Antispark battery connector

Patent metadata

Field	Value
Publication number	US-12149017-B2
Application number	US-202318464868-A
Country	US
Kind code	B2
Filing date	Sep 11, 2023
Priority date	Dec 1, 2020
Publication date	Nov 19, 2024
Grant date	Nov 19, 2024

Abstract

In an embodiment, a battery connector includes: power terminals configured to be coupled to a load having an input capacitance; power pins electrically coupled to the power terminals; a charge pin, the charge pin being longer than each of the power pins; and an antispark circuit electrically interposed between the charge pin and the power terminals, the antispark circuit including: a dissipation circuit configured to charge the input capacitance of the load in response to a battery being coupled to the charge pin; and a delay circuit configured to delay charging of the input capacitance of the load for a predetermined duration after the battery is coupled to the charge pin.

First claim

What is claimed is:

1. An aircraft comprising:
pilot flight controls;
a flight control computer coupled to the pilot flight controls, the flight control computer configured to receive input signals from the pilot flight controls and generate control signals according to the input signals; and
an engine comprising an engine control computer and a power converter, the engine control computer coupled to the flight control computer, the flight control computer further configured to transmit the control signals to the engine control computer, the power converter comprising power terminals and a battery connector, the battery connector comprising:
an antispark circuit coupled to the power terminals;
a charge pin coupled to the antispark circuit; and
power pins coupled to the power terminals, the charge pin being longer than each of the power pins.

2. The aircraft of claim 1 , wherein the flight control computer comprises data terminals, and the battery connector further comprises:
data pins coupled to the data terminals, the data pins having a smaller width and a smaller spacing than the power pins.

3. The aircraft of claim 2 , wherein the battery connector further comprises:
a circuit board, wherein each of the data pins, the power pins, and the charge pin are attached to the circuit board; and
a connector housing attached to the circuit board, wherein the data pins, the power pins, and the charge pin each extend from a same side of the connector housing.

4. The aircraft of claim 2 , wherein the data terminals are part of a serial communications bus for the flight control computer.

5. The aircraft of claim 1 , further comprising:
a battery connected to the power converter with the battery connector.

6. The aircraft of claim 1 , wherein the power converter has an input capacitance, and the antispark circuit comprises:
a resistor in series with the input capacitance, the resistor and the input capacitance forming a RC circuit having a transient response time of less than 250 ms.

7. The aircraft of claim 6 , wherein the antispark circuit further comprises:
a delay circuit in series with the resistor and the input capacitance, the delay circuit comprising passive devices and being free of active devices.

8. The aircraft of claim 7 , wherein the delay circuit comprises a thermistor.

9. The aircraft of claim 6 , wherein the antispark circuit further comprises:
a delay circuit in series with the resistor and the input capacitance, the delay circuit comprising passive devices and active devices.

10. The aircraft of claim 9 , wherein the delay circuit comprises:
a switch connected in series with the resistor and the input capacitance;
a timer circuit configured to produce a timer signal;
a reference circuit configured to produce a reference signal; and
a compare circuit coupled to the reference circuit, the timer circuit, and the switch, the compare circuit configured to turn off the switch when the timer signal is less than the reference signal, the compare circuit configured to turn on the switch when the timer signal is greater than the reference signal.

11. The aircraft of claim 1 , wherein the power pins are directly coupled to the power terminals such that no intervening circuits are interposed between the power pins and the power terminals.

12. An aircraft comprising:
an engine comprising a power converter, the power converter having an input capacitance, the power converter comprising power terminals and a battery connector, the battery connector comprising:
power pins coupled to the power terminals;
a charge pin, the charge pin being longer than each of the power pins; and
an antispark circuit electrically interposed between the charge pin and the power terminals, the antispark circuit comprising a resistor in series with the input capacitance, the resistor and the input capacitance forming a RC circuit having a transient response time of less than 250 ms.

13. The aircraft of claim 12 , further comprising:
pilot flight controls; and
a flight control computer coupled to the pilot flight controls and to an engine control computer of the engine, the flight control computer configured to receive input signals from the pilot flight controls, to generate control signals according to the input signals, and to transmit the control signals to the engine control computer.

14. The aircraft of claim 12 , further comprising:
a battery comprising a battery socket, the battery connector inserted in the battery socket.

15. The aircraft of claim 12 , wherein the antispark circuit further comprises a delay circuit in series with the resistor and the input capacitance, the delay circuit configured to delay charging of the input capacitance.

16. The aircraft of claim 15 , wherein the delay circuit comprises a thermistor.

17. The aircraft of claim 15 , wherein the delay circuit comprises a switch.

18. An aircraft comprising:
a battery management system comprising data terminals; and
an engine comprising a power converter, the power converter comprising power terminals and a battery connector, the battery connector comprising:
an antispark circuit coupled to the power terminals;
a charge pin coupled to the antispark circuit;
power pins coupled to the power terminals, the charge pin being longer than each of the power pins; and
data pins coupled to the data terminals, the data pins having a smaller width and a smaller spacing than the power pins.

19. The aircraft of claim 18 , wherein the data terminals are part of a serial communications bus.

20. The aircraft of claim 18 , wherein the battery connector further comprises:
a circuit board, wherein each of the data pins, the power pins, and the charge pin are attached to the circuit board; and
a connector housing attached to the circuit board, wherein the data pins, the power pins, and the charge pin each extend from a same side of the connector housing.

Assignees

• Textron Innovations Inc

Inventors

• Brown Jason
• Schulte Kynn J

Classifications

• H02J7/64

  against overvoltage · CPC title

• H02J7/70 Primary

  characterised by the mechanical construction · CPC title

• G05D1/46

  Control of position or course in three dimensions [3D] · CPC title

• H01R2201/26

  for vehicles · CPC title

• H01R43/205

  with a panel or printed circuit board · CPC title