An aircraft electrical power system and an aircraft

Abstract

The application discloses an aircraft equipment power supply system and an aircraft, wherein the system comprises a first power management unit, a second power management unit, a third power management unit and a power control unit connected to a controller area network bus, the second power management unit and the power control unit constitute a first power distribution unit, and the third power management unit and the power control unit constitute a second power distribution unit. The application realizes an equipment power supply scheme with better power supply safety, on one hand, the aircraft can still be provided with safe equipment power supply when part of components of the aircraft fails, on the other hand, risks possibly existing during power conversion and the battery itself can be fed back in time, and an active and effective processing way is provided for emergency escape when the aircraft is powered.

Description

Technical Field

[0001] This invention relates to the field of aircraft technology, and more particularly to an aircraft power supply system and an aircraft. Background Technology

[0002] Currently, drones and other aircraft are being used more and more widely. These aircraft can be used for aerial photography, aerial videography, aerial logistics transportation, and passenger flights.

[0003] However, existing aircraft generally employ a single-battery design. This design presents two problems: first, it makes it impossible to accurately estimate the aircraft's range; second, it cannot effectively predict other potential risks associated with a single battery. Therefore, in cases of insufficient range or unexpected malfunctions due to single-battery issues, the aircraft will lose power and control, ultimately leading to a crash.

[0004] In conclusion, how to ensure the safe flight or landing of an aircraft without compromising its safety in the event of a main power failure, and how to prevent the aircraft from losing power and control, have become urgent technical problems that need to be solved. Summary of the Invention

[0005] To address the aforementioned technical deficiencies in the prior art, this invention proposes an equipment power system for an aircraft, comprising:

[0006] The system comprises a first power management unit, a second power management unit, a third power management unit, and a power control unit connected to the controller local area network (Controller Area Network) bus. The second power management unit and the power control unit constitute a first power distribution unit, and the third power management unit and the power control unit constitute a second power distribution unit.

[0007] The first power management unit is used to supply power to the central control unit;

[0008] The first power distribution unit is used to supply power to the gimbal, radar altimeter, airborne router, bus recorder and cockpit display unit;

[0009] The first power distribution unit and the second power distribution unit together supply power to multiple sets of power battery packs, multiple flight control units, magnetic compass units, and barometer units.

[0010] The controller local area network bus is used to report current current information, voltage information, and status information.

[0011] Optionally, the second power management unit is connected in parallel with the power control unit;

[0012] When the power supply is not turned on, the first power distribution unit is powered solely by the second power management unit;

[0013] When the power supply is turned on, if the voltage of the second power management unit is higher than the voltage of the power control unit, the second power management unit will supply power alone. When the voltage of the second power management unit drops to the same level as the voltage of the power control unit, the second power management unit and the power control unit will supply power together. When the voltage of the second power management unit drops to a level lower than the voltage of the power control unit, the power control unit will supply power alone.

[0014] When the power supply is turned on, if the voltage of the second power management unit is lower than the voltage of the power control unit, the power control unit will supply power separately so that the second power management unit can retain power for use in abnormal situations.

[0015] Optionally, the third power management unit is connected in parallel with the power control unit;

[0016] When the power supply is not turned on, the second power distribution unit is powered solely by the third power management unit;

[0017] When the power supply is turned on, if the voltage of the third power management unit is higher than the voltage of the power control unit, the third power management unit will supply power alone. When the voltage of the third power management unit drops to the same level as the voltage of the power control unit, the third power management unit and the power control unit will supply power together. When the voltage of the third power management unit drops to a level lower than the voltage of the power control unit, the power control unit will supply power alone.

[0018] When the power supply is turned on, if the voltage of the third power management unit is lower than the voltage of the power control unit, the power control unit will supply power separately so that the third power management unit can retain power for use in abnormal situations.

[0019] Optionally, the multiple sets of power battery components, the multiple flight control units, the magnetic compass unit, and the barometer unit are used as the first group of electrical equipment; the gimbal, the radar altimeter, the airborne router, the bus recorder, and the cockpit display unit are used as the second group of electrical equipment.

[0020] The power supply relationship between the first group of electrical devices and the second group of electrical devices is adjusted according to the voltage relationship between the second power management unit, the third power management unit, and the power control unit.

[0021] Optionally, when the voltage relationship is such 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:

[0022] The third power management unit supplies power to the first group of electrical devices;

[0023] The second power management unit supplies power to the second group of electrical devices;

[0024] The power control unit does not supply power.

[0025] Optionally, when the voltage relationship is such 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:

[0026] The third power management unit supplies power to the first group of electrical devices;

[0027] The power control unit supplies power to the second group of electrical devices;

[0028] The second power management unit does not supply power.

[0029] Optionally, when the voltage relationship is such 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:

[0030] The third power management unit supplies power to the first group of electrical devices;

[0031] The second power management unit and the power control unit jointly supply power to the second group of electrical devices.

[0032] Optionally, when the voltage relationship is such 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:

[0033] The second power management unit supplies power to both the first group of electrical devices and the second group of electrical devices.

[0034] The third power management unit and the power control unit do not supply power.

[0035] Optionally, when the voltage relationship is such 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:

[0036] The power control unit supplies power to both the first group of electrical devices and the second group of electrical devices.

[0037] The second power management unit and the third power management unit do not supply power.

[0038] Optionally, when the voltage relationship is such 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:

[0039] The second power management unit, the third power management unit, and the power control unit jointly supply power to the first group of electrical devices and the second group of electrical devices.

[0040] The present invention also proposes an aircraft, which includes a charging dock auxiliary power pin, wherein the first power management unit, the second power management unit, and the third power management unit are respectively connected to the charging dock auxiliary power pin;

[0041] 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 charging dock outputs electrical energy to the first power management unit PMU1, the second power management unit PMU2, and the third power management unit PMU3.

[0042] The aircraft also includes a power system for implementing the aircraft as described in any of the preceding claims.

[0043] The present invention discloses an equipment power system and an aircraft implementing an aircraft. The system includes a first power management unit, a second power management unit, a third power management unit, and a power control unit connected to a controller local area network (Controller Area Network) bus. The second power management unit and the power control unit constitute a first power distribution unit, and the third power management unit and the power control unit constitute a second power distribution unit. The first power management unit supplies power to the central control unit; the first power distribution unit supplies power to the gimbal, radar altimeter, airborne router, bus recorder, and cockpit display unit; the first and second power distribution units jointly supply power to multiple sets of power battery modules, multiple flight control units, a magnetic compass unit, and a barometer unit; the Controller Area Network bus is used to report current current information, voltage information, and status information. This invention provides a more secure equipment power supply solution. On the one hand, it can still provide safe equipment power to the aircraft when some components malfunction; on the other hand, it can provide timely feedback on potential risks related to the battery itself and power conversion, providing a proactive and effective approach for emergency risk avoidance during aircraft power supply. Attached Figure Description

[0044] The present invention will be further described below with reference to the accompanying drawings and embodiments. In the accompanying drawings:

[0045] Figure 1 This is a block diagram of the first embodiment of the device power system method for the aircraft of the present invention. Detailed Implementation

[0046] It should be understood that the specific embodiments described herein are for illustrative purposes only and are not intended to limit the scope of the invention.

[0047] In the following description, the use of suffixes such as "module," "part," or "unit" to denote elements is solely for the purpose of illustrative purposes and has no specific meaning in itself. Therefore, "module," "part," or "unit" may be used interchangeably.

[0048] The following descriptions explain the relevant abbreviations:

[0049] ALLCAN is a CAN bus that connects devices such as flight control systems, power battery packs, and power management units.

[0050] PMU, Power Management Unit.

[0051] PCU, Power Control Unit.

[0052] PDU, Power Distribution Unit.

[0053] CCU, Centre Control Unit.

[0054] FCU, Flight Control Unit.

[0055] CBU, Compass & Barometer Unit, magnetic compass unit and barometer unit.

[0056] Example 1

[0057] Figure 1 This is a block diagram of a first embodiment of the equipment power system for an aircraft according to the present invention. This embodiment proposes an equipment power system for an aircraft, the system comprising:

[0058] A first power management unit (PMU1), a second power management unit (PMU2), a third power management unit (PMU3), and a power control unit (PCU) are connected to the ALLCAN controller local area network bus. The second power management unit (PMU2) and the power control unit (PCU) form a first power distribution unit (PDU1), and the third power management unit (PMU3) and the power control unit (PCU) form a second power distribution unit (PDU2).

[0059] The first power management unit PMU1 is used to supply power to the central control unit CCU;

[0060] The first power distribution unit PDU1 is used to supply power to the gimbal, radar altimeter, airborne router, bus recorder and cockpit display unit;

[0061] The first power distribution unit PDU1 and the second power distribution unit PDU2 jointly supply power to multiple sets of power battery packs, multiple sets of flight control units (FCUs), magnetic compass units, and barometer units.

[0062] The ALLCAN controller local area network bus is used to report current current information, voltage information, and status information.

[0063] 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 the auxiliary power pin of the charging dock. The auxiliary power pin of the charging dock is used to provide power to the first power management unit PMU1, the second power management unit PMU2, and the third power management unit PMU3.

[0064] In this embodiment, the first power management unit PMU1, the second power management unit PMU2, and the third power management unit PMU3 respectively support power-on signals generated by external touch or external buttons to execute the power-on output of the corresponding units.

[0065] 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 the controller local area network bus ALLCAN, which is used to collect and transmit the current information, voltage information, and status information currently reported by the power supply equipment.

[0066] 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, gimbal, radar altimeter, airborne router, bus recorder, cockpit display unit, multiple sets of power battery packs, multiple sets of flight control units FCU, magnetic compass unit, and barometer unit are all power supply devices.

[0067] In this embodiment, multiple sets of power battery modules, multiple flight control units (FCUs), magnetic compass units, and barometer units are key system equipment of the aircraft. Therefore, in order to improve the safety of such equipment, this embodiment uses a first power distribution unit (PDU1) and a second power distribution unit (PDU2) to jointly supply power to such key system equipment.

[0068] In this embodiment, the first power distribution unit PDU1 is powered by the second power management unit PMU2 and the power control unit PCU, and the second power distribution unit PDU2 is powered by the third power management unit PMU3 and the power control unit PCU. Therefore, the aforementioned critical system equipment is jointly powered by the second power management unit PMU2, the third power management unit PMU3, and the power control unit PCU. That is, the final power source for the aforementioned critical system equipment is the second power management unit PMU2, the third power management unit PMU3, and the power control unit PCU.

[0069] In this embodiment, please refer to Table 1, which shows the power supply requirements of various key system devices inside an aircraft.

[0070] FCU-1 18～35 24 5 FCU2+CBU 18～35 24 7 FCU3 18～35 24 5.6 Battery assemblies 1-12 10～30 24 3.8 gimbal 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 Components 18～35 24 14 total 18～30 24 116.8

[0071] Table 1

[0072] In Table 1, both the second power management unit PMU2 and the third power management unit PMU3 can output a voltage of 18 to 25.2V and a current of 35A, which means they can both output a power of approximately 777W.

[0073] In Table 1, the power control unit (PCU) can provide a power supply of 24V and 135W.

[0074] Considering the need to provide 18-30V power to the key electrical equipment in Table 1, the total power consumption of each device is 116.8W. Therefore, when all the aforementioned key system equipment is operating normally, the power supply system of this embodiment can meet the current voltage and power requirements.

[0075] Furthermore, considering that the power 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 requirements of the aforementioned critical equipment, 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 simultaneously, the remaining power supply equipment can still meet the power needs of all other critical equipment.

[0076] Optionally, the battery pack energy of the second power management unit PMU2 and the third power management unit PMU3 in this embodiment is 488.4Wh. Based on this, even if the two are selected to supply power to the above-mentioned key electrical equipment alone, they can maintain continuous power supply for 4.2 hours, which is sufficient to meet the power supply requirements of the aircraft during its flight time.

