CN215475774U

CN215475774U - Power device of electric manned aircraft and electric manned aircraft

Info

Publication number: CN215475774U
Application number: CN202120697603.7U
Authority: CN
Inventors: 赵德力; 全洪飞; 李�杰; 伍惠康
Original assignee: Guangdong Huitian Aerospace Technology Co Ltd
Current assignee: Guangdong Huitian Aerospace Technology Co Ltd
Priority date: 2021-04-06
Filing date: 2021-04-06
Publication date: 2022-01-11
Anticipated expiration: 2031-04-06

Abstract

The application discloses power device and electronic manned vehicle of electronic manned vehicle. The power device comprises a plurality of motor sets and a plurality of battery packs corresponding to the motor sets. Wherein, a motor group includes a plurality of motors, and a group battery includes a plurality of batteries, and every battery in the group battery is all independently to be connected with the motor group that corresponds in order to supply power to a plurality of motors in the motor group. In the power device and the electronic manned vehicle of electronic manned vehicle that this application discloses, supply power to a plurality of motors in the motor train through solitary battery in using the group battery, the electric quantity of a plurality of batteries in the group battery can be balanced for the voltage difference of a plurality of batteries keeps relatively stable, ensures that the battery is normal, operate steadily.

Description

Power device of electric manned aircraft and electric manned aircraft

Technical Field

The application relates to the technical field of battery charging, in particular to a power device of an electric manned aircraft and the electric manned aircraft.

Background

In the driving system of the multi-rotor electric manned aircraft, generally, each battery is connected with an electric regulator, each electric regulator is connected with a motor, and the motor drives a propeller to rotate, so that the take-off, landing and flying of the aircraft are realized. Under the general condition, an electricity is transferred and is controlled corresponding a motor, when electronic manned vehicle long-time when flying to one side, will lead to the battery ionization consumption ratio on one side great, and the battery power consumption on the other side is little, and battery power system discharges and will be inhomogeneous.

SUMMERY OF THE UTILITY MODEL

In view of the above, embodiments of the present application provide a power device of an electric manned vehicle and an electric manned vehicle.

The power device of electronic manned aircraft of this application embodiment includes:

a plurality of motor sets, one said motor set comprising a plurality of motors;

and each battery in the battery pack is independently connected with the corresponding motor set to supply power to a plurality of motors in the motor set.

In some embodiments, the power device includes a plurality of electric tunes, one electric tune is connected with one motor, and the power terminals of a plurality of electric tunes corresponding to one motor group are connected with each other so that each battery in the corresponding battery group independently supplies power to the corresponding plurality of electric tunes.

In some embodiments, the power device includes a plurality of diodes, the anode and the cathode of one of the diodes are respectively connected to one of the batteries and a corresponding one of the motor sets, and the cathodes of the plurality of diodes corresponding to one of the motor sets are connected to each other.

In some embodiments, the power device includes a connection line, and the connection line connects a plurality of power terminals of the electric power regulator in one of the motor sets and the cathodes of a corresponding plurality of the diodes.

In some embodiments, the diode is an ideal diode.

In some embodiments, the power plant includes a battery power module and a plurality of first relays connected to the battery power module, and one of the batteries is connected to a corresponding one of the diodes through one of the first relays.

In some embodiments, the power plant further comprises a backup battery pack including at least one battery, the backup battery pack being connected to the corresponding plurality of diodes through a plurality of second relays, respectively.

In some embodiments, the battery pack further comprises a backup battery connected to the plurality of diodes corresponding to the battery pack through a plurality of third relays.

In some embodiments, the battery power module includes a battery detection unit connected to the plurality of batteries to detect a voltage, a current, and/or a temperature of the batteries.

The embodiment of the application provides an electric manned vehicle, which comprises a plurality of rotors and the power device of any one of the above embodiments, wherein one motor is connected with one rotor to drive the rotor to work.

In certain embodiments, the plurality of rotors includes a plurality of left rotors and a plurality of right rotors, and the one of the motor assemblies includes a left rotor motor and a right rotor motor, the left rotor motor being coupled to a corresponding one of the left rotors, and the right rotor motor being coupled to a corresponding one of the right rotors.

In certain embodiments, the plurality of rotors includes a plurality of front rotors and a plurality of rear rotors, and the one motor assembly includes a front rotor motor coupled to a corresponding one of the front rotors and a rear rotor motor coupled to a corresponding one of the rear rotors.

In the power device of the electric manned aircraft and the electric manned aircraft, the electric quantity of the batteries in the battery pack can be balanced by supplying power to the motors in the motor pack through the independent batteries in the battery pack, so that the voltage difference of the batteries is kept relatively stable, and the batteries are ensured to normally and stably run.

Additional aspects and advantages of the present application will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the present application.

Drawings

The foregoing and/or additional aspects and advantages of the present application will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:

fig. 1 is a block schematic diagram of a power plant of an embodiment of the present application.

Fig. 2 is a schematic view of a motor distribution according to an embodiment of the present application.

Fig. 3 is a block schematic diagram of a power plant of an embodiment of the present application.

Fig. 4 is a block schematic diagram of a power plant of an embodiment of the present application.

Fig. 5 is a schematic view of a motor distribution according to an embodiment of the present application.

Description of the main element symbols:

the power device 10, the motor set 101, the motor 1011, the left wing motors M2, M4, M6 and M8, the right wing motors M1, M3, M5 and M7, the front wing motors M1', M3', M5 'and M7', the rear wing motors M2', M4', M6 'and M8', the first diode 1051, the second diode 1052, the third diode 1053, the fourth diode 1054, the fifth diode 1055, the sixth diode 1056, the seventh diode 1057, the eighth diode 1058, the first electrically tunable 1061, the second electrically tunable 1062, the third electrically tunable 1063, the fourth electrically tunable 1064, the fifth electrically tunable 1065, the sixth electrically tunable 1066, the seventh electrically tunable 1067, the eighth electrically tunable 1068, the first relay 1071, the second relay 1072, the third 1073, the standby relay 106108, the standby battery 1081, the first electrically tunable 1062, the third electrically tunable 1083, the fifth electrically tunable 1088, the fourth electrically tunable 1084, the fifth electrically tunable battery 1081, the sixth 1083, the fifth electrically tunable 1084, the fifth electrically tunable battery 1083, the sixth battery 1084, the fifth electrically tunable 1086, the fifth electrically tunable 1084, the sixth battery 1084, the fifth electrically tunable battery 1084, the fourth electrically tunable battery 1086, the fifth battery 1084, the sixth battery 1084, the fourth electrically tunable battery 1084, the fifth electrically tunable battery 1084, the fourth electrically tunable battery 1086, the fifth electrically tunable battery 1088, a backup battery 1089, a flight control module 109, and a battery power module 111.

Detailed Description

Reference will now be made in detail to embodiments of the present application, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application.

Referring to fig. 1, the present embodiment provides a power device 10 of an electric manned vehicle, where the power device 10 includes a plurality of motor sets 101 and a plurality of battery packs 108 corresponding to the plurality of motor sets 101. One motor group 101 includes a plurality of motors 1011. One battery pack 108 includes a plurality of batteries, and each battery in the battery pack 108 is independently connected to a corresponding motor group 101 to supply power to a plurality of motors 1011 in the motor group.

Specifically, under the condition that the electric manned vehicle keeps flying in the same side direction for a long time or the flying time towards one side is far longer than that of the other side, the running power of the motor for controlling the rotor wing on one side of the flying direction is smaller, and the consumption of the electric quantity of the battery corresponding to the motor on the side is smaller. And the motor of the rotor on the other side of the control flight direction has larger running power, the consumption of the electric quantity of the battery corresponding to the motor on the other side is also larger, and the discharge of the battery power system is uneven. At the moment, the batteries are charged, and due to the fact that voltage difference among the batteries is large, after the batteries are connected in parallel, the situation of battery charging overcurrent can occur, the batteries are damaged, and flight safety is affected.

In the power device 10 of the embodiment of the present application, the electric quantity of the plurality of batteries in the battery pack 108 can be balanced by supplying power to the plurality of motors 1011 in the motor group 101 by using the single battery in the battery pack 108, so that the voltage difference of the plurality of batteries is kept relatively stable, and the batteries are ensured to normally and stably operate.

