A power distribution system for aircraft

Abstract

This patent discloses a power distribution system for aircraft, which belongs to the field of aviation electrical systems and is used to provide a power source for new energy vertical take-off and landing aircraft. Compared with existing aircraft, it simplifies the power supply structