Aircraft Refueling Flow Booster with Dynamic Pressure Control
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Solution Overview
Problem
Current aircraft fueling techniques lack efficiency and safety, with existing systems struggling to optimize fuel flow and maintain pressure within safe limits during refueling operations.
Innovation Solution
A flow booster system that adjusts fuel flow by using an intake tuner and trigger mechanism, coupled with sensors to monitor and control fuel parameters, ensuring continuous optimization of fuel flow into aircraft during refueling.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If conventional refueling systems are used, then fuel transfer can be performed, but fuel flow optimization and pressure control are insufficient
Solution Approach 1:
The system employs a dynamic flow booster that actively adjusts fuel flow rate in real-time based on sensor feedback, transitioning from static conventional refueling to dynamic controlled refueling. The flow booster modulates its operation to optimize transfer rate while maintaining pressure within safe limits, resolving the contradiction between productivity and reliability.
Solution Approach 2:
The system implements a closed-loop feedback control mechanism where sensors continuously monitor fuel pressure and flow rate, and this information feeds back to the flow booster controller which adjusts operation accordingly. This feedback loop ensures pressure safety while maximizing fuel transfer efficiency, addressing both reliability and productivity requirements.
2Loss of time
If fuel flow rate is increased to reduce refueling time, then productivity improves, but pressure surges and equipment stress increase
Solution Approach 1:
The flow booster provides dynamic control of fuel flow rate, adjusting it continuously to prevent pressure surges while maintaining high transfer rates. Instead of using fixed high flow rates that cause pressure issues, the system adaptively modulates flow to optimize refueling speed without creating harmful pressure variations.
Solution Approach 2:
The system anticipates potential pressure surges by using the flow booster to gradually increase and smooth fuel flow transitions. The flow booster acts as a cushioning element that prevents sudden pressure spikes before they occur, protecting equipment while maintaining efficient refueling rates.
3Productivity
If conventional refueling systems are used, then equipment simplicity is maintained, but flow optimization capability is limited
Solution Approach 1:
The flow booster serves as an intermediary device inserted into the existing refueling system between the fuel source and the aircraft. This mediator component provides advanced flow optimization capabilities without requiring complete system replacement, balancing productivity improvement with manageable complexity addition.
Solution Approach 2:
The flow booster is designed as a multi-functional device that simultaneously optimizes fuel flow rate, controls pressure, reduces refueling time, and minimizes pressure surges. By consolidating multiple functions into a single unit, the system achieves high productivity without proportionally increasing overall system 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 enhances safety and efficiency by maintaining fuel pressure within safe limits, reducing refueling time, and optimizing fuel transfer rates, while minimizing pressure surges and equipment stress.
Implementation Method 1
The piston has a fuel force applied to the piston and a tuning force applied to the piston against the fuel force
Data Source
AI summary
A flow booster for optimizing flow of fuel passing into an aircraft. The flow booster includes a fuel intake fluidly coupled to the fuel circuit, and includes a housing and a piston. The piston has a piston head slidably movable in the housing to define h a variable fuel inlet to receive the fuel. The fuel applies a fuel force to the piston. An intake tuner is operatively connected to the fuel M intake, and has a tuning force applied to the piston against the fuel force. A trigger is coupled to the intake tuner to vary the tuning force applied by the intake tuner. The flow regulator is coupled to sensors to receive fuel measurements. A flow regulator is operatively connected to the trigger to activate the trigger in response to the fuel measurements whereby the flow of the fuel into the aircraft is continuously adjustable during refueling.