A battery system for a manned aircraft

Abstract

The present invention discloses a battery system for a manned aircraft. The key points of the technical solution are as follows: it includes a flight controller, an upper electronic system, and a battery management subsystem. The flight controller is arranged in the airframe. A plurality of rotors are arranged on the airframe. The rotors are driven by rotor motors, and there are several rotor motors. Among them, two of the rotor motors are connected to one upper electronic system, so that one upper electronic system controls the driving of two juxtaposed rotor motors. The battery management subsystem is used to manage and control the control of the upper electronic system over the rotor motors. The battery system for a manned aircraft of the present invention has the effect of being able to reduce the inrush current during power-on while providing a large current and protecting the stable operation of the motor.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft power supply, and more particularly to a battery system for a manned aircraft. Background Art

[0002] With the continuous development of the aerospace industry, the number of onboard electrical equipment is increasing, and the design of the aviation power battery management system has become the key. The aviation power battery management system is not only a functional system, but also an important safety assurance system. At present, with the continuous development of batteries, the BMS system has been derived. The BMS system is mainly for intelligent management and maintenance of each battery unit, to prevent the battery from overcharging and over-discharging, and to extend the battery life and monitor the battery status.

[0003] However, in the field of aircraft, with the continuous development of aircraft types, the power supply systems of different models will also change. In response to the current limitations of road resources, more and more aircraft need to consider vertical take-off and landing without slide assistance. However, when the vertical take-off and landing aircraft is started and the body is controlled to rise, the output power of the battery pack is very large, which may easily cause the motor to burn or break down, resulting in the paralysis of the entire power supply system, and then the aircraft safety accident. In this regard, a stable battery system that can be applied to manned vertical take-off and landing aircraft is urgently needed. Summary of the invention

[0004] In view of the deficiencies in the prior art, the object of the present invention is to provide a manned aircraft battery system, which has the effect of reducing the impact current during power-on while providing a large current, thereby protecting the stable operation of the motor.

[0005] To achieve the above object, the present invention provides the following technical solutions:

[0006] A manned aircraft battery system, comprising:

[0007] A flight controller, the flight controller is arranged in the fuselage;

[0008] An upper electronic system, the upper electronic system comprising a battery pack, a pre-charging circuit, a power-on circuit and a switch assembly, the battery pack being connected to a rotor motor driving the rotor to rotate via the power-on circuit, the power-on circuit being further connected to the pre-charging circuit, the pre-charging circuit being used to pre-charge the rotor motor, the switch assembly comprising a pre-charging switch group and a power-on switch group, the pre-charging switch group being used to connect the battery pack and the pre-charging circuit, and to control the pre-charging circuit to be turned on to pre-charge the rotor motor, the power-on switch group being used to connect the power-on circuit and the rotor motor, and to control the conduction between the power-on circuit and the rotor motor, the pre-charging switch group and the power-on switch group being kept one closed and the other open;

[0009] Battery management subsystem, the battery management subsystem includes an external power supply and a BMS management module, the external power supply is used to supply power to the BMS management module and the switch assembly, the BMS management module is used to control the disconnection of the power-on switch group, a serial port is provided on the flight controller, and the BMS management module is also connected to the serial port.

[0010] As a further improvement of the present invention, a plurality of rotor motors are provided, and two of the rotor motors are connected to one of the upper electronic systems, so that one of the upper electronic systems controls the driving of two juxtaposed rotor motors.

[0011] As a further improvement of the present invention, the pre-charge switch group includes a pre-charge switch, a pre-charge relay and a pre-charge resistor, the pre-charge switch is connected to the external power supply, the pre-charge resistor is arranged on the pre-charge circuit, and the pre-charge switch is used to control the pre-charge relay to be turned on, so as to control the pre-charge circuit to be conducted with the rotor motor and pre-charge the rotor power.

[0012] As a further improvement of the present invention, the power-on switch group includes a power-on switch and a contactor, the power-on switch is connected to the external power supply, the power-on switch is used to control the contactor to turn on the power-on circuit and the rotor motor, and when the power-on circuit is connected to the rotor motor, the pre-charge circuit is short-circuited.

[0013] As a further improvement of the present invention, the number of the BMS management modules is the same as the number of the upper electronic systems.

[0014] As a further improvement of the present invention, the power-on switch group further includes a normally closed relay, the normally closed relay is arranged between the power-on switch and the external power supply, the BMS management module is connected to the normally closed relay and is used to control the normally closed relay to be turned off, so as to cut off the power supply of the power-on circuit to the rotor motor.

[0015] As a further improvement of the present invention, the BMS management modules are communicatively connected through a CAN bus.

[0016] As a further improvement of the present invention, a circuit control strategy for controlling the BMS management module is further configured in the flight controller, and the circuit control strategy is specifically:

[0017] During landing, the flight controller sends a power-off instruction, the BMS management module controls the normally closed relay to be turned off, controls the power-on circuit to be turned off, so that the contactor loses power, the power-on circuit is turned off, and sends a disconnection instruction for turning off the pre-charge switch to control the pre-charge switch to be turned off.

[0018] As a further improvement of the present invention, both the pre-charge switch and the power-on switch can be electrically connected control or manual control controlled by the flight controller.

[0019] Advantages of the present invention: By providing a power-on circuit and a pre-charge circuit, and regulating them through a switch assembly, when powering on, to prevent excessive instantaneous current from burning out the rotor motor, the switch assembly first controls the pre-charge circuit to power on the rotor motor. After stable power-on, by controlling the conduction of the power-on circuit and the rotor motor, the pre-charge circuit is short-circuited, so as to stably supply power to the rotor motor through the power-on circuit. Under the action of the battery management subsystem, it is possible to stably analyze the power supply requirements between circuits and perform intelligent control, achieving the effect of reducing the inrush current during power-on on the premise of providing a large current and protecting the stable operation of the motor. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 To show the power supply system diagram of the present invention.

[0021] Reference numerals: 1, flight controller; 2, battery pack; 3, pre-charge switch group; 31, pre-charge switch; 32, pre-charge relay; 33, pre-charge resistor; 4, power-on switch group; 41, power-on switch; 42, contactor; 5, external power supply; 6, BMS management module; 7, normally-closed relay; 8, rotor motor. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0022] The present invention will be further described in detail below with reference to the drawings and embodiments. The same components are denoted by the same reference numerals. It should be noted that the terms "front", "rear", "left", "right", "upper" and "lower" used in the following description refer to the directions in the drawings, and the terms "bottom surface" and "top surface", "inner" and "outer" respectively refer to the directions towards or away from the geometric center of a specific component.

[0023] Refer to Figure 1 As shown, a specific embodiment of a battery system for a manned aircraft of the present invention includes: a flight controller 1, an upper electronic system and a battery management subsystem. The flight controller 1 is disposed in the airframe, and a plurality of rotors are provided on the airframe. The rotors are driven by rotor motors 8, and a plurality of rotor motors 8 are provided. Two of the rotor motors 8 are connected to an upper electronic system, so that an upper electronic system controls two juxtaposed rotor motors 8 to drive.

[0024] The upper electronic system includes a battery pack 2, a pre-charge circuit, a power-on circuit, and a switch assembly. The battery pack 2 is connected to a rotor motor 8 that drives the rotor to rotate through the power-on circuit. The pre-charge circuit is also connected to the power-on circuit. The pre-charge circuit is used to pre-charge the rotor motor 8. The switch assembly includes a pre-charge switch group 31 of 3 and a power-on switch group 41 of 4. The pre-charge switch group 31 of 3 is used to connect the battery pack 2 and the pre-charge circuit, and control the pre-charge circuit to conduct to pre-charge the rotor motor 8. The power-on switch group 41 of 4 is used to connect the power-on circuit and the rotor motor 8, and control the conduction of the power-on circuit and the rotor motor 8. One of the pre-charge switch group 31 of 3 and the power-on switch group 41 of 4 is kept closed, and the other is open.

[0025] The battery management subsystem includes an external power supply 5 and a BMS management module 6. The external power supply 5 is used to supply power to the BMS management module 6 and the switch assembly. The BMS management module 6 is used to control the disconnection of the power-on switch group 41 of 4. A serial port is provided on the flight controller 1. The BMS management module 6 is also connected to the serial port.

[0026] The pre-charge switch group 31 of 3 includes a pre-charge switch 31, a pre-charge relay 32, and a pre-charge resistor 33. The pre-charge switch 31 is connected to the external power supply 5. The pre-charge resistor 33 is arranged on the pre-charge circuit. The pre-charge switch 31 is used to control the pre-charge relay 32 to be turned on, so as to control the pre-charge circuit to conduct with the rotor motor 8 and pre-charge the rotor power. The power-on switch group 41 of 4 includes a power-on switch 41 and a contactor 42. The power-on switch 41 is connected to the external power supply 5. The power-on switch 41 is used to control the contactor 42 to connect the power-on circuit and the rotor motor 8. When the power-on circuit is connected to the rotor motor 8, the pre-charge circuit is short-circuited. Both the pre-charge switch 31 and the power-on switch 41 can be electrically connected and controlled or manually controlled by the flight control.

[0027] The number of the BMS management modules 6 is the same as the number of the upper electronic systems. The BMS management modules 6 are connected by CAN bus communication. The power-on switch group 41 of 4 further includes a normally closed relay 7. The normally closed relay 7 is arranged between the power-on switch 41 and the external power supply 5. The BMS management module 6 is connected to the normally closed relay 7 and is used to control the normally closed relay 7 to be turned off, so as to cut off the power supply of the power-on circuit to the rotor motor 8.

[0028] A circuit control strategy for controlling the BMS management module 6 is further configured in the flight controller 1. The circuit control strategy is specifically as follows:

[0029] During landing, the flight control sends a power-off command, and the BMS management module 6 controls the normally closed relay 7 to disconnect, controls the power-on circuit to disconnect, so that the contactor 42 loses power, the power-on circuit disconnects, and sends a disconnection command to disconnect the precharge switch 31, controls the precharge switch 31 to disconnect, and realizes the opening and closing of the precharge switch 31 and the power-on switch 41 under the action of the flight control through the BMS management module 6.

[0030] Working principle and its effects:

[0031] First, since the current of the battery pack 2 is too large, in order to prevent the motor from being burned out instantly after power-on, a precharge circuit needs to be added, and its function is to protect the motor. Therefore, first manually turn on multiple precharge switches 31. The external power supply 5 receives the power-on logic and supplies power to the precharge relay 32, controls the entire precharge circuit to perform power-on of the rotor motor 8, and the connected precharge resistor 33 precharges the motor. After the circuit works normally for a period of time, the short-circuit logic of the precharge resistor 33 is executed.

[0032] After precharging, then enter the most important task in the entire electrical system, driving the power-on circuit to execute the power-on logic. First, turn on the power-on switch 41. The normally closed relay 7 does not receive a signal and remains closed. The external power supply 5 receives the power supply signal to make the power-on loop conduct. After the contactor 42 receives the electrical signal, it executes the switch closing logic. Thus, after the entire power-on circuit is powered on, the power-on is completed, and the rotor motor 8 executes the operation of driving the rotor to rotate, so as to realize operations such as the overall body hovering flight.

[0033] After the body lands, the flight control sends a power-off command to the BMS management module 6. The BMS management modules 6 transmit the power-off command through the CAN bus. After all the BMS management modules 6 receive the power-off command, the normally closed relay 7 receives the disconnection signal and executes the disconnection switch logic. Thus, the power-on circuit of the contactor 42 also disconnects, the entire power circuit disconnects, the rotor motor 8 executes the stop power supply signal, the rotor stops rotating, and finally the precharge switch 31 is also disconnected.

[0034] By setting the power-on circuit and the precharge circuit, and regulating through the switch assembly, so that when power-on is performed, in order to prevent the instantaneous current from being too large and causing the rotor motor 8 to be burned out, the switch assembly first controls the precharge circuit to perform power-on on the rotor motor 8. After stable power-on, by controlling the conduction of the power-on circuit and the rotor motor 8, the precharge circuit is short-circuited, and stable power supply to the rotor motor 8 is realized through the power-on circuit. Under the action of the battery management subsystem, it is possible to stably analyze the power supply requirements between circuits and perform intelligent control, achieving the effect of reducing the inrush current during power-on on the premise of providing a large current and protecting the motor to work stably.