Referring to fig. 2, in some embodiments, when the electric manned vehicle keeps flying to the right for a long time or the duration of the flight to the right is much longer than the duration of the flight to the left, the battery power consumption corresponding to the left wing motors M2, M4, M6, and M8 is larger, and the battery power consumption corresponding to the right wing motors M1, M3, M5, and M7 is smaller. That is, the battery voltage corresponding to M2 is greater than the battery voltage corresponding to M1, the battery voltage corresponding to M4 is greater than the battery voltage corresponding to M3, the battery voltage corresponding to M6 is greater than the battery voltage corresponding to M5, and the battery voltage corresponding to M8 is greater than the battery voltage corresponding to M7.

In the electric manned vehicle, 8 motors M1-M8 are arranged, a motor group G1 is formed by M1 and M2, a motor group G2 is formed by M3 and M4, a motor group G3 is formed by M5 and M6, and a motor group G4 is formed by M7 and M8. The battery pack is powered by the battery with higher voltage, namely the battery corresponding to M2 is used for supplying power to G1, the battery corresponding to M4 is used for supplying power to G2, the battery corresponding to M6 is used for supplying power to G3, and the battery corresponding to M8 is used for supplying power to G4, so that the electric quantity of a plurality of batteries corresponding to left wing motors M2, M4, M6 and M8 and right wing motors M1, M3, M5 and M7 in the battery pack 108 can be balanced, the voltage difference of the plurality of batteries is kept relatively stable, the batteries can be ensured to normally and stably operate, and the flight safety of the electric manned vehicle is ensured.

It is understood that, in the above embodiment, the battery corresponding to M1 may continue to supply power to the motor M1 while the battery corresponding to M2 is used to supply power to G1. In this embodiment, an electric manned vehicle is exemplified to be provided with 8 motors, but in actual use, the number of parts such as the motors, batteries, and rotors is not limited to 8.

For example, set up 2 motor groups and 2 group batteries in electronic manned vehicle, each motor group includes 2 motors, and each group battery includes 2 batteries, and each battery in the group battery all independently is connected with corresponding motor group to a plurality of motors in the motor group power supply. For another example, set up 8 motor groups and 8 group batteries in electronic manned vehicle, every motor group includes 2 motors, and every group battery includes 2 batteries, and every battery in the group battery is all independently to be connected with the motor group that corresponds to a plurality of motors power supplies in to the motor group.

In some embodiments, the power device 10 includes a plurality of electronic modules, one electronic module is connected to one motor 1011, and power terminals of a plurality of electronic modules corresponding to one motor group 101 are connected to each other so that each battery 1011 in the corresponding battery group 101 independently supplies power to the corresponding plurality of electronic modules.

Specifically, one electric controller is connected with one motor 1011, and one electric controller correspondingly controls one motor, and the electric controller can be used for controlling the rotating speed of the motor and adjusting the running power of the motor. In this way, independent control of the individual motors can be achieved. Because one motor correspondingly controls one or more rotors, independent control of the single motor can also help the electric manned vehicle to sail more flexibly.

Further, a plurality of power ends of the electric power regulator corresponding to one of the battery packs 101 are connected to each other, and each battery 1011 in the corresponding battery pack 101 can independently supply power to the corresponding plurality of electric power regulators. For example, a first battery 1081 may be capable of supplying power to the first and

second power banks

1061 and 1062, and a second battery 1082 may be capable of supplying power to the first and

second power banks

1061 and 1062.

In some embodiments, 8 motors M1-M8 and 8

electric controls

1061 and 1068 are arranged in the electric manned vehicle. The first electronic governor 1061 controls the motor M1, the second electronic governor 1062 controls the motor M2, the third electronic governor 1063 controls the motor M3, and so on. 8 electric turnings correspond 8 motors of control, control electronic manned aircraft and keep flying right for a long time. At this time, the battery power consumption corresponding to the left wing motors M2, M4, M6, and M8 is large, and the battery power consumption corresponding to the right wing motors M1, M3, M5, and M7 is small.

