CN115360775A - Equipment power supply system of aircraft and aircraft - Google Patents

Equipment power supply system of aircraft and aircraft Download PDF

Info

Publication number
CN115360775A
CN115360775A CN202211061926.2A CN202211061926A CN115360775A CN 115360775 A CN115360775 A CN 115360775A CN 202211061926 A CN202211061926 A CN 202211061926A CN 115360775 A CN115360775 A CN 115360775A
Authority
CN
China
Prior art keywords
power
management unit
voltage
power supply
unit
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN202211061926.2A
Other languages
Chinese (zh)
Inventor
胡华智
谢惠鹏
刘勇
陈星敏
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Ehang Intelligent Equipment Guangzhou Co Ltd
Original Assignee
Ehang Intelligent Equipment Guangzhou Co Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Ehang Intelligent Equipment Guangzhou Co Ltd filed Critical Ehang Intelligent Equipment Guangzhou Co Ltd
Priority to CN202211061926.2A priority Critical patent/CN115360775A/en
Publication of CN115360775A publication Critical patent/CN115360775A/en
Priority to PCT/CN2023/111678 priority patent/WO2024046050A1/en
Pending legal-status Critical Current

Links

Images

Classifications

    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J4/00—Circuit arrangements for mains or distribution networks not specified as ac or dc
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
    • B64D27/02—Aircraft characterised by the type or position of power plant
    • B64D27/24—Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D47/00—Equipment not otherwise provided for
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
    • H02J7/0013—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries acting upon several batteries simultaneously or sequentially
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
    • H02J7/0029—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with safety or protection devices or circuits
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
    • H02J7/0063—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with circuits adapted for supplying loads from the battery
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J9/00—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting
    • H02J9/005—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting using a power saving mode
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J9/00—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting
    • H02J9/04—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source
    • H02J9/06—Circuit arrangements for emergency or stand-by power supply, e.g. for emergency lighting in which the distribution system is disconnected from the normal source and connected to a standby source with automatic change-over, e.g. UPS systems
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D2221/00—Electric power distribution systems onboard aircraft

Abstract

The invention discloses an aircraft and a device power supply system thereof, wherein the system comprises: the power supply management system comprises a first power supply management unit, a second power supply management unit, a third power supply management unit and a power supply control unit, wherein the first power supply management unit, the second power supply management unit, the third power supply management unit and the power supply control unit are connected to a controller area network bus, the second power supply management unit and the power supply control unit form a first power supply distribution unit, and the third power supply management unit and the power supply control unit form a second power supply distribution unit. The invention realizes an equipment power supply scheme with better power supply safety, on one hand, the safe equipment power supply can still be provided for the aircraft when partial parts of the aircraft have faults, on the other hand, the risks possibly existing during the power conversion and the battery self can be fed back in time, and an active and effective processing way is provided for the emergency risk avoidance during the power supply of the aircraft.