[0077] The beneficial effect of this embodiment is that it proposes a power supply system for an aircraft, which includes 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 the ALLCAN controller local area network bus. The second power management unit (PMU2) and the power control unit (PCU) form a first power distribution unit (PDU1), and the third power management unit (PMU3) and the power control unit (PCU) form a second power distribution unit (PDU2). The first power management unit (PMU1) supplies power to the central control unit (CCU). The first power distribution unit (PDU1) supplies power to the gimbal, radar altimeter, airborne router, bus recorder, and cockpit display unit. The first power distribution unit (PDU1) and the second power distribution unit (PDU2) jointly supply power to multiple sets of power battery packs, multiple flight control units (FCUs), a magnetic compass unit, and a barometer unit. The ALLCAN controller local area network bus is used to report current current information, voltage information, and status information. This embodiment implements a device power supply solution with better power supply safety. On the one hand, it can still provide safe device power to the aircraft when some components fail. On the other hand, it can provide timely feedback on the risks that may exist in the battery itself and during power conversion, providing a positive and effective way to deal with emergency risks when powering the aircraft.

[0078] Example 2

[0079] 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 to achieve power input backup and seamless switching.

[0080] In this embodiment, anti-backflow circuits are provided in the second power management unit PMU2 and the power control unit PCU. When the power control unit PCU is short-circuited, the second power management unit PMU2 can supply power to the first power distribution unit PDU1. At the same time, it prevents the power of the second power management unit PMU2 from flowing back to the power control unit PCU through the first power distribution unit PDU1, thereby preventing the overall power supply of the first power distribution unit PDU1 from failing.

[0081] In this embodiment, based on the above-mentioned anti-backflow circuit, when the second power management unit PMU2 is short-circuited, the power control unit PCU can supply power to the first power distribution unit PDU1. Due to the presence of the diode and the anti-backflow circuit, the power of the power control unit PCU can be prevented from flowing back to the second power management unit PMU2 through the first power distribution unit PDU1, thereby preventing the overall power supply of the first power distribution unit PDU1 from failing.

[0082] 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 PDU1.

[0083] FCU-1 24 5 0.21 FCU2+CBU 24 7 0.29 FCU3 24 5.6 0.23 Battery assemblies 1-12 24 3.8 0.16 gimbal 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 Components 24 14 0.58 total 116.8 4.89

[0084] Table 2

[0085] Table 2 shows that the total power of all load devices connected to the first power distribution unit (PDU1) is 116.8W, which is less than the 135W output power of the power control unit (PCU). Furthermore, considering that the total current of all load devices on the first power distribution unit (PDU1) is 4.89A, this is also significantly less than the 35A output capacity of the second power management unit (PMU2). Therefore, even if the second power management unit (PMU2) or the power control unit (PCU) fails, the power supply needs of all load devices on the first power distribution unit (PDU1) can still be met.

[0086] In this embodiment, when the power supply is not turned on, the first power distribution unit PDU1 is powered solely by the second power management unit PMU2.

[0087] 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, then the second power management unit PMU2 supplies power alone. When the voltage of the second power management unit PMU2 drops to the same level as the voltage of the power control unit PCU, the second power management unit PMU2 and the power control unit PCU supply power together. When the voltage of the second power management unit PMU2 drops to a level lower than the voltage of the power control unit PCU, the power control unit PCU supplies power alone.

[0088] 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 will supply power separately so that the second power management unit PMU2 can retain power for use in abnormal situations.

[0089] 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 via diodes to achieve power input backup and seamless switching.

[0090] In this embodiment, anti-backflow circuits are provided in the third power management unit PMU3 and the power control unit PCU. When the power control unit PCU is short-circuited, the third power management unit PMU3 can supply power to the second power distribution unit PDU2. At the same time, it prevents the power of the third power management unit PMU3 from flowing back to the power control unit PCU through the second power distribution unit PDU2, thereby preventing the overall power supply of the second power distribution unit PDU2 from failing.

