Systems and methods for transferring electric power to an aircraft during flight
First Claim
1. A system for transferring electric power, comprising:
- a receiver aircraft comprising a first fuselage and a first coupling device externally mounted to the first fuselage, wherein the first coupling device comprises first and second electrical contacts and first and second electrical conductors respectively connected to the first and second electrical contacts; and
a donor aircraft comprising a second fuselage and a second coupling device positioned aft of the second fuselage, wherein the second coupling device comprises third and fourth electrical contacts and third and fourth electrical conductors respectively connected to the third and fourth electrical contacts,wherein the first and second electrical contacts are respectively in contact with the third and fourth electrical contacts when the first and second coupling devices are coupled together;
wherein one of the first and second coupling devices has an annular groove and the other of the first and second coupling devices comprises a piston that fits into the annular groove for locking the first and second coupling devices together, a crank connected to the piston, and a motor having an output shaft connected to the crank; and
wherein the piston is displaced radially inward into the annular groove when the motor drives rotation of the crank.
1 Assignment
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Accused Products
Abstract
Systems and methods for transferring electric power to an aircraft during flight. Power transfer to the receiver aircraft is effected by means of a donor aircraft using a wired electrical connection. The method for transferring electric power includes: establishing an electrical connection between a receiver aircraft and a donor aircraft during flight; and transferring electric power from the donor aircraft to the receiver aircraft via the electrical connection. In one embodiment, electric power is transferred by way of a power cable deployed by the donor aircraft, a drogue attached to a trailing end of the power cable, and a probe mounted to the fuselage of the receiver aircraft, The probe and drogue are configured to form an electrical connection when fully engaged.
28 Citations
21 Claims
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1. A system for transferring electric power, comprising:
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a receiver aircraft comprising a first fuselage and a first coupling device externally mounted to the first fuselage, wherein the first coupling device comprises first and second electrical contacts and first and second electrical conductors respectively connected to the first and second electrical contacts; and a donor aircraft comprising a second fuselage and a second coupling device positioned aft of the second fuselage, wherein the second coupling device comprises third and fourth electrical contacts and third and fourth electrical conductors respectively connected to the third and fourth electrical contacts, wherein the first and second electrical contacts are respectively in contact with the third and fourth electrical contacts when the first and second coupling devices are coupled together; wherein one of the first and second coupling devices has an annular groove and the other of the first and second coupling devices comprises a piston that fits into the annular groove for locking the first and second coupling devices together, a crank connected to the piston, and a motor having an output shaft connected to the crank; and wherein the piston is displaced radially inward into the annular groove when the motor drives rotation of the crank. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 12, 13, 14, 17)
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11. A system for transferring electric power, comprising:
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a receiver aircraft comprising a first fuselage and a first coupling device externally mounted to the first fuselage, wherein the first coupling device comprises first and second electrical contacts and first and second electrical conductors respectively connected to the first and second electrical contacts; and a donor aircraft comprising a second fuselage and a second coupling device positioned aft of the second fuselage, wherein the second coupling device comprises third and fourth electrical contacts and third and fourth electrical conductors respectively connected to the third and fourth electrical contacts, wherein the first and second electrical contacts are respectively in contact with the third and fourth electrical contacts when the first and second coupling devices are coupled together; wherein the first coupling device comprises a hook, a pivot axle having opposing ends affixed to the hook, and a pivotable latch that is rotatably coupled to the pivot axle and spring-loaded; and wherein the second coupling device comprises a trapeze bar configured to fit between the hook and the pivotable latch when the pivotable latch is in a closed position. - View Dependent Claims (15, 18, 19, 20, 21)
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16. A system for transferring electric power during flight, comprising:
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a receiver aircraft comprising a first fuselage, a battery, a battery charger connected to the battery, a rectifier connected to the battery charger, and a first coupling device externally mounted to the first fuselage, wherein the first coupling device comprises first and second electrical contacts and first and second electrical conductors respectively connecting the first and second electrical contacts to the rectifier; and a donor aircraft comprising a second fuselage, a power supply, a power cable connected to the power supply, and a second coupling device external to and positioned aft of the second fuselage, wherein the second coupling device comprises third and fourth electrical contacts connected to the power supply via the power cable, wherein the first and second electrical conductors are cups having profiles that are truncated cones; wherein the third and fourth electrical conductors are annular bands; and wherein the first and second electrical contacts are respectively in contact with the third and fourth electrical contacts.
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Specification