# US 12,191,683 B2 · Charger connector for an electric aircraft

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- Number: US 12,191,683 B2
- Document ID: US12191683B2
- Status: Granted
- Kind: B2
- Application number: 18/116,190
- Filed: 2023-03-01
- Published: 2023-06-29
- Granted: 2025-01-07
- Earliest claimed: 2021-12-28
- Assignees: Beta Air, LLC
- Applicants: Beta Air, LLC
- Inventors: Herman Wiegman
- Web page: https://patentgrep.com/patent/US12191683B2

## CPC

- H02J 7/751: {concerning the insertion or the connection of the batteries}
- B60L 53/11: {DC charging controlled by the charging station, e.g. mode 4}
- B60L 53/16: Connectors, e.g. plugs or sockets, specially adapted for charging electric vehicles
- B60L 53/35: Means for automatic or assisted adjustment of the relative position of charging devices and vehicles
- B60L 53/62: in response to charging parameters, e.g. current, voltage or electrical charge
- B60L 53/66: Data transfer between charging stations and vehicles
- B60L 53/68: Off-site monitoring or control, e.g. remote control
- B64F 1/35: for supplying electrical power to stationary aircraft
- H02J 7/40: characterised by the exchange of charge or discharge related data
- H02J 7/70: characterised by the mechanical construction
- B60L 2200/10: Air crafts
- B64C 29/0008: {having its flight directional axis horizontal when grounded}
- Y02T 10/70: Energy storage systems for electromobility, e.g. batteries
- Y02T 10/7072: Electromobility specific charging systems or methods for batteries, ultracapacitors, supercapacitors or double-layer capacitors
- Y02T 90/14: Plug-in electric vehicles
- H02J: ELECTRIC POWER NETWORKS; CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- B60L: PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES (arrangements or mounting of electrical propulsion units or of plural diverse prime-movers for mutual or common propulsion in vehicles B60K1/00, B60K6/20; arrangements or mounting of electrical gearing in vehicles B60K17/12, B60K17/14; preventing wheel slip by reducing power in rail vehicles B61C15/08; dynamo-electric machines H02K; control or regulation of electric motors H02P); SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES (electric coupling devices combined with mechanical couplings of vehicles B60D1/64; electric heating for vehicles B60H1/00); ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL (control or regulation of electric motors H02P); MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
- B64F: GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64C: AEROPLANES; HELICOPTERS
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION

## Abstract

Aspects relate to a connector of a charger and methods of use terminating a charging connection between the charger and an electric aircraft. A connector includes a controller that is configured to receive a control signal from a remote device and terminate the charging connection in response to the control signal.

## Claims

### Claim 1

A connector of an electric aircraft charger, the connector comprising:
a housing configured to attach with an electric aircraft port of an electric aircraft to facilitate
a charging connection between the charger and the electric aircraft, wherein the housing comprises a fastener for removable attachment with the electric aircraft port, wherein the charging connection comprises an electric communication and a mechanical coupling;
a contactor, wherein the contactor is configured to selectively disengage the electric communication of the charging connection;
a conductor configured to conduct a current of the charging connection;
a control circuit configured to control the electric communication to terminate and reengage the charging connection between the charger and the electric aircraft by actions including:
terminate the charging connection between the charger and the electric aircraft using the contactor a in response to receiving a first control signal from a remote device; and
reengage the charging connection using the contactor in response to receiving a second control signal from the remote device.

### Claim 2 (depends on 1)

The connector of claim 1, wherein the contactor comprises a solenoid.

### Claim 3 (depends on 1)

The connector of claim 1, wherein the contactor comprises a contact protection configured to prevent electrical arcing during use of the contactor.

### Claim 4 (depends on 1)

The connector of claim 1, wherein the contractor comprises a relay.

### Claim 5 (depends on 1)

The connector of claim 1, wherein the fastener comprises an electromagnet.

### Claim 6 (depends on 1)

The connector of claim 1, wherein the control circuit is further configured to control a parameter of an electrical charging current of the charging connector as a function of the control signal.

### Claim 7 (depends on 1)

The connector of claim 1, further comprising a proximity sensor, wherein the proximity signal sensor is configured to detect a proximity signal.

### Claim 8 (depends on 7)

The connector of claim 7, further comprising a proximity signal conductor in electrical communication with the proximity sensor, wherein the proximity signal conductor is configured to conduct the proximity signal.

### Claim 9 (depends on 1)

The connector of claim 1, further comprising a sensor, wherein the sensor is configured to detect a characteristic of the charger, wherein the characteristic of the charger comprises a change in current through the connector.

### Claim 10

A method of terminating a charging connection using a connector, the method comprising:
attaching, by a fastener of a housing of the connector, the housing of the connector to an electric aircraft port of an electric aircraft to facilitate a charging connection between the charger and the electric aircraft, wherein the charging connection comprises an electric communication and a mechanical coupling;
conducting, by a conductor of the connector, a current of the charging connection;
terminating, by the control circuit, the charging connection between the charger and the electric aircraft using a contactor in response to a first control signal from a remote device, wherein the contactor is configured to selectively disengage the electric communication of the charging connection;
reengaging, by the control circuit, the charging connection using the contactor in response to receiving a second control signal from the remote device.

### Claim 11 (depends on 10)

The method of claim 10, wherein the contactor comprises a solenoid.

### Claim 12 (depends on 10)

The method of claim 10, wherein the contactor comprises a contact protection configured to prevent electrical arcing during use of the contactor.

### Claim 13 (depends on 10)

The method of claim 10, wherein the contractor comprises a relay.

### Claim 14 (depends on 10)

The method of claim 10, wherein the fastener comprises an electromagnet.

### Claim 15 (depends on 1)

The method of claim 1, further comprising controlling, by the control circuit, a parameter of an electrical charging current of the charging connector as a function of the control signal.

### Claim 16 (depends on 10)

The method of claim 10, further comprising detecting a proximity signal using a proximity sensor.

### Claim 17 (depends on 16)

The method of claim 16, further comprising conducting the proximity signal using a proximity signal conductor in electrical communication with the proximity sensor.

### Claim 18 (depends on 10)

The method of claim 10, further comprising detecting a charging characteristic of the charger by the sensor, wherein the characteristic of the charger includes a change in current through the connector.