[0091] In this embodiment, based on the above-mentioned anti-backflow circuit, when the third power management unit PMU3 is short-circuited, the power control unit PCU can supply power to the second power distribution unit PDU2. Due to the presence of the diode and the anti-backflow circuit, the power of the power control unit PCU can be prevented from flowing back to the third power management unit PMU3 through the second power distribution unit PDU2, thereby preventing the overall power supply of the second power distribution unit PDU2 from failing.

[0092] In this embodiment, please refer to Table 3, which shows the power and current of the load device connected to the first power distribution unit PDU1.

[0093] FCU-1 24 5 0.21 FCU2+CBU 24 7 0.29 FCU3 24 5.6 0.23 Battery assemblies 1-12 24 3.8 0.16 total 63.2 2.65

[0094] Table 3

[0095] Table 3 shows that the total power of all load devices connected to the second power distribution unit (PDU2) is 63.2W, which is less than the 135W output power of the power control unit (PCU). Furthermore, considering that the total current of all load devices on the second power distribution unit (PDU2) is 2.65A, this is also significantly less than the 35A output capacity of the third power management unit (PMU3). Therefore, even if the third power management unit (PMU3) or the power control unit (PCU) fails, the power supply needs of all load devices connected to the second power distribution unit (PDU2) can still be met.

[0096] In this embodiment, when the power supply is not turned on, the second power distribution unit PDU2 is powered solely by the third power management unit PMU3.

[0097] 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, then the third power management unit PMU3 supplies power alone. When the voltage of the third power management unit PMU3 drops to the same level as the voltage of the power control unit PCU, the third power management unit PMU3 and the power control unit PCU supply power together. When the voltage of the third power management unit PMU3 drops to a level lower than the voltage of the power control unit PCU, the power control unit PCU supplies power alone.

[0098] 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, the power control unit PCU will supply power separately so that the third power management unit PMU3 can retain power for supplying power in abnormal conditions.

[0099] Example 3

[0100] In this embodiment, as can be seen from the power supply scheme of the first power distribution unit PDU1 and the second power distribution unit PDU2 in the above embodiment 2, when the power is turned on, if any of the power supply devices in the second power management unit PMU2, the third power management unit PMU3 and the power control unit PCU fails, the first power distribution unit PDU1 and the second power distribution unit PDU2 can be guaranteed to be powered normally.

[0101] In this embodiment, considering the importance of multiple battery packs, a first power distribution unit (PDU1) and a second power distribution unit (PDU2) are used to jointly power the 12 power battery packs of the FCU flight control unit. 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 normal working condition, the power supply relationship to each load device depends on the voltages of the second power management unit (PMU2) and the third power management unit (PMU3).

[0102] Therefore, in this embodiment, the multiple sets of power battery modules, the multiple flight control units (FCUs), the magnetic compass unit, and the barometer unit are designated as the first group of electrical equipment; the gimbal, the radar altimeter, the airborne router, the bus recorder, and the cockpit display unit are designated as the second group of electrical equipment; the power supply relationship between the first group and the second group of electrical equipment is adjusted according to the voltage relationship between 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 current of each load device.

[0103]

[0104] Table 4

[0105] As shown in Table 4, in this embodiment, when the voltage relationship 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 relationship is:

[0106] The third power management unit PMU3 supplies power to the first group of electrical devices;

[0107] The second power management unit PMU2 supplies power to the second group of electrical devices;

[0108] The power control unit (PCU) does not supply power.

[0109] As shown in Table 4, in this embodiment, when the voltage relationship 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 relationship is:

[0110] The third power management unit PMU3 supplies power to the first group of electrical devices;

[0111] The power control unit (PCU) supplies power to the second group of electrical devices;

[0112] The second power management unit PMU2 is not powered.

[0113] As shown in Table 4, in this embodiment, when the voltage relationship 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 relationship is:

[0114] The third power management unit PMU3 supplies power to the first group of electrical devices;

[0115] The second power management unit PMU2 and the power control unit PCU jointly supply power to the second group of electrical devices.