Description

Equipment power supply system of aircraft and aircraft
Technical Field
The invention relates to the technical field of aircrafts, in particular to an aircraft and a device power supply system thereof.
Background
At present, aircrafts such as unmanned aerial vehicles and the like are increasingly widely applied, and the aircrafts can be applied to scenes such as aerial photographing, aerial camera shooting, aerial logistics transportation and aerial passenger carrying flight.
However, the existing aircraft generally adopts a single cell design, and the design scheme has two problems, namely, the endurance of the aircraft cannot be accurately estimated, and other risks possibly existing in the single cell cannot be effectively predicted. Based on this, when insufficient endurance or unexpected failure occurs due to the single battery problem, the aircraft will lose power and control capability, and eventually will cause a crash event.
In summary, under the condition that the main power supply fails, how to avoid the loss of power and control capability of the aircraft without affecting the safe flight or landing safety of the aircraft becomes a technical problem to be solved urgently.
Disclosure of Invention
In order to solve the above technical drawbacks of the prior art, the present invention proposes an aircraft equipment power supply system, comprising:
the power supply control device comprises a first power supply management unit, a second power supply management unit, a third power supply management unit and a power supply control unit which are connected to a controller area network bus, wherein the second power supply management unit and the power supply control unit form a first power supply distribution unit, and the third power supply management unit and the power supply control unit form a second power supply distribution unit; wherein the content of the first and second substances,
the first power supply management unit is used for supplying power to the central control unit;
the first power distribution unit is used for supplying power to the holder, the radar altimeter, the airborne router, the bus recorder and the cabin display unit;
the first power distribution unit and the second power distribution unit jointly supply power to a plurality of sets of power battery assemblies, a plurality of groups of flight control units, a magnetic compass unit and a barometer unit;
the controller area network bus is used for reporting current information, voltage information and state information.
Optionally, the second power management unit is connected in parallel with the power control unit;
when the power electricity is not started, the first power supply distribution unit is independently powered by the second power supply management unit;
when the power electricity is started, if the voltage of the second power management unit is higher than the voltage of the power control unit, the second power management unit supplies power independently, when the voltage of the second power management unit is reduced to be consistent with the voltage of the power control unit, the second power management unit and the power control unit supply power together, and when the voltage of the second power management unit is reduced to be lower than the voltage of the power control unit, the power control unit supplies power independently;
when the power electricity is started, if the voltage of the second power management unit is lower than the voltage of the power control unit, the power control unit supplies power independently, so that the second power management unit reserves electric energy for supplying power in an abnormal state.
Optionally, the third power management unit is connected in parallel with the power control unit;
when the power supply is not started, the second power supply distribution unit is independently powered by the third power supply management unit;
when the power electricity is started, if the voltage of the third power management unit is higher than that of the power control unit, the third power management unit supplies power independently, when the voltage of the third power management unit is reduced to be consistent with that of the power control unit, the third power management unit and the power control unit supply power together, and when the voltage of the third power management unit is reduced to be lower than that of the power control unit, the power control unit supplies power independently;
when the power electricity is started, if the voltage of the third power management unit is lower than the voltage of the power control unit, the power control unit supplies power alone, so that the third power management unit retains electric energy for supplying power in an abnormal state.
Optionally, the multiple sets of power battery assemblies, the multiple sets of flight control units, the magnetic compass unit and the barometer unit are used as a first set of electric equipment; the cradle head, the radar altimeter, the airborne router, the bus recorder and the cabin display unit are used as a second group of electric equipment;
and regulating and controlling the power supply relation of the first group of electric equipment and the second group of electric equipment according to the voltage relation of the second power management unit, the third power management unit and the power control unit.
Optionally, when the voltage relationship is that the voltage of the third power management unit is higher than the voltage of the second power management unit, and the voltage of the second power management unit is higher than the voltage of the power control unit, the power supply relationship is:
providing power to the first set of powered devices by the third power management unit;
providing power to the second group of powered devices by the second power management unit;
the power control unit does not supply power.
Optionally, when the voltage relationship is that the voltage of the third power management unit is higher than the voltage of the power control unit, and the voltage of the power control unit is higher than the voltage of the second power management unit, the power supply relationship is:
providing power to the first set of powered devices by the third power management unit;
supplying power to the second group of powered devices by the power control unit;
the second power management unit does not supply power.
Optionally, when the voltage relationship is that the voltage of the third power management unit is higher than the voltage of the second power management unit, and the voltage of the second power management unit is equal to the voltage of the power control unit, the power supply relationship is:
providing power to the first set of powered devices by the third power management unit;
and the second power management unit and the power control unit jointly supply power to the second group of electric equipment.
Optionally, when the voltage relationship is that the voltage of the second power management unit is higher than the voltage of the third power management unit and higher than the voltage of the power control unit, the power supply relationship is:
providing, by the second power management unit, power to both the first set of powered devices and the second set of powered devices;
the third power management unit and the power control unit do not supply power.
