiple mechanical pumps or complex valve arrangements, thereby reducing overall system weight while maintaining or improving delivery reliability through electronic control.
4Ease of manufacture
If conventional fuel control systems are used, then fuel flow scheduling is maintained, but manufacturing cost increases
Solution Approach 1:
The patent creates a multi-functional integrated controller that performs both pump motor control and engine control functions. This universal controller consolidates what would traditionally require separate dedicated control units, simplifying the overall system architecture and reducing manufacturing costs by decreasing the number of components that need to be designed, tested, and assembled.
Data Source
Figure 1~2
AI summary
A fuel control system (100) for an aircraft includes first and second electric motor controlled fuel pumps (104, 110) connected in parallel with one another to a fuel line (102). A plurality of fuel nozzles (116) are connected to the fuel line to issue pressurized fuel from the fuel line with the ability to throttle flow based on system needs along with the electric pumping. At least one fuel nozzle in the plurality of fuel nozzles includes a respective sensor system (118). A fuel controller (124) is operatively connected to receive input from the respective sensor system of the at least one fuel nozzle, and operatively connected to control the first and second electric motor controlled pumps based on input from the respective sensor system of the at least one fuel nozzle.