Electric aircraft emergency power supply module

Patent metadata

Field	Value
Publication number	US-12506347-B2
Application number	US-202217706756-A
Country	US
Kind code	B2
Filing date	Mar 29, 2022
Priority date	Mar 29, 2021
Publication date	Dec 23, 2025
Grant date	Dec 23, 2025

Abstract

An electric aircraft emergency power supply module includes at least one electric power cell for storing and supplying electric energy and a controller for controlling charging and discharging of the at least one electric power cell and for determining a charging level of the at least one electric power cell. The controller includes a simulator, which is configured for simulating an electric behavior of at least one temperature sensitive element as a function of the charging level of the at least one electric power cell.

First claim

The invention claimed is:

1 . An electric aircraft emergency power supply module comprising:
a plurality of electric power cells, which are connected, for storing and supplying electric energy; and a controller for determining a charging level of at least one electric power cell of the plurality of electric power cells and for controlling charging and discharging of the at least one electric power cell, wherein the controller comprises: a plurality of individual power cell controllers, each being associated with and configured for individually controlling the charging and the discharging of a single electric power cell of the plurality of electric power cells; and a simulator, which is configured for simulating an electric behavior of at least one temperature sensitive element as a function of charging level of the at least one electric power cell of the plurality of electric power cells, wherein the plurality of electric power cells are connected in series and each individual power cell controller of the controller comprises: an individual electric bypass circuit, which is controlled by a corresponding bypass controller and is configured for selectively bypassing a single electric power cell; an individual isolation switch and an associated individual isolation switch activator, which allow for selectively and individually connecting the associated electric power cell with power supply terminals and disconnecting the associated electric power cell from the power supply terminals; and a bypass switch, which allows for bypassing the deactivated electric power cell and which is controlled by the corresponding bypass switch controller.

2 . The electric aircraft emergency power supply module according to claim 1 ,
wherein the controller is configured for determining a desired charging current for charging the at least one electric power cell of the plurality of electric power cells from the determined charging level of the at least one electric power cell of the plurality of electric power cells; and wherein the simulator is configured for simulating the electric behavior of the at least one temperature sensitive element for causing an external charge monitor to supply the desired charging current to the electric aircraft emergency power supply module.

3 . The electric aircraft emergency power supply module according to claim 1 , wherein the simulator is configured for simulating the electric behavior of the at least one temperature sensitive element based on a temperature vs. charging current relation of at least one electric power cell of the plurality of electric power cells which is of a NiCd-type.

4 . The electric aircraft emergency power supply module according to claim 1 , wherein the at least one electric power cell of the plurality of electric power cells comprises at least one electric power cell of a NiMH-type.

5 . The electric aircraft emergency power supply module according to claim 1 , wherein the simulator is configured for simulating the electric behavior of at least one NTC thermal resistor and of at least one PTC thermal resistor.

6 . The electric aircraft emergency power supply module according to claim 1 , further comprising:
at least two power supply terminals, internally coupled to the plurality of electric power cells and coupleable to an aircraft power supply; and at least two status indication terminals, internally coupled to the simulator and coupleable to a charge monitor of an aircraft, wherein the simulator is configured to output a status signal on the at least two status indication terminals, the status signal being indicative of the simulated electric behavior of at least one temperature sensitive element.

7 . The electric aircraft emergency power supply module according to claim 1 , further comprising at least one electric bypass circuit configured for selectively bypassing the at least one electric power cell of the plurality of electric power cells, wherein the controller is in particular configured for temporarily bypassing the at least one electric power cell and measuring the voltage (U) of the bypassed electric power cell.

8 . The electric aircraft emergency power supply module according to claim 1 , further comprising at least one temperature sensor configured for detecting a temperature (T) of the electric aircraft emergency power supply module and a temperature (T) of the at least one electric power cell of the plurality of electric power cells.

9 . The electric aircraft emergency power supply module according to claim 1 , wherein the controller is configured for determining the charging level of the at least one electric power cell of the plurality of electric power cells from a detected temperature (T) and from a detected voltage (V) of the at least one electric power cell.

10 . The electric aircraft emergency power supply module according to claim 1 , wherein the controller is configured for selectively charging the at least one electric power cell of the plurality of electric power cells with a high charging current I high in a rapid charging mode or with a low charging current I low , which is lower than the high charging current I high , in a low charging mode.

11 . The electric aircraft emergency power supply module according to claim 1 , wherein the controller is configured for determining the maximum load capacity Q max of the at least one electric power cell of the plurality of electric power cells by monitoring a controlled charging and discharging of the at least one electric power cell, and
wherein the controller is in particular configured for at least one of: displaying the determined maximum load capacity Q max of the at least one electric power cell at the electric aircraft emergency power supply module; providing a capacity signal indicating the determined maximum load capacity Q max of the at least one electric power cell; and comparing the determined maximum load capacity Q max of the at least one electric power cell with a predefined threshold and providing an alarm signal and deactivating the electric aircraft emergency power supply module if the determined maximum load capacity Q max of the at least one electric power cell is below the predefined threshold.

12 . The electric aircraft emergency power supply module according to claim 1 , wherein each individual power cell controller of the controller further comprises a voltmeter, an ammeter and a temperature sensor, which are configured for measuring the voltage, the electric current and the temperature of the associated electric power cell.

Assignees

• Goodrich Lighting Systems Gmbh & Co Kg

Inventors

• Hessling-Von Heimendahl Andre
• Trinschek Robert

Classifications

• H02J2105/32

  for aircrafts · CPC title

• H02J7/50

  acting upon multiple batteries simultaneously or sequentially · CPC title

• H02J7/977

  of the battery · CPC title

• H02J7/965

  obtained with the battery disconnected from the charge or discharge circuit · CPC title

• H02J7/82 Primary

  Control of state of charge [SOC] · CPC title