By making M1 and M2 form a motor group G1, M3 and M4 form a motor group G2, M5 and M6 form a motor group G3, M7 and M8 form a motor group G4, power is supplied to the motor group G1 by using a battery corresponding to M2, power is supplied to the motor group G2 by using a battery corresponding to M4, power is supplied to the motor group G3 by using a battery corresponding to M6, and power is supplied to the motor group G4 by using a battery corresponding to M8, the electric quantities of a plurality of batteries corresponding to left wing motors M2, M4, M6 and M8 and right wing motors M1, M3, M5 and M7 in the battery group 108 can be balanced, so that the voltage differences of the plurality of batteries are kept relatively stable, the batteries are ensured to operate normally and stably, and the safety of the electric manned aircraft is ensured.

In some embodiments, the power device 10 includes a plurality of diodes, the positive pole and the negative pole of one diode are respectively connected to one battery and a corresponding motor set 101, and the negative poles of the plurality of diodes corresponding to one motor set 101 are connected to each other.

Specifically, the anode of the diode is connected to the corresponding battery, and the cathode of the diode is connected to the corresponding motor group 101. For example, referring to fig. 1 again, the anode of the first diode 1051 is connected to the first battery 1081, the cathode of the first diode 1051 is connected to the motor set 101, the anode of the second diode 1052 is connected to the second battery 1082, the cathode of the second diode 1052 is connected to the motor set 101, and so on.

In the embodiment of the application, the diode with small voltage drop is adopted, and the diode is utilized to realize the one-way conduction of the circuit, so that the charging and discharging phenomena between batteries are avoided. For example, the charging and discharging phenomena between the batteries means that the first battery 1081 and the second battery 1082 may be charged and discharged when the voltage of the first battery 1081 is high and the voltage of the second battery 1082 is low. The charging and discharging between the batteries may result in the reduction of the service life of the batteries, the failure of the batteries to work normally, and the like.

Therefore, the anode and the cathode of the diode are respectively connected with one battery and one corresponding motor set 101, so that the normal and stable operation of the battery can be ensured.

In some embodiments, the diode is an ideal diode.

Specifically, the ideal diode may be a diode with a small voltage drop, and the ideal diode is used to realize unidirectional conduction of the circuit, so that the charging and discharging phenomena between batteries can be avoided. For example, the inter-battery charge/discharge phenomenon means that when the voltage of the first battery 1081 is high and the voltage of the second battery 1082 is low, charge/discharge may be performed between the first battery 1081 and the second battery 1082. The charging and discharging between the batteries may result in the reduction of the service life of the batteries, the failure of the batteries to work normally, and the like.

Thus, the normal and stable operation of the battery can be ensured.

In certain embodiments, the power plant 10 includes a battery power module 111 and a plurality of first relays 1071 coupled to the battery power module 111, one battery coupled to a corresponding one of the diodes through one of the first relays 1071.

Specifically, one end of the first relay 1071 is connected to the battery, and the other end is connected to the diode. Under the condition that the first relay 1071 is closed, a passage is formed between the battery and the electric regulator, and the battery supplies power to the corresponding motor 1011 through the first relay 1071, the diode and the electric regulator. For example, a first battery 1081 supplies power to the motor 1011 in the motor group 101 through the first relay 1071, the diode 1051, and the first power tap 1061, and a second battery 1082 supplies power to the motor 1011 in the motor group 101 through the first relay 1071, the diode 1052, and the second power tap 1062. When the first relay 1071 is turned off, an open circuit is formed between the battery and the electric regulator, and the battery cannot supply power to the motor.

In addition, the battery power module 111 is connected in parallel with the plurality of first relays 1071, and the battery power module 111 is configured to drive the plurality of first relays to be turned on or off, so as to selectively control the battery to supply power to the motor 1011.

In this manner, individual control of the first relay 1071 can be realized. Meanwhile, in the upgrading or debugging process of the power device 10, the control of a certain part in the power device 10 can be realized by selectively closing or opening a certain first relay 1071, so that the upgrading and maintenance process of the power device 10 is simpler and more convenient.

Referring to fig. 3, in some embodiments, the power plant 10 further includes a backup battery pack 1010, the backup battery pack 1010 includes at least one battery, and the backup battery pack 1010 is connected to the corresponding plurality of diodes through a plurality of second relays 2072.

Specifically, when any battery pack 108 fails and cannot supply power to the motor 1011, the power device 10 may use the spare battery pack 1010 to supply power to the motor 1011. The backup battery pack 1010 includes at least one battery, and the backup battery pack 1010 is connected to a plurality of corresponding diodes through a plurality of second relays 1072. Under the closed condition of second relay 1072, form the route between reserve battery pack 1010 and the electricity accent, reserve battery pack 1010 supplies power to corresponding motor 1011 through second relay 1072, diode, electricity accent. For example, the backup battery pack 1010 supplies power to the motor 1011 in the motor group 101 through the second relay 1072, the diode 1051, and the first power tap 1061, and supplies power to the motor 1011 in the motor group 101 through the second relay 1072, the diode 1052, and the second power tap 1062. Under the condition that the second relay 1072 is disconnected, an open circuit is formed between the battery and the electric power regulator, and the battery cannot supply power to the motor.

Thus, the motor 1011 can operate normally when the battery pack 101 fails, and the flight safety of the electric manned vehicle can be ensured.

In addition, the battery power module 111 is connected in parallel with the plurality of second relays 1072, and the battery power module 111 is configured to drive the plurality of second relays 1072 to be turned on or off, thereby selectively controlling the battery output power supply voltage.

In this manner, individual control of the second relay 1072 can be realized. Meanwhile, in the upgrading or debugging process of the power plant 10, the control of certain parts in the power plant 10 can be realized by selectively closing or opening certain second relay 1072, so that the upgrading and maintenance process of the power plant 10 is simpler and more convenient.

Referring to fig. 4, in some embodiments, the battery 108 further includes a backup battery 1089, and the backup battery 1089 is connected to a plurality of diodes corresponding to the battery pack 108 through a plurality of third relays 1073.

Specifically, when the first battery and/or the second battery in the battery pack 108 fail to supply power to the motor 1011, the power device 10 may use the backup battery 1089 in the battery pack 108 to supply power to the motor 1011. A battery backup 1089 may be provided within each battery pack 108.

The backup battery 1089 is connected to the corresponding diodes via the third relays 1073. Under the condition that the third relay 1073 is closed, a passage is formed between the standby battery 1089 and the corresponding power regulator, and the battery flows to the corresponding motor through the third relay 1073, the diode and the power regulator. For example, the backup battery 1089 supplies power to the motor 1011 in the motor group 101 through the third relay 1073, the diode 1051, and the first power tap 1061, and supplies power to the motor 1011 in the motor group 101 through the third relay 1073, the diode 1052, and the second power tap 1062. Under the condition that the third relay 1073 is disconnected, an open circuit is formed between the battery and the electric power regulator, and the battery cannot supply power to the motor.

Thus, the motor 1011 can operate normally when the battery pack 108 fails, and the flight safety of the electric manned vehicle can be ensured.

In some embodiments, the battery power module 111 includes a battery detection unit (not shown) connected to the plurality of batteries to detect the voltage, current, and/or temperature of the batteries.

Specifically, the battery detection unit is connected to the plurality of batteries and configured to detect voltages, currents and/or temperatures of the batteries, so that the power device 10 controls the components thereof according to the voltage, current and/or temperature information.

In some embodiments, the battery detection unit detects that the voltage of a certain battery exceeds a predetermined voltage threshold, or detects that the temperature of a certain battery exceeds a predetermined temperature threshold, or detects that the current of a certain battery exceeds a predetermined current threshold, the battery detection unit sends the detected voltage, temperature, current and other information of the battery to the battery management unit of the electric manned aircraft, and the battery management unit counts the battery information of each battery and issues an instruction according to the current battery information.

Therefore, the corresponding parts of the power device 10 can be controlled by detecting the battery information, the battery can be adjusted, and the problems of over-discharge or over-charge and the like of the battery can be avoided.

It should be noted that the voltage threshold, the current threshold, and the temperature threshold of the battery may be determined according to characteristics of a battery core in the battery, for example, parameters such as operating voltage, operating current, and operating temperature, and are not specifically limited, for example, the voltage threshold may be 80V, 85V, 90V, 95V, 100V, 110V, and 118V, and the temperature threshold may be 55 degrees celsius, 60 degrees celsius, 65 degrees celsius, and 70 degrees celsius, and the like.

The embodiment of the application also provides an electric manned aircraft, which comprises a plurality of rotors and the power device 10 of any one of the above embodiments, wherein one motor is connected with one rotor to drive the rotor to work.

In some embodiments, the plurality of rotors includes a plurality of left rotors and a plurality of right rotors, and one motor assembly 101 includes one left rotor motor and one right rotor motor, the left rotor motor being coupled to a corresponding one of the left rotors and the right rotor motor being coupled to a corresponding one of the right rotors.

In some embodiments, the number of rotors is eight, and the power plant comprises four motor banks and four battery packs, each motor bank comprising two motors, and each battery pack comprising two batteries.

In some embodiments, the electric manned vehicle includes a cockpit over which a plurality of rotors are located.

Specifically, referring to fig. 5, group G1 includes a left rotor motor M2 and a right rotor motor M1, group G2 includes a left rotor motor M4 and a right rotor motor M3, group G3 includes a left rotor motor M6 and a right rotor motor M5, and group G4 includes a left rotor motor M8 and a right rotor motor M7. Left rotor motors M2, M4, M6, and M8 are connected to the corresponding left rotor, and right rotor motors M1, M3, M5, and M7 are connected to the corresponding right rotor.

In some embodiments, in the case where the electric manned vehicle remains flying to the right for a longer period of time, or for a period of time much longer than that of flying to the left, the battery power consumption corresponding to the left wing motors M2, M4, M6, and M8 is greater, and the battery power consumption corresponding to the right wing motors M1, M3, M5, and M7 is smaller. That is, the battery voltage corresponding to M2 is greater than the battery voltage corresponding to M1, the battery voltage corresponding to M4 is greater than the battery voltage corresponding to M3, the battery voltage corresponding to M6 is greater than the battery voltage corresponding to M5, and the battery voltage corresponding to M8 is greater than the battery voltage corresponding to M7.

It is understood that, in the above embodiment, the battery corresponding to M1 may continue to supply power to the motor M1 while the battery corresponding to M2 is used to supply power to G1. In the present embodiment, an electric manned vehicle is exemplified by 8 sets of motors, but in actual use, the number of components such as motors, batteries, rotors, etc. is not limited to 8 sets.

In some embodiments, the plurality of rotors includes a plurality of front rotors and a plurality of rear rotors, and one motor assembly 101 includes one front rotor motor coupled to a corresponding one of the front rotors and one rear rotor motor coupled to a corresponding one of the rear rotors.

Specifically, referring to fig. 3, cluster G1 'includes a front rotor motor M1 and a rear rotor motor M2, cluster G2' includes a front rotor motor M3 'and a rear rotor motor M4', cluster G3 'includes a front rotor motor M5' and a rear rotor motor M6', and cluster G4' includes a front rotor motor M7 'and a rear rotor motor M8'. Rear rotor motors M2', M4', M6 'and M8' are connected to the corresponding rear rotors, and front rotor motors M1', M3', M5 'and M7' are connected to the corresponding front rotors.

In some embodiments, in the event that the electric manned vehicle remains in the backward flight for a longer period of time, or for a period of time that is much greater than the forward flight period of time, the battery power consumption corresponding to front rotor motors M1', M3', M5 'and M7' is greater and the battery power consumption corresponding to rear rotor motors M2', M4', M6 'and M8' is less. That is, the battery voltage corresponding to M2 'is greater than the battery voltage corresponding to M1', the battery voltage corresponding to M4 'is greater than the battery voltage corresponding to M3', the battery voltage corresponding to M6 'is greater than the battery voltage corresponding to M5', and the battery voltage corresponding to M8 'is greater than the battery voltage corresponding to M7'.

In the electric manned aircraft, 8 motors M1'-M8', M1 'and M2' are arranged to form a motor group G1', M3' and M4 'are arranged to form a motor group G2', M5 'and M6' are arranged to form a motor group G3', and M7' and M8 'are arranged to form a motor group G4'. By supplying power to G1 'by using the battery corresponding to M2', supplying power to G2 'by using the battery corresponding to M4', supplying power to G3 'by using the battery corresponding to M6', and supplying power to G4 'by using the battery corresponding to M8', the electric quantities of the plurality of batteries corresponding to the front rotor motors M1', M3', M5 'and M7' and the rear rotor motors M2', M4', M6 'and M8' in the battery pack 108 can be balanced, so that the voltage differences of the plurality of batteries are kept relatively stable, the batteries are ensured to normally and stably operate, and the flight safety of the electric manned vehicle is ensured.

It is understood that, in the above embodiment, the battery corresponding to M2 'is used to supply power to G1', and the battery corresponding to M1 'can also continue to supply power to motor M1'. In the present embodiment, an electric manned vehicle is exemplified by 8 sets of motors, but in actual use, the number of components such as motors, batteries, rotors, etc. is not limited to 8 sets.

The embodiment of the application also provides a computer readable storage medium. One or more non-transitory computer-readable storage media containing computer-executable instructions that, when executed by one or more processors, cause the processors to perform the charging control method of any of the embodiments described above.

It will be understood by those skilled in the art that all or part of the processes of the methods of the above embodiments may be implemented by hardware instructions of a computer program, which may be stored in a non-volatile computer-readable storage medium, and when executed, may include the processes of the embodiments of the methods described above. The storage medium may be a magnetic disk, an optical disk, a Read-Only Memory (ROM), or the like.

The above examples only express several embodiments of the present application, and the description thereof is more specific and detailed, but not construed as limiting the scope of the present application. It should be noted that, for a person skilled in the art, several variations and modifications can be made without departing from the concept of the present application, which falls within the scope of protection of the present application. Therefore, the protection scope of the present patent shall be subject to the appended claims.

Claims

1. A power device of an electric manned aircraft is characterized by comprising:

a plurality of motor sets, one said motor set comprising a plurality of motors;

2. The power device of claim 1, wherein the power device comprises a plurality of power banks, one power bank is connected to one motor, and power terminals of a plurality of power banks corresponding to one motor bank are connected to each other so that each battery in the corresponding battery pack independently supplies power to the corresponding plurality of power banks.

3. The power plant of claim 2, wherein said power plant includes a plurality of diodes, the positive and negative poles of one of said diodes being connected to one of said batteries and to a corresponding one of said motor assemblies, respectively, and the negative poles of a corresponding plurality of said diodes of one of said motor assemblies being connected to one another.

4. The power device according to claim 3, wherein the power device comprises a connecting wire, and the connecting wire is connected with a plurality of power ends of the electric power regulator in one motor group and the cathodes of a plurality of corresponding diodes.

5. The power plant of claim 4, wherein the diode is an ideal diode.

6. A power plant according to claim 3, wherein said power plant includes a battery power module and a plurality of first relays connected to said battery power module, one of said batteries being connected to a corresponding one of said diodes via one of said first relays.

7. The power plant of claim 3, further comprising a backup battery pack including at least one battery, the backup battery pack being connected to the corresponding plurality of diodes through a plurality of second relays, respectively.

8. The power plant of claim 3, wherein the battery pack further comprises a backup battery coupled to the plurality of diodes corresponding to the battery pack via a plurality of third relays.

9. The power plant of claim 6, wherein the battery power module comprises a battery detection unit connected to the plurality of batteries to detect voltage, current and/or temperature of the batteries.

10. An electric manned vehicle comprising a plurality of rotors and a power plant according to any one of claims 1 to 9, one of said motors being connected to one of said rotors to drive said rotors in operation.

11. The electric manned vehicle of claim 10, wherein said plurality of rotors includes a plurality of left rotors and a plurality of right rotors, and wherein one of said motor assemblies includes a left rotor motor and a right rotor motor, said left rotor motor being coupled to a corresponding one of said left rotors, and said right rotor motor being coupled to a corresponding one of said right rotors.

12. The electric manned vehicle of claim 10, wherein the plurality of rotors includes a plurality of front rotors and a plurality of rear rotors, and wherein one of the motor assemblies includes a front rotor motor and a rear rotor motor, the front rotor motor being coupled to a corresponding one of the front rotors and the rear rotor motor being coupled to a corresponding one of the rear rotors.