Optionally, when the voltage relationship is that the voltage of the power control unit is higher than the voltage of the second power management unit and higher than the voltage of the third power management unit, the power supply relationship is:
supplying power to the first set of electrical devices and the second set of electrical devices collectively by the power control unit;
the second power management unit and the third power management unit do not supply power.
Optionally, when the voltage relationship is that the voltage of the power control unit is equal to the voltage of the second power management unit and equal to the voltage of the third power management unit, the power supply relationship is:
the second power management unit, the third power management unit, and the power control unit collectively supply power to the first group of electrical devices and the second group of electrical devices.
The invention also provides an aircraft which comprises a charging seat auxiliary power supply pin, wherein the first power supply management unit, the second power supply management unit and the third power supply management unit are respectively connected to the charging seat auxiliary power supply pin;
when the first power management unit, the second power management unit and the third power management unit are connected to an external charger, the auxiliary power pin of the charger outputs electric energy to the first power management unit PMU1, the second power management unit PMU2 and the third power management unit PMU 3;
the aircraft further comprises a device power supply system implementing the aircraft as defined in any one of the above.
The aircraft power supply system comprises a first power supply management unit, a second power supply management unit, a third power supply management unit and a power supply control unit which are connected to a controller area network bus, wherein the second power supply management unit and the power supply control unit form a first power supply distribution unit, and the third power supply management unit and the power supply control unit form a second power supply distribution unit; the first power supply management unit is used for supplying power to the central control unit; the first power distribution unit is used for supplying power to the holder, the radar altimeter, the airborne router, the bus recorder and the cabin display unit; the first power distribution unit and the second power distribution unit jointly supply power to a plurality of sets of power battery assemblies, a plurality of groups of flight control units, a magnetic compass unit and a barometer unit; the controller area network bus is used for reporting current information, voltage information and state information. The invention realizes an equipment power supply scheme with better power supply safety, on one hand, the safe equipment power supply can still be provided for the aircraft when partial parts of the aircraft have faults, on the other hand, the risks possibly existing during the power conversion and the battery self can be fed back in time, and an active and effective processing way is provided for the emergency risk avoidance during the power supply of the aircraft.
Drawings
The invention will be further described with reference to the accompanying drawings and examples, in which:
fig. 1 is a block diagram of a first embodiment of the aircraft equipment power system method of the present invention.
Detailed Description
It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
In the following description, suffixes such as "module", "component", or "unit" used to denote elements are used only for facilitating the explanation of the present invention, and have no specific meaning in itself. Thus, "module", "component" or "unit" may be used mixedly.
In the following description, the relevant abbreviations are explained as follows:
and the ALLCAN is connected with a CAN bus of the equipment such as a flight control system, a power battery assembly, a power management unit and the like.
PMU, power management Unit, power management Unit.
PCU, power Control Unit.
PDU, power Distribution Unit.
CCU, centre Control Uint, central Control unit.
FCU, flight Control Unit.
CBU, compass & Barometer Unit, magnetic Compass Unit and Barometer Unit.
Example one
Fig. 1 is a block diagram of a first embodiment of the device power supply system of the aircraft of the present invention. This embodiment proposes an equipment power supply system of an aircraft, the system comprising:
a first power management unit PMU1, a second power management unit PMU2, a third power management unit PMU3 and a power control unit PCU connected to a controller area network bus ALLCAN, the second power management unit PMU2 and the power control unit PCU constituting a first power distribution unit PDU1, the third power management unit PMU3 and the power control unit PCU constituting a second power distribution unit PDU2; wherein the content of the first and second substances,
the first power management unit PMU1 is used for supplying power to the CCU;
the first power distribution unit PDU1 is used for supplying power to the holder, the radar altimeter, the airborne router, the bus recorder and the cabin display unit;
the first power distribution unit PDU1 and the second power distribution unit PDU2 jointly supply power to a plurality of sets of power battery assemblies, a plurality of sets of flight control units FCUs, a magnetic compass unit and a barometer unit;
the controller area network bus ALLCAN is used for reporting current information, voltage information and state information.
In this embodiment, the first power management unit PMU1, the second power management unit PMU2, and the third power management unit PMU3 are respectively connected to a charging stand auxiliary power pin, and the charging stand auxiliary power pin is configured to provide electric energy to the first power management unit PMU1, the second power management unit PMU2, and the third power management unit PMU 3.
In this embodiment, the first power management unit PMU1, the second power management unit PMU2, and the third power management unit PMU3 support a power-on signal generated by an external touch or an external key, respectively, to perform on-output of the corresponding units.
In this embodiment, the first power management unit PMU1, the second power management unit PMU2, the third power management unit PMU3, and the power control unit PCU are respectively connected to a controller area network bus ALLCAN, and configured to collect and transmit current information, voltage information, and state information currently reported by the power supply device.
In this embodiment, the first power management unit PMU1, the second power management unit PMU2, the third power management unit PMU3, the power control unit PCU, the first power distribution unit PDU1, and the second power distribution unit PDU2 are all power supply devices; the central control unit CCU, the cloud platform, the radar altimeter, the airborne router, the bus recorder, the cabin display unit, the multiple sets of power battery components, the multiple sets of flight control units FCU, the magnetic compass unit and the barometer unit are all power supply equipment.
In this embodiment, the multiple sets of power battery packs, the multiple sets of flight control units FCUs, the magnetic compass unit, and the barometer unit are key system devices of the aircraft, and therefore, in order to improve the safety of such devices, the first power distribution unit PDU1 and the second power distribution unit PDU2 are used to supply power to such key system devices together.
