In-Flight Refuelling Coupling for Fuel and Power Transfer
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Solution Overview
Problem
Conventional in-flight refuelling systems face challenges in efficiently transferring both fuel and electric power to receiver aircraft during air-to-air refuelling, particularly due to the high fuel pressure closing the fuel passage and the need for improved electrical connectivity between the tanker and receiver aircraft.
Innovation Solution
The system incorporates a refuelling hose with a coupling that includes a valve member for controlling fuel flow and transmitting electric power using resistive or inductive coupling, allowing simultaneous transfer of fuel and electric power through resistive contact or wireless charging between the tanker and receiver aircraft.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a conventional poppet-type valve is used to control fuel flow, then the fuel passage can be closed to prevent fuel leakage, but the high fuel pressure acts on the valve surface urging it towards the closed position, making it difficult to open the fuel passage
Solution Approach 1:
The patent replaces the conventional poppet-type mechanical valve with a magnetically actuated valve system. A magnet is positioned on the valve member, and a coil generates a magnetic field to actuate the valve open or closed. This magnetic actuation system overcomes the high fuel pressure forces that hinder conventional mechanical valve operation, enabling reliable opening and closing without direct mechanical contact with the pressurized fuel.
2Ease of operation
If the refuelling probe engages with the reception coupling to push the valve open, then the fuel passage opens for refuelling, but the system cannot transmit electric power from the tanker aircraft to the receiver aircraft
Solution Approach 1:
The refuelling probe and reception coupling system is designed to perform multiple functions: it controls the fuel passage valve, transmits electric power from the tanker aircraft to the receiver aircraft, and provides structural engagement for refuelling. The electrically conductive members are integrated into the coupling mechanism, allowing simultaneous fuel and power transfer through the same engagement interface.
Solution Approach 2:
The patent combines the mechanical valve actuation function with the electric power transmission function in a single integrated system. The refuelling probe contains both mechanical engagement features for pushing the valve open and electrically conductive members for power transmission, merging these previously separate functions into one unified refuelling interface.
3Adaptability or versatility
If the valve member is made electrically conductive for power transmission, then electric power can be transmitted through the valve, but the fuel pressure acting on the valve surface increases the risk of fuel leakage through the conductive material
Solution Approach 1:
The valve member is constructed from composite materials or coated with specialized materials that combine electrical conductivity with fuel impermeability. This allows the valve to transmit electric power while maintaining its sealing function against high-pressure fuel, resolving the contradiction between power transmission capability and fuel leakage prevention.
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
Enables efficient and simultaneous refuelling of both fuel and electric power to the receiver aircraft, enhancing operational flexibility and efficiency in air-to-air refuelling operations.
Implementation Method 1
The third electrically conductive member and the fourth electrically conductive member are for transmitting electric power to the refuelling probe by resistive contact, i.e. by forming a physical contact and therefore an electrically resistive contact between corresponding electrically conductive members on the refuelling probe
Implementation Method 2
The valve member comprises a nozzle engaging portion that is shaped to correspond to a nozzle tip of the refuelling probe and that comprises means for transmitting electric power to the refuelling probe
Data Source
Figure 1
Figure 2
Figure 3A
AI summary
An in-flight refuelling system (10) for an aircraft is provided. The system comprises a refuelling hose (11) of an in-flight refuelling system (10) for a tanker aircraft (100) and a refuelling probe (12) of an in-flight refuelling system for a receiver aircraft (101). The refuelling hose (12) comprises a coupling (14) comprising an opening for receiving a refuelling probe (12) of a receiver aircraft (101), a main body (81) comprising a fuel passage (23), and a valve member (28) disposed in the fuel passage (23) that is configured to close the fuel passage (23) and to open the fuel passage (23) to allow refuelling of the receiver aircraft (101). The valve member (28) comprises a nozzle engaging portion (29) that is shaped to correspond to a nozzle tip (16) of the refuelling probe (12) and means (36, 37; 28, 75) for transmitting electric power to the refuelling probe (12). The refuelling probe (12) comprises a nozzle (15) comprising a nozzle tip (16) and a fuel passage. The nozzle tip (16) comprises means (42; 91) for receiving electric power from a refuelling hose (11) of a tanker aircraft (100).