[0035] The above are only the preferred embodiments of the present invention, and the protection scope of the present invention is not limited to the above embodiments. All technical solutions within the concept of the present invention belong to the protection scope of the present invention. It should be noted that for those of ordinary skill in the art, without departing from the principle of the present invention, several improvements and refinements should also be regarded as within the protection scope of the present invention.

Claims

1. A battery system for a manned aircraft, characterized in that, Including: A flight controller (1), which is arranged in the airframe; An upper electronic system, which includes a battery pack (2), a pre-charge circuit, a power-on circuit, and a switch assembly. The battery pack (2) is connected to a rotor motor (8) that drives the rotor to rotate through the power-on circuit. The pre-charge circuit is also connected to the power-on circuit. The pre-charge circuit is used to pre-charge the rotor motor (8). The switch assembly includes a pre-charge switch (31) group (3) and a power-on switch (41) group (4). The pre-charge switch (31) group (3) is used to connect the battery pack (2) and the pre-charge circuit, and control the pre-charge circuit to conduct to pre-charge the rotor motor (8). The power-on switch (41) group (4) is used to connect the power-on circuit and the rotor motor (8), and control the conduction of the power-on circuit and the rotor motor (8). One of the pre-charge switch (31) group (3) and the power-on switch (41) group (4) is kept closed, and the other is open; A battery management subsystem, which includes an external power supply (5) and a BMS management module (6). The external power supply (5) is used to supply power to the BMS management module (6) and the switch assembly. The BMS management module (6) is used to control the disconnection of the power-on switch (41) group (4). A serial port is arranged on the flight controller (1), and the BMS management module (6) is also connected to the serial port; The pre-charge switch (31) group (3) includes a pre-charge switch (31), a pre-charge relay (32), and a pre-charge resistor (33). The pre-charge switch (31) is connected to the external power supply (5). The pre-charge resistor (33) is arranged on the pre-charge circuit. The pre-charge switch (31) is used to control the pre-charge relay (32) to be turned on, so as to control the pre-charge circuit to conduct with the rotor motor (8) and pre-charge the rotor power; The power-on switch (41) group (4) includes a power-on switch (41) and a contactor (42). The power-on switch (41) is connected to the external power supply (5). The power-on switch (41) is used to control the contactor (42) to connect the power-on circuit and the rotor motor (8). When the power-on circuit is connected to the rotor motor (8), the pre-charge circuit is short-circuited; The number of the BMS management modules (6) is the same as the number of the upper electronic system lines; The power-on switch (41) group (4) further includes a normally closed relay (7). The normally closed relay (7) is arranged between the power-on switch (41) and the external power supply (5). The BMS management module (6) is connected to the normally closed relay (7), and is used to control the normally closed relay (7) to be turned off, so as to disconnect the power supply of the power-on circuit to the rotor motor (8); The BMS management modules (6) are communicatively connected through a CAN bus; A circuit control strategy for controlling the BMS management module (6) is further configured in the flight controller (1). The circuit control strategy is specifically: During landing, the flight control sends a power-off command, and the BMS management module (6) controls the normally closed relay (7) to disconnect, controls the power-on circuit to disconnect, so that the contactor (42) loses power, the power-on circuit disconnects, and sends a disconnection command for the precharge switch (31) to disconnect, controlling the precharge switch (31) to disconnect.

2. The battery system of a manned aircraft according to claim 1, characterized in that: A number of the rotor motors (8) are provided, and two of the rotor motors (8) are connected to one upper electronic system, so that one upper electronic system controls two juxtaposed rotor motors (8) to drive.

3. The battery system of a manned aircraft according to claim 1, wherein: Both the precharge switch (31) and the power-on switch (41) are electrically connected and controlled or manually controlled under the control of the flight control.

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