In this embodiment, since the first power distribution unit PDU1 is supplied by the second power management unit PMU2 and the power control unit PCU, the second power distribution unit PDU2 is supplied by the third power management unit PMU3 and the power control unit PCU. Therefore, the above-mentioned key system device is powered by the second power management unit PMU2, the third power management unit PMU3, and the power control unit PCU together, that is, the final power sources of the above-mentioned key system device are the second power management unit PMU2, the third power management unit PMU3, and the power control unit PCU.
In the present embodiment, referring to table 1, the power supply requirements of each critical system device in an aircraft are shown.
Device Voltage Range (VDC) Rated input Voltage (VDC) Power (W)
FCU-1 18～35 24 5
FCU2+CBU 18～35 24 7
FCU3 18～35 24 5.6
Battery pack 1 to 12 10～30 24 3.8
Cloud platform 18～35 24 28
Radar altimeter 9～36 24 1.8
Airborne router 9～36 24 7
Bus recorder 18～35 24 2.8
Cockpit display assembly 18～35 24 14
Total up to 18～30 24 116.8
TABLE 1
In table 1, both the second power management unit PMU2 and the third power management unit PMU3 can output voltages of 18 to 25.2V and can output currents of 35A, that is, can output power of about 777W.
In table 1, the power supply control unit PCU can supply a power supply of 24V voltage, 135W power.
Considering the need to provide 18-30V power to the critical electrical devices in table 1, the overall power consumption of each device was 116.8W. Therefore, when all the above-mentioned key system devices are in normal operation, the power supply of the device power supply system of this embodiment can meet the current power consumption voltage requirement and power consumption power requirement.
Further, considering that the powers of the second power management unit PMU2, the third power management unit PMU3 and the power control unit PCU are all greater than the power demands of the above-mentioned key devices, in this embodiment, even if any two of the second power management unit PMU2, the third power management unit PMU3 and the power control unit PCU fail at the same time, the remaining one power supply device can satisfy the power demands of all other key devices.
Optionally, the battery pack energy of the second power management unit PMU2 and the third power management unit PMU3 of this embodiment are 488.4Wh, and based on this, even if the above-mentioned alternative alone supplies power to the above-mentioned electrical key device, the power supply can be maintained for 4.2 hours continuously, which is enough to meet the power supply requirement of the aircraft during the endurance time.
The beneficial effect of this embodiment is that by proposing an aircraft equipment power supply system, this system includes first power management unit PMU1, second power management unit PMU2, third power management unit PMU3 and power control unit PCU connected to controller area network bus ALLCAN, and the second power management unit PMU2 and the power control unit PCU constitute first power distribution unit PDU1, and the third power management unit PMU3 and the power control unit PCU constitute second power distribution unit PDU2; the first power management unit PMU1 is used for supplying power to a central control unit CCU; the first power distribution unit PDU1 is used for supplying power to the holder, the radar altimeter, the airborne router, the bus recorder and the cabin display unit; the first power distribution unit PDU1 and the second power distribution unit PDU2 jointly supply power to a plurality of sets of power battery assemblies, a plurality of sets of Flight Control Units (FCUs), a magnetic compass unit and a barometer unit; the controller area network bus ALLCAN is used for reporting current information, voltage information and state information. The embodiment realizes an equipment power supply scheme with better power supply safety, on one hand, the equipment power supply can still be provided for the aircraft when partial parts of the aircraft break down, on the other hand, risks possibly existing during battery self and power conversion can be fed back in time, and a positive and effective processing way is provided for emergency risk avoidance during power supply of the aircraft.
Example two
Based on the above embodiments, in this embodiment, the output of the second power management unit PMU2 and the output of the power control unit PCU are connected in parallel through a diode, so as to implement power input backup and seamless switching.
In this embodiment, a backflow prevention circuit is provided in the second power management unit PMU2 and the power control unit PCU. When power control unit PCU short circuit, second power management unit PMU2 can supply power for first power distribution unit PDU1, and simultaneously, avoid second power management unit PMU 2's electric energy to flow backward to power control unit PCU through first power distribution unit PDU1 to avoid first power distribution unit PDU 1's the whole inefficacy of power supply.
In this embodiment, based on the above anti-backflow circuit, when the second power management unit PMU2 is in a short circuit, the power control unit PCU can supply power to the first power distribution unit PDU1, and due to the presence of the diode and the anti-backflow circuit, it is possible to prevent the electric power of the power control unit PCU from flowing backward to the second power management unit PMU2 through the first power distribution unit PDU1, thereby preventing the power supply of the first power distribution unit PDU1 from being wholly disabled.
In this embodiment, please refer to table 2, which shows the power and current of the load device connected to the first power distribution unit PDU 1.
Device Rated input Voltage (VDC) Power (W) 24V input current (A)
FCU-1 24 5 0.21
FCU2+CBU 24 7 0.29
FCU3 24 5.6 0.23
Battery pack 1 to 12 24 3.8 0.16
Cloud platform 24 28 1.17
Radar altimeter 24 1.8 0.08
Airborne router 24 7 0.29
Bus recorder 24 2.8 0.12
Cockpit display assembly 24 14 0.58
Total up to 116.8 4.89
TABLE 2
In table 2, the total power of all load devices connected to the first power distribution unit PDU1, which is smaller than the output power of the power control unit PCU 135W, can be calculated to be 116.8W. At the same time, the total current of all load devices on the first power distribution unit PDU1 is considered to be 4.89A, which is also much smaller than the output capability of 35A of the second power management unit PMU 2. Therefore, if the second power management unit PMU2 or the power control unit PCU fails, it can be ensured that the power supply requirements of all load devices of the first power distribution unit PDU1 can be met.
In this embodiment, when the power supply is not turned on, the first power distribution unit PDU1 is separately powered by the second power management unit PMU 2.
In this embodiment, when the power supply is turned on, if the voltage of the second power management unit PMU2 is higher than the voltage of the power control unit PCU, the second power management unit PMU2 supplies power alone, and when the voltage of the second power management unit PMU2 decreases to coincide with the voltage of the power control unit PCU, the second power management unit PMU2 supplies power in common with the power control unit PCU, and when the voltage of the second power management unit PMU2 decreases to be lower than the voltage of the power control unit PCU, the power control unit PCU supplies power alone.