[0116] As shown in Table 4, voltage relationships 4, 5, and 6, in this embodiment, when the voltage relationship is 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 power supply relationship is:

[0117] The second power management unit PMU2 supplies power to both the first group of electrical devices and the second group of electrical devices.

[0118] The third power management unit PMU3 and the power control unit PCU are not powered.

[0119] As shown in Table 4, voltage relationships 7, 8, and 9, in this embodiment, when the voltage relationship 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 third power management unit PMU3, or the voltage of the second power management unit PMU2 is lower than the third power management unit PMU3, or the voltage of the second power management unit PMU2 is equal to the third power management unit PMU3. The power supply relationship is:

[0120] The power control unit (PCU) supplies power to both the first group of electrical devices and the second group of electrical devices.

[0121] The second power management unit PMU2 and the third power management unit PMU3 are not powered.

[0122] As shown in Table 4, in this 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:

[0123] The second power management unit PMU2, the third power management unit PMU3, and the power control unit PCU jointly supply power to the first group of electrical devices and the second group of electrical devices.

[0124] Example 4

[0125] 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 connected to the power-on button on the cockpit display unit. For example, pressing and holding the power-on button for more than one second will activate the discharge switches of all three power management units (PMU1, PMU2, and PMU3), initiating external discharge. At this time, all load equipment, including the flight control system and the power battery assembly, has begun operation. Optionally, the power supply can be activated via the ground control station or the power equipment button on the cockpit display unit. After the power supply is activated, the power control unit (PCU) begins operation, providing power backup for the entire equipment power system.

[0126] In this embodiment, when it is necessary to shut down the aircraft, firstly, a command to shut down the power supply is issued through the ground control station. Then, when the power supply is shut down, the power control unit (PCU) immediately stops outputting. Finally, a command to shut down the first power management unit (PMU1), the second power management unit (PMU2), and the third power management unit (PMU3) is issued through the ground control station, thereby shutting down the output of the first power management unit (PMU1), the second power management unit (PMU2), and the third power management unit (PMU3).

[0127] In this embodiment, the shutdown command of the power supply 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 all divided into two parts. That is, the second identical command is only valid if it is received within a preset time period (e.g., 3 seconds) after the first command is received, thereby reducing the possibility of the power supply or power management unit being accidentally shut down.

[0128] Example 5

[0129] Based on the above embodiments, the present invention also proposes an aircraft, which includes a charging dock auxiliary power pin, wherein the first power management unit PMU1, the second power management unit PMU2, and the third power management unit PMU3 are respectively connected to the charging dock auxiliary power pin.

[0130] 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, electrical energy is output to the first power management unit PMU1, the second power management unit PMU2, and the third power management unit PMU3 through the auxiliary power pin of the charging dock.

[0131] The aircraft also includes a power system for implementing the aircraft as described in any of the preceding claims.

[0132] It should be noted that the above-mentioned aircraft embodiments and system embodiments belong to the same concept. The specific implementation process can be found in the system embodiments. Furthermore, the technical features in the system embodiments are also applicable to the aircraft embodiments, and will not be repeated here.

[0133] It should be noted that, in this document, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Unless otherwise specified, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes that element.

[0134] The sequence numbers of the above embodiments of the present invention are for descriptive purposes only and do not represent the superiority or inferiority of the embodiments.

[0135] Through the above description of the embodiments, those skilled in the art can clearly understand that the methods of the above embodiments can be implemented by means of software plus necessary general-purpose hardware platforms. Of course, they can also be implemented by hardware, but in many cases the former is a better implementation method. Based on this understanding, the technical solution of the present invention, in essence, or the part that contributes to the prior art, can be embodied in the form of a software product. This computer software product is stored in a storage medium (such as ROM / RAM, magnetic disk, optical disk), and includes several instructions to cause a terminal (which may be a mobile phone, computer, server, air conditioner, or network device, etc.) to execute the methods described in the various embodiments of the present invention.

[0136] The embodiments of the present invention have been described above with reference to the accompanying drawings. However, the present invention is not limited to the specific embodiments described above. The specific embodiments described above are merely illustrative and not restrictive. Those skilled in the art can make many other forms under the guidance of the present invention without departing from the spirit and scope of the claims. All of these forms are within the protection scope of the present invention.

Claims

1. An electrical power system for an aircraft, comprising: The system includes: a first power management unit, a second power management unit, a third power management unit, and a power control unit connected to a controller local area network (Controller Area Network) bus. The second power management unit and the power control unit constitute a first power distribution unit, and the third power management unit and the power control unit constitute a second power distribution unit. The first power management unit is used to supply power to the central control unit; The first power distribution unit is used to supply power to the second group of electrical equipment, which includes a gimbal, a radar altimeter, an airborne router, a bus recorder, and a cockpit display unit. The first power distribution unit and the second power distribution unit jointly supply power to the first group of electrical equipment, which includes multiple sets of power battery packs, multiple sets of flight control units, a magnetic compass unit, and a barometer unit. The controller local area network bus is used to report current current information, voltage information, and status information; The second power management unit, the third power management unit, and the power control unit are connected in parallel; The power supply relationship between the first group of electrical devices and the second group of electrical devices is adjusted according to the voltage relationship between the second power management unit, the third power management unit, and the power control unit. When the voltage relationship is such 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: The third power management unit supplies power to the first group of electrical devices; The power control unit supplies power to the second group of electrical devices; The second power management unit is not powered. When the voltage relationship is such 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: The third power management unit supplies power to the first group of electrical devices; The second power management unit and the power control unit jointly supply power to the second group of electrical devices.

2. The power supply system for the aircraft according to claim 1, characterized in that, When the power supply is not turned on, the first power distribution unit is powered solely by the second power management unit; When the power supply is turned on, if the voltage of the second power management unit is higher than the voltage of the power control unit, the second power management unit will supply power alone. When the voltage of the second power management unit drops to the same level as the voltage of the power control unit, the second power management unit and the power control unit will supply power together. When the voltage of the second power management unit drops to a level lower than the voltage of the power control unit, the power control unit will supply power alone. When the power supply is turned on, if the voltage of the second power management unit is lower than the voltage of the power control unit, the power control unit will supply power separately so that the second power management unit can retain power for use in abnormal situations.

3. The power supply system for the aircraft according to claim 1, characterized in that, When the power supply is not turned on, the second power distribution unit is powered solely by the third power management unit; When the power supply is turned on, if the voltage of the third power management unit is higher than the voltage of the power control unit, the third power management unit will supply power alone. When the voltage of the third power management unit drops to the same level as the voltage of the power control unit, the third power management unit and the power control unit will supply power together. When the voltage of the third power management unit drops to a level lower than the voltage of the power control unit, the power control unit will supply power alone. When the power supply is turned on, if the voltage of the third power management unit is lower than the voltage of the power control unit, the power control unit will supply power separately so that the third power management unit can retain power for use in abnormal situations.

4. The aircraft electrical power system of claim 1, wherein, When the voltage relationship is such 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: The third power management unit supplies power to the first group of electrical devices; The second power management unit supplies power to the second group of electrical devices; The power control unit does not supply power.

5. The aircraft electrical power system of claim 1, wherein, When the voltage relationship is such 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: The second power management unit supplies power to both the first group of electrical devices and the second group of electrical devices. The third power management unit and the power control unit do not supply power.

6. The aircraft electrical power system of claim 1, wherein, When the voltage relationship is such 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: The power control unit supplies power to both the first group of electrical devices and the second group of electrical devices. The second power management unit and the third power management unit do not supply power.

7. An aircraft, characterized in that The aircraft includes a charging dock auxiliary power pin, and the first power management unit, the second power management unit, and the third power management unit are respectively connected to the charging dock auxiliary power 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 charging dock outputs electrical energy to the first power management unit PMU1, the second power management unit PMU2, and the third power management unit PMU3. The aircraft also includes a power system for implementing the aircraft as described in any one of claims 1 to 6.

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