Aircraft external DC power voltage protection

Patent metadata

Field	Value
Publication number	US-9764856-B2
Application number	US-201414294763-A
Country	US
Kind code	B2
Filing date	Jun 3, 2014
Priority date	Jun 3, 2014
Publication date	Sep 19, 2017
Grant date	Sep 19, 2017

Abstract

An external power supply system for an aircraft includes a power receptacle configured to connect to an external power source to provide external power, a power switch operative to switch between a battery power source and the external power source, and a voltage check system configured to prevent at least one of under-voltage or over-voltage of an aircraft electrical system. The voltage check system includes a voltage relay sensor configured to determine if the external power is within a suitable voltage range and a check switch operatively connected to the voltage relay sensor, wherein if the external power is within a suitable voltage range, the voltage relay sensor activates the check switch to allow external power to the aircraft electrical system, and wherein if the external power is outside the suitable voltage range, then the voltage relay sensor does not allow power to the aircraft electrical system.

First claim

What is claimed is:

1. An external power supply system for an aircraft, comprising:
a power receptacle configured to connect to an external power cable from an external power source to provide an external power;
a power switch operative to switch between a battery power source and the external power source; and
a voltage check system configured to prevent both of under-voltage and over-voltage of an aircraft electrical system, the voltage check system including:
a voltage relay sensor configured to determine if the external power is within a suitable voltage range, wherein the voltage relay sensor is configured to determine if the external power is within a low voltage threshold and a high voltage threshold; and
a check switch, wherein if the external power is within a suitable voltage range, the voltage relay sensor activates the check switch to allow external power to the aircraft electrical system, wherein if the external power is outside the suitable voltage range, then the voltage relay sensor does not allow power to the aircraft electrical system.

2. The system of claim 1 , further comprising at least one first indicator operatively connected to the power receptacle to indicate that the external power is available.

3. The system of claim 2 , wherein the voltage check system is configured to only allow activation of the first indicator when the external power is within the suitable voltage range.

4. The system of claim 1 , further comprising at least one second indicator operatively connected to the power receptacle to indicate that the external power is in use.

5. The system of claim 1 , wherein the low voltage threshold is about 18 volts DC.

6. The system of claim 1 , wherein the low voltage threshold is high enough to allow for starting of an auxiliary power unit.

7. The system of claim 1 , wherein the high voltage threshold is about 32 volts DC.

8. The system of claim 1 , wherein the voltage relay sensor is operatively connected to the power receptacle to be powered by the external power, wherein in the event of a power sag in the external power supply, the battery power source powers the voltage relay sensor to prevent system shutoff.

9. The system of claim 1 , wherein the aircraft electrical system includes an electrical power distribution circuit (EPDC) operatively connected to the power receptacle, and connected to and controlled by the voltage check system.

10. The system of claim 1 , wherein the aircraft electrical system includes an APU starter operatively connected to the power receptacle.

11. An aircraft electrical system, comprising:
a power receptacle configured to connect to an external power cable from an external power source to provide an external power;
a power switch operative to switch between a battery power source and the external power source; and
a voltage check system configured to prevent both of under-voltage and over-voltage of an aircraft electrical system, the voltage check system including:
a voltage relay sensor configured to determine if the external power is within a suitable voltage range, wherein the voltage relay sensor is configured to determine if the external power is within a low voltage threshold and a high voltage threshold; and
a check switch, wherein if the external power is within a suitable voltage range, the voltage relay sensor activates the check switch to allow external power to an electrical power distribution circuit (EPDC) of an aircraft, wherein if the external power is outside the suitable voltage range, then the voltage relay sensor does not activate the check switch.

12. The system of claim 11 , wherein the check switch is an inductive coil switch operatively coupled to the voltage relay sensor.

13. The system of claim 11 , further comprising a voltage comparator ahead of the voltage relay sensor to allow for an auxiliary power unit (APU) starter to be supplied with power if a sufficiently high voltage is present in the battery supply to account for a voltage droop in the external power due to activating the APU starter, thereby preventing the check switch from opening due to low voltage after an APU start has been initiated.

14. The system of claim 11 , further including a first indicator operatively connected to the voltage relay sensor and the EPDC, wherein the first indicator is powered through the EPDC when the EPDC receives power through the voltage check system.

Assignees

• Hamilton Sundstrand Corp

Inventors

• Stevens Clifford G
• Kramer Kenneth

Classifications

• B64F1/35

  for supplying electrical power to stationary aircraft · CPC title

• B64F1/34 Primary

  for starting propulsion plant · CPC title

• H02H11/006

  in case of too high or too low voltage · CPC title

• H02J1/00

  Circuit arrangements for DC mains or DC distribution networks · CPC title

• H02H1/0007 Primary

  concerning the detecting means (in general G01R or other subclasses of G01; reed switches H01H71/2445) · CPC title