In this embodiment, when the power supply is turned on, if the voltage of the second power management unit PMU2 is lower than the voltage of the power control unit PCU, the power control unit PCU supplies power alone, so that the second power management unit PMU2 retains electric energy for supplying power in an abnormal state.
In this embodiment, the output of the third power management unit PMU3 and the output of the power control unit PCU are also connected in parallel through a diode, thereby implementing power input backup and seamless switching.
In this embodiment, a backflow prevention circuit is provided in the third power management unit PMU3 and the power control unit PCU. When power control unit PCU short circuit, third power management unit PMU3 can supply power for second power distribution unit PDU2, and simultaneously, avoid third power management unit PMU 3's electric energy to flow backward to power control unit PCU through second power distribution unit PDU2 to avoid the whole inefficacy of power supply of second power distribution unit PDU 2.
In this embodiment, based on the above anti-backflow circuit, when the third power management unit PMU3 is in a short circuit, the power control unit PCU can supply power to the second power distribution unit PDU2, and due to the presence of the diode and the anti-backflow circuit, it is possible to prevent the electric power of the power control unit PCU from flowing backward to the third power management unit PMU3 through the second power distribution unit PDU2, thereby preventing the power supply of the second power distribution unit PDU2 from being wholly disabled.
In this embodiment, please refer to table 3, which shows the power and current of the load device to which the first power distribution unit PDU1 is connected.
Device Rated input Voltage (VDC) Power (W) 24V input current (A)
FCU-1 24 5 0.21
FCU2+CBU 24 7 0.29
FCU3 24 5.6 0.23
Battery pack 1 to 12 24 3.8 0.16
Is totaled 63.2 2.65
TABLE 3
In table 3, the total power of all load devices connected to the second power distribution unit PDU2, which is smaller than the output power of the power control unit PCU 135W, can be calculated to be 63.2W. At the same time, the total current of all load devices on the second power distribution unit PDU2 is considered to be 2.65A, which is also much smaller than the 35A output capability of the third power management unit PMU 3. Therefore, in case of a failure of the third power management unit PMU3 or the power control unit PCU, it is ensured that the power supply requirements of all load devices connected to the second power distribution unit PDU2 can be met.
In this embodiment, when the power supply is not turned on, the second power distribution unit PDU2 is separately powered by the third power management unit PMU 3.
In this embodiment, when the power supply is turned on, if the voltage of the third power management unit PMU3 is higher than the voltage of the power control unit PCU, the third power management unit PMU3 supplies power alone, and when the voltage of the third power management unit PMU3 decreases to coincide with the voltage of the power control unit PCU, the third power management unit PMU3 supplies power in common with the power control unit PCU, and when the voltage of the third power management unit PMU3 decreases to be lower than the voltage of the power control unit PCU, the power control unit PCU supplies power alone.
In this embodiment, when the power supply is turned on, if the voltage of the third power management unit PMU3 is lower than the voltage of the power control unit PCU, power is supplied by the power control unit PCU alone, so that the third power management unit PMU3 retains electric energy for supplying power in an abnormal state.
EXAMPLE III
In this embodiment, as can be seen from the power supply schemes of the first power distribution unit PDU1 and the second power distribution unit PDU2 in the second embodiment, when the power supply is turned on, a fault occurs in any one of the power supply devices of the second power management unit PMU2, the third power management unit PMU3, and the power control unit PCU, which can ensure that the first power distribution unit PDU1 and the second power distribution unit PDU2 supply power normally.
In the present embodiment, the first power distribution unit PDU1 and the second power distribution unit PDU2 are used to supply power to 12 sets of power battery modules of the FCU flight control unit in common, taking into account the importance of multiple sets of battery modules. Based on this, when the second power management unit PMU2, the third power management unit PMU3, and the power control unit PCU are all in a normal operating state, the relation of power supply to each load device depends on the voltages of the second power management unit PMU2 and the third power management unit PMU 3.
Therefore, in this embodiment, the multiple sets of power battery assemblies, the multiple sets of flight control units FCUs, the magnetic compass unit, and the barometer unit are used as a first set of electric devices; the cradle head, the radar altimeter, the airborne router, the bus recorder and the cabin display unit are used as a second group of electric equipment; and regulating and controlling the power supply relation of the first group of electric equipment and the second group of electric equipment according to the voltage relation of the second power management unit PMU2, the third power management unit PMU3 and the power control unit PCU. Specifically, please refer to table 4, which shows the power supply relationship and the power supply current of each load device.
Figure BDA0003826621490000121
TABLE 4
As shown in the voltage relation 1 in table 4, in this embodiment, when the voltage relation is that the voltage of the third power management unit PMU3 is higher than the voltage of the second power management unit PMU2, and the voltage of the second power management unit PMU2 is higher than the voltage of the power control unit PCU, the power supply relation is:
supplying power to the first group of electrical devices by the third power management unit PMU 3;
supplying power to the second group of electrical devices by the second power management unit PMU 2;
the power control unit PCU is not powered.
As shown in the voltage relation 2 in table 4, in this embodiment, when the voltage relation is that the voltage of the third power management unit PMU3 is higher than the voltage of the power control unit PCU and the voltage of the power control unit PCU is higher than the voltage of the second power management unit PMU2, the power supply relation is:
supplying power to the first group of electrical devices by the third power management unit PMU 3;
supplying power to the second group of electrical devices by the power control unit PCU;
the second power management unit PMU2 does not supply power.
As shown in voltage relation 3 in table 4, in this embodiment, when the voltage relation is that the voltage of the third power management unit PMU3 is higher than the voltage of the second power management unit PMU2, and the voltage of the second power management unit PMU2 is equal to the voltage of the power control unit PCU, the power supply relation is:
supplying power to the first group of electrical devices by the third power management unit PMU 3;
said second group of consumers is supplied with power jointly by said second power management unit PMU2 and said power control unit PCU.
As shown in table 4, voltage relation 5, and voltage relation 6, in this embodiment, when the voltage relations are that the voltage of the second power management unit PMU2 is higher than the voltage of the third power management unit PMU3 and higher than the voltage of the power control unit PCU, the voltage of the third power management unit PMU3 is higher than the voltage of the power control unit PCU, or the voltage of the third power management unit PMU3 is lower than the voltage of the power control unit PCU, or the voltage of the third power management unit PMU3 is equal to the voltage of the power control unit PCU, the power supply relation is:
-supplying power jointly to said first group of electrical consumers and to said second group of electrical consumers by said second power management unit PMU 2;
the third power management unit PMU3 and the power control unit PCU are not powered.
As shown in table 4, in voltage relations 7, 8, and 9, in this embodiment, when the voltage relation is that the voltage of the power control unit PCU is higher than the voltage of the second power management unit PMU2 and higher than the voltage of the third power management unit PMU3, the voltage of the second power management unit PMU2 is higher than the voltage of the third power management unit PMU3, or the voltage of the second power management unit PMU2 is lower than the voltage of the third power management unit PMU3, or the voltage of the second power management unit PMU2 is equal to the voltage of the third power management unit PMU3, the power supply relation is:
supplying power to the first and second groups of electrical devices collectively by the power control unit PCU;
the second power management unit PMU2 and the third power management unit PMU3 do not supply power.
As shown in table 4, in the present embodiment, when the voltage relationship is that the voltage of the power control unit PCU is equal to the voltage of the second power management unit PMU2 and equal to the voltage of the third power management unit PMU3, the power supply relationship is:
the first and second groups of electrical consumers are supplied by the second power management unit PMU2, the third power management unit PMU3 and the power control unit PCU in common.
Example four
In this embodiment, the power-on signal lines of the first power management unit PMU1, the second power management unit PMU2, and the third power management unit PMU3 are connected in parallel, and the power-on signal line is connected to the power-on button of the cockpit display unit. For example, if the power-on button is pressed for more than 1 second, the first power management unit PMU1, the second power management unit PMU2, and the third power management unit PMU3 all turn on the discharge switches, and start discharging to the outside. At this point, all load devices, including the flight control system and the power cell assembly, have begun to operate. Alternatively, the power electricity is turned on by a power electricity device button on the ground control station, or the cockpit display unit. After the power supply is turned on, the power supply control unit PCU starts to work to provide power utilization backup for the whole equipment power supply system.
In this embodiment, when the aircraft needs to be shut down, first, a command to shut down the power supply is issued by the ground control station, then, when the power supply is shut down, the power supply control unit PCU immediately stops outputting, and finally, a command to shut down the first power supply management unit PMU1, the second power supply management unit PMU2, and the third power supply management unit PMU3 is issued by the ground control station, and the outputs of the first power supply management unit PMU1, the second power supply management unit PMU2, and the third power supply management unit PMU3 are shut down.
In this embodiment, the power supply shutdown command and the shutdown commands of the first power management unit PMU1, the second power management unit PMU2, and the third power management unit PMU3 are divided into two, that is, a second identical command is received as an effective command within a preset time period (for example, 3 seconds) after the first command is received, so as to reduce the possibility that the power supply or the power management unit is shutdown by mistake.
EXAMPLE five
Based on the above embodiment, the present invention further provides an aircraft, where the aircraft includes a charging-dock auxiliary power pin, and the first power management unit PMU1, the second power management unit PMU2, and the third power management unit PMU3 are connected to the charging-dock auxiliary power pin, respectively.
When the first power management unit PMU1, the second power management unit PMU2 and the third power management unit PMU3 are connected to an external charger, the auxiliary power pin of the charger outputs electric energy to the first power management unit PMU1, the second power management unit PMU2 and the third power management unit PMU 3.
The aircraft further comprises a device power supply system implementing the aircraft as defined in any one of the above.
It should be noted that the aircraft embodiment and the system embodiment belong to the same concept, and specific implementation processes thereof are detailed in the system embodiment, and technical features in the system embodiment are correspondingly applicable in the aircraft embodiment, which is not described herein again.
It should be noted that, in this document, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one of 8230, and" comprising 8230does not exclude the presence of additional like elements in a process, method, article, or apparatus comprising the element.
The above-mentioned serial numbers of the embodiments of the present invention are only for description, and do not represent the advantages and disadvantages of the embodiments.
Through the description of the foregoing embodiments, it is clear to those skilled in the art that the method of the foregoing embodiments may be implemented by software plus a necessary general hardware platform, and certainly may also be implemented by hardware, but in many cases, the former is a better implementation. Based on such understanding, the technical solutions of the present invention may be embodied in the form of a software product, which is stored in a storage medium (such as ROM/RAM, magnetic disk, optical disk) and includes instructions for enabling a terminal (such as a mobile phone, a computer, a server, an air conditioner, or a network device) to execute the method according to the embodiments of the present invention.
While the present invention has been described with reference to the particular illustrative embodiments, it is to be understood that the invention is not limited to the disclosed embodiments, but is intended to cover various modifications, equivalent arrangements, and equivalents thereof, which may be made by those skilled in the art without departing from the spirit and scope of the invention as defined by the appended claims.

Claims (11)

1. An equipment power system method for an aircraft, the system comprising: the power supply management system comprises a first power supply management unit, a second power supply management unit, a third power supply management unit and a power supply control unit, wherein the first power supply management unit, the second power supply management unit, the third power supply management unit and the power supply control unit are connected to a controller area network bus; wherein the content of the first and second substances,
the first power supply management unit is used for supplying power to the central control unit;
the first power distribution unit is used for supplying power to the holder, the radar altimeter, the airborne router, the bus recorder and the cabin display unit;
the first power distribution unit and the second power distribution unit jointly supply power to a plurality of sets of power battery assemblies, a plurality of groups of flight control units, a magnetic compass unit and a barometer unit;
the controller area network bus is used for reporting current information, voltage information and state information.
2. The aircraft equipment power system method of claim 1, wherein the second power management unit is connected in parallel with the power control unit;
when the power electricity is not started, the first power supply distribution unit is independently powered by the second power supply management unit;
when the power electricity is started, if the voltage of the second power management unit is higher than the voltage of the power control unit, the second power management unit supplies power independently, when the voltage of the second power management unit is reduced to be consistent with the voltage of the power control unit, the second power management unit and the power control unit supply power together, and when the voltage of the second power management unit is reduced to be lower than the voltage of the power control unit, the power control unit supplies power independently;
when the power electricity is started, if the voltage of the second power management unit is lower than the voltage of the power control unit, the power control unit supplies power independently, so that the second power management unit reserves electric energy for supplying power in an abnormal state.
3. The aircraft equipment power system method of claim 1 wherein said third power management unit is connected in parallel with said power control unit;
when the power supply is not started, the second power supply distribution unit is independently powered by the third power supply management unit;
when the power electricity is started, if the voltage of the third power management unit is higher than that of the power control unit, the third power management unit supplies power independently, when the voltage of the third power management unit is reduced to be consistent with that of the power control unit, the third power management unit and the power control unit supply power together, and when the voltage of the third power management unit is reduced to be lower than that of the power control unit, the power control unit supplies power independently;
when the power electricity is started, if the voltage of the third power management unit is lower than the voltage of the power control unit, the power control unit supplies power alone, so that the third power management unit retains electric energy for supplying power in an abnormal state.
4. The aircraft equipment power supply system method of claim 1, wherein the plurality of power battery packs, the plurality of sets of flight control units, the magnetic compass unit, and the barometer unit are provided as a first set of powered equipment; taking the cradle head, the radar altimeter, the airborne router, the bus recorder and the cabin display unit as a second group of electric equipment;
and regulating and controlling the power supply relation of the first group of electric equipment and the second group of electric equipment according to the voltage relation of the second power supply management unit, the third power supply management unit and the power supply control unit.
5. The aircraft equipment power system method according to claim 4, wherein when the voltage relationship is that the voltage of the third power management unit is higher than the voltage of the second power management unit and the voltage of the second power management unit is higher than the voltage of the power control unit, the power supply relationship is:
providing power to the first set of powered devices by the third power management unit;
providing power to the second set of powered devices by the second power management unit;
the power control unit does not supply power.
6. The aircraft equipment power supply system method according to claim 4, wherein when the voltage relationship is that the voltage of the third power management unit is higher than the voltage of the power control unit and the voltage of the power control unit is higher than the voltage of the second power management unit, the power supply relationship is:
providing power to the first set of powered devices by the third power management unit;
supplying power to the second group of powered devices by the power control unit;
the second power management unit does not supply power.
7. The aircraft equipment power supply system method according to claim 4, wherein when the voltage relationship is that the voltage of the third power management unit is higher than the voltage of the second power management unit and the voltage of the second power management unit is equal to the voltage of the power control unit, the power supply relationship is:
providing power to the first set of powered devices by the third power management unit;
and the second power management unit and the power control unit jointly supply power to the second group of electric equipment.
8. The aircraft equipment power system method of claim 4 wherein when the voltage relationship is that the voltage of the second power management unit is higher than the voltage of the third power management unit and higher than the voltage of the power control unit, the power supply relationship is:
providing, by the second power management unit, power to the first set of powered devices and the second set of powered devices together;
the third power management unit and the power control unit do not supply power.
9. The aircraft equipment power system method of claim 4 wherein when the voltage relationship is that the voltage of the power control unit is higher than the voltage of the second power management unit and higher than the voltage of the third power management unit, the power supply relationship is:
supplying power to the first set of electrical devices and the second set of electrical devices collectively by the power control unit;
the second power management unit and the third power management unit do not supply power.
10. The aircraft equipment power system method according to claim 4, wherein when the voltage relationship is that the voltage of the power control unit is equal to the voltage of the second power management unit and equal to the voltage of the third power management unit, the power supply relationship is:
the second power management unit, the third power management unit, and the power control unit collectively supply power to the first group of electrical devices and the second group of electrical devices.
11. An aircraft is characterized by comprising a charging-seat auxiliary power supply pin, wherein the first power supply management unit, the second power supply management unit and the third power supply management unit are respectively connected to the charging-seat auxiliary power supply pin;
when the first power management unit, the second power management unit and the third power management unit are connected to an external charger, the auxiliary power pin of the charger outputs electric energy to the first power management unit PMU1, the second power management unit PMU2 and the third power management unit PMU 3;
the aircraft further comprising a device power supply system implementing the aircraft according to any one of claims 1 to 10.
CN202211061926.2A 2022-08-31 2022-08-31 Equipment power supply system of aircraft and aircraft Pending CN115360775A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
CN202211061926.2A CN115360775A (en) 2022-08-31 2022-08-31 Equipment power supply system of aircraft and aircraft
PCT/CN2023/111678 WO2024046050A1 (en) 2022-08-31 2023-08-08 Device power source system of aircraft, and aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202211061926.2A CN115360775A (en) 2022-08-31 2022-08-31 Equipment power supply system of aircraft and aircraft

Publications (1)

Publication Number Publication Date
CN115360775A true CN115360775A (en) 2022-11-18

Family

ID=84005202

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202211061926.2A Pending CN115360775A (en) 2022-08-31 2022-08-31 Equipment power supply system of aircraft and aircraft

Country Status (2)

Country Link
CN (1) CN115360775A (en)
WO (1) WO2024046050A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2024046050A1 (en) * 2022-08-31 2024-03-07 亿航智能设备（广州）有限公司 Device power source system of aircraft, and aircraft

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH0549177A (en) * 1991-08-09 1993-02-26 Fujitsu Ltd Battery voltage checking system
CN101552543B (en) * 2009-01-08 2012-02-29 广州金升阳科技有限公司 Multi-path input alternating/direct current hybrid power supply
CN113036894B (en) * 2019-12-25 2022-11-11 海鹰航空通用装备有限责任公司 Solar unmanned aerial vehicle electrical system architecture
US20210320519A1 (en) * 2020-04-09 2021-10-14 Delta Electronics, Inc. Power supply system and method of operating the same
CN113555948A (en) * 2021-06-26 2021-10-26 华为技术有限公司 Power supply control system, power supply control method, and communication device
CN115360775A (en) * 2022-08-31 2022-11-18 亿航智能设备（广州）有限公司 Equipment power supply system of aircraft and aircraft

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2024046050A1 (en) * 2022-08-31 2024-03-07 亿航智能设备（广州）有限公司 Device power source system of aircraft, and aircraft

Also Published As

Publication number Publication date
WO2024046050A1 (en) 2024-03-07

Similar Documents

Publication Publication Date Title
US8406936B1 (en) Modular battery network system with life-optimal power management
EP2408085B1 (en) Methods for aircraft emergency power management
US8820677B2 (en) Aircraft power systems and methods
EP2442425B1 (en) Electrical power control system for a vehicle.
CN104884349B (en) The management method of the electric power networks of aircraft
EP2850717B1 (en) Elevator backup power supply
EP1990892B1 (en) Battery discharge current sharing in a tightly regulated power system
US10468909B2 (en) Data center power systems with dynamic source designation
Lapena-Rey et al. Environmentally friendly power sources for aerospace applications
WO2006024005A2 (en) Electrical starting, generation, conversion and distribution system architecture for a more electric vehicle
US11214383B2 (en) Method and architecture for distributing on-board power in an aircraft
EP3691068B1 (en) Control system
US11472297B2 (en) Hybrid energy storage system
CN115360775A (en) Equipment power supply system of aircraft and aircraft
WO2018010592A1 (en) Redundancy power supply utilized in unmanned aerial vehicle system, power supply method thereof, and device utilizing same
US7071580B2 (en) Uninterruptible power supply apparatus
US20110204714A1 (en) Electric power supply system, in particular in an aircraft
RU2648233C2 (en) Method and system of power supply of the aircraft
JP2023103991A (en) Electric power conversion system and vehicle
CN109747848B (en) Unmanned aerial vehicle power supply assembly management system, management method and unmanned aerial vehicle
US11383855B2 (en) DC bus voltage input into RAT auto-deploy
CN110544933A (en) control method and device of distributed direct current power supply system
CN113193646A (en) Power supply device, method and system
WO2019020098A1 (en) Power supply system for fuel cell and fuel cell system
US20240083589A1 (en) Aircraft electrical system

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination