Solid state power controller
AssigneeLilium eAircraft GmbH
InventorsEd Culpin, Thalles Gomes, Martin Angerer
Life of this patent
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Abstract
Provided is a solid state power controller (SSPC). The SSPC comprises a power supply line configured to be connected between a power source and a load. Further, the solid state power controller comprises a semiconductor switching unit provided on the power supply line and configured to switch between at least two states according to a command signal. The at least two states include a conducting state and a non-conducting state. Further the solid state power controller comprises a state machine, which is configured to exhibit at least two states, including an ON state and an OFF state. The state machine is further configured to output the command signal according to a current state of the state machine.
Claims19
A solid state power controller, comprising:
- a power supply line configured to be connected between a power source and a load;
- a semiconductor switching unit provided on the power supply line and configured to switch between at least two states, including a conducting state and a non-conducting state,
- according to a command signal;
- and
- a state machine configured to:
- exhibit at least three states including an ON state, an OFF state, and a pre-charge state;
- and
- output the command signal according to a current state of the state machine, wherein:
- in the ON state, a power dissipation within the semiconductor switching unit is controlled according to a positive supply power voltage,
- in the OFF state, the power dissipation within the semiconductor switching unit is controlled to be zero,
- in the pre-charge state, the power dissipation within the semiconductor switching unit is controlled according to a predetermined reference voltage,
- the state machine is a non-programmable logic part formed by a plurality of non-programmable electronic components and is configured to:
- transition from the OFF state to the pre-charge state based on a vehicle command transmitted via an external communication line, and
- transition from the pre-charge state to the ON state when a voltage across the semiconductor switching unit drops below the reference voltage, and
- the semiconductor switching unit is formed by one or more non-programmable electronic components.
An aircraft, comprising:
- a power source;
- a load;
- and
- a solid state power controller including:
- a power supply line configured to be connected between the power source and the load;
- a semiconductor switching unit provided on the power supply line and configured to switch between at least two states, including a conducting state and a non-conducting state, according to a command signal;
- and
- a state machine configured to:
- exhibit at least three states including an ON state, an OFF state, and a pre-charge state;
- and
- output the command signal according to a current state of the state machine, wherein:
- in the ON state, a power dissipation within the semiconductor switching unit is controlled according to a positive supply power voltage,
- in the OFF state, the power dissipation within the semiconductor switching unit is controlled to be zero,
- in the pre-charge state, the power dissipation within the semiconductor switching unit is controlled according to a predetermined reference voltage,
- the state machine is a non-programmable logic part formed by a plurality of non-programmable electronic components and is configured to:
- transition from the OFF state to the pre-charge state based on a vehicle command transmitted via an external communication line, and
- transition from the pre-charge state to the ON state when a voltage across the semiconductor switching unit drops below the reference voltage, and
- the semiconductor switching unit is formed by one or more non-programmable electronic components.
Dependencies are inferred from the claim text.