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1. 发明授权

US11945601B2 Methods and systems for in-flight charging of aircraft 有权
公开(公告)号：US11945601B2
公开(公告)日：2024-04-02
申请号：US17279468
申请日：2019-09-19
申请人： Brulic Ltd.
发明人： James Pitman
IPC分类号： B64D39/02 , B64D39/00 , B64D39/06 , H02J7/00 , H02J50/10
CPC分类号： B64D39/02 , B64D39/00 , B64D39/06 , H02J7/00032 , H02J7/0045 , H02J50/10
摘要： A method of operating a supply aircraft for in-flight recharging comprises: transmitting a deploy command signal from a communication unit of the supply aircraft to a communication unit of a receiver aircraft, to cause a line and drogue to deploy from the receiver aircraft; controlling at least one of the supply aircraft and the drogue to engage the drogue with a first end of an electrical cable of the supply aircraft, a second end of the electrical cable being connected to the supply aircraft; and transmitting a return command signal from the communication unit of the supply aircraft to the communication unit of the receiver aircraft, to cause the line and drogue to return to the receiver aircraft with the first end of the electrical cable. The supply aircraft is located behind the receiver aircraft and the deploy command signal is for causing the line and drogue to deploy rearwardly of the receiver aircraft.

2. 发明申请

US20210362872A1 Methods and Systems for In-Flight Charging of Aircraft 有权
公开(公告)号：US20210362872A1
公开(公告)日：2021-11-25
申请号：US17279468
申请日：2019-09-19
申请人： Brulic Ltd.
发明人： James Pitman
IPC分类号： B64D39/02 , B64D39/06 , H02J7/00 , H02J50/10
摘要： A method of operating a supply aircraft for in-flight recharging comprises: transmitting a deploy command signal from a communication unit of the supply aircraft to a communication unit of a receiver aircraft, to cause a line and drogue to deploy from the receiver aircraft; controlling at least one of the supply aircraft and the drogue to engage the drogue with a first end of an electrical cable of the supply aircraft, a second end of the electrical cable being connected to the supply aircraft; and transmitting a return command signal from the communication unit of the supply aircraft to the communication unit of the receiver aircraft, to cause the line and drogue to return to the receiver aircraft with the first end of the electrical cable. The supply aircraft is located behind the receiver aircraft and the deploy command signal is for causing the line and drogue to deploy rearwardly of the receiver aircraft.

3. 发明申请

US20210362871A1 Propellant-Handling Module for an Aircraft 有权
公开(公告)号：US20210362871A1
公开(公告)日：2021-11-25
申请号：US17279467
申请日：2019-09-26
申请人： Brulic Ltd.
发明人： James Pitman
IPC分类号： B64D39/02 , B64D39/06
摘要： A propellant-handling module for installation in a host aircraft comprises: a motorised drum unit comprising a line and drogue for engagement with a propellant supply line of a propellant supply aircraft and for drawing the propellant supply line from the propellant supply aircraft to the host aircraft when the propellant supply aircraft is located behind the host aircraft; a propellant inlet configured for connection with the propellant supply line; a propellant outlet in communication with the propellant inlet and configured for connection with a propellant system of the host aircraft; an electrical power unit for powering the propellant-handling module; and a communication and control system for receiving a deploy command signal and a return command signal from the supply aircraft and configured to: receive said deploy command signal and in response control the motorised drum unit to deploy the line and drogue for said engagement with the propellant supply line; and receive said return command signal and in response control the motorised drum unit to return the line and drogue to the host aircraft in said engagement with the propellant supply line for drawing the propellant supply line from the propellant supply aircraft to the host aircraft when the propellant supply aircraft is located behind the host aircraft.

4. 发明授权

US11718412B2 Propellant-handling module for an aircraft 有权
公开(公告)号：US11718412B2
公开(公告)日：2023-08-08
申请号：US17279467
申请日：2019-09-26
申请人： Brulic Ltd.
发明人： James Pitman
IPC分类号： B64D39/02 , H02J50/10 , H02J7/00 , B64D39/06 , B64D39/00
CPC分类号： B64D39/02 , B64D39/00 , B64D39/06 , H02J7/00032 , H02J7/0045 , H02J50/10
摘要： A propellant-handling module for installation in a host aircraft comprises: a motorised drum unit comprising a line and drogue for engagement with a propellant supply line of a propellant supply aircraft and for drawing the propellant supply line from the propellant supply aircraft to the host aircraft when the propellant supply aircraft is located behind the host aircraft; a propellant inlet configured for connection with the propellant supply line; a propellant outlet in communication with the propellant inlet and configured for connection with a propellant system of the host aircraft; an electrical power unit for powering the propellant-handling module; and a communication and control system for receiving a deploy command signal and a return command signal from the supply aircraft and configured to: receive said deploy command signal and in response control the motorised drum unit to deploy the line and drogue for said engagement with the propellant supply line; and receive said return command signal and in response control the motorised drum unit to return the line and drogue to the host aircraft in said engagement with the propellant supply line for drawing the propellant supply line from the propellant supply aircraft to the host aircraft when the propellant supply aircraft is located behind the host aircraft.

5. 发明申请

US20210362873A1 Fuel Hose Assembly for In-Flight Fuelling of Aircraft 有权
公开(公告)号：US20210362873A1
公开(公告)日：2021-11-25
申请号：US17279485
申请日：2019-10-21
申请人： Brulic Ltd.
发明人： James Pitman
IPC分类号： B64D39/04 , F16L11/12 , F16L11/18
摘要： A fuel hose assembly for inflight fuelling of aircraft comprises: a flexible inner tube for conveying fuel under pressure; an outer cover comprising a plurality of rigid parts; and an actuator configured to move the rigid parts lengthwise along the flexible inner tube. The rigid parts are movable by the actuator to provide continuous lengthwise cover over the flexible inner tube, so as to be able to resist radial expansion of the flexible inner tube when the flexible inner tube is pressurised. The rigid parts are further movable by the actuator to uncover lengthwise portions of the flexible inner tube between the rigid parts, so as to allow bending of the flexible inner tube when the flexible inner tube is unpressurised.

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