Aircraft with hybrid power source and with junction having a transistor for distribution and protection
An aircraft includes drive units, at least one battery of the drive units, at least one electrical generation source connected to each battery and comprising at least one electrical converter, and a power supply control device to control each electrical generation source according to the power requirements of the drive units and to treat each battery passively. Each electrical converter is connected to each battery via a respective junction including two metal-oxide-semiconductor field-effect transistors connected in series and of opposite forward directions. Each junction can operate exclusively according to a unidirectional state in which the current flows from the electrical converter to the battery, a bidirectional state, and a blocking state.
1 . A hybrid powered aircraft comprising:
at least two drive units each comprising a propulsion unit and an electric motor,
at least one stored electrical energy source arranged to provide electrical energy to one or more of the electric motors,
at least one electrical generation source comprising a fuel-based electrical energy generator and connected to each stored electrical energy source, and
a power supply control device arranged to output a power command to the at least one electrical generation source according to the power requirements of the drive units, the at least one stored electrical energy source being arranged to provide electrical energy according to a difference between the power requirements of the drive units and power provided by the at least one electrical generation source on the basis of the power command, the at least one electrical generation source being further configured to recharge the at least one stored electrical energy source such that each stored electrical energy source is treated passively,
wherein each electrical generation source comprises at least one electrical converter, which is connected to each stored electrical energy source via a respective junction including:
a first metal-oxide-semiconductor field-effect transistor and a second metal-oxide-semiconductor field-effect transistor connected in series and of opposite forward directions, or
two electrical circuits each comprising an insulated-gate bipolar transistor and a reverse diode connected in parallel, the two electrical circuits being connected in series and of opposite forward directions,
and wherein the power supply control device is arranged to control the operation of each junction according to a set of states consisting of: a unidirectional state in which a current flows from the electrical converter to the stored electrical energy source, a bidirectional state in which the current flows in both directions, and a blocking state in which the flow of the current is blocked.
2 . The aircraft according to claim 1 , wherein the first metal-oxide-semiconductor field-effect transistor and the second metal-oxide-semiconductor field-effect transistor of at least one junction are made of silicon carbide.
3 . The aircraft according to claim 1 , wherein at least one junction further comprises an electronic component comprising a resistor connected in series with:
a metal-oxide-semiconductor field-effect transistor, or
an electrical circuit comprising an insulated-gate bipolar transistor and a reverse diode connected in parallel,
said electronic component being arranged to allow precharging of the corresponding stored electrical energy source.
4 . The aircraft according to claim 1 , wherein at least one stored electrical energy source is a battery.
5 . The aircraft according to claim 1 , wherein the drive units comprise at least one take-off drive unit and at least one cruise drive unit.
6 . The aircraft according to claim 5 , wherein at least one take-off drive unit is a vertical take-off and landing drive unit, and at least one cruise drive unit is a horizontal drive unit.
7 . The aircraft according to claim 1 , wherein the fuel-based electrical energy generator of at least one electrical generation source is a turbo engine, and wherein each electrical converter of said electrical generation source is an AC-DC converter.
8 . The aircraft according to claim 7 , wherein the turbo engine is powered by fuel, biofuel or synthetic fuel.
9 . The aircraft according to claim 1 , wherein the fuel-based electrical energy generator of at least one electrical generation source is a fuel cell, and wherein each electrical converter of said electrical generation source is a DC-DC converter.
10 . The aircraft according to claim 1 , configured to operate at least according to a turbo mode in which the power requirements of the drive units require a power supply from the at least one electrical generation source and the at least one stored electrical energy source, and in which the power supply control device controls each junction according to the unidirectional state.
11 . The aircraft according to claim 1 , configured to operate at least according to an energy-saving mode in which the power supply control device controls each junction according to the blocking state.
12 . The aircraft according to claim 1 , configured to operate at least according to a charging mode in which the power supply control device outputs a power command to the at least one electrical generation source to satisfy the power requirements of the drive units, while charging the at least one stored electrical energy source.
13 . The aircraft according to claim 12 , wherein, in the charging mode, the power supply control device sequentially controls each junction in one or more charging phases, the power supply control device being arranged to implement each charging phase by associating each electrical converter with a respective stored electrical energy source controlling each junction between an electrical converter and an associated stored electrical energy source according to the unidirectional state, and controlling any other junction according to the blocking state, until each stored electrical energy source is charged.
14 . The aircraft according to claim 12 , comprising a plurality of stored electrical energy sources, and wherein, in the charging mode, the power supply control device sequentially controls each junction in one or more charging phases, the power supply control device being arranged to implement each charging phase by associating each electrical converter with several respective stored electrical energy sources, controlling each junction between an electrical converter and an associated stored electrical energy source according to the bidirectional state, and controlling any other junction according to the blocking state, until each stored electrical energy source is charged.
15 . The aircrafts according to claim 1 , configured to operate at least according to a buffer mode in which the power supply control device transmits a power command to the at least one electrical generation source in order to satisfy the power requirements of the drive units via the at least one stored electrical energy source, and in which the power supply control device sequentially controls each junction in one or more power phases, the power supply control device being arranged to implement each power phase by associating each electrical converter with a respective stored electrical energy source, controlling each junction between an electrical converter and an associated stored electrical energy source according to the unidirectional state, and controlling any other junction according to the blocking state, until the power requirements of the drive units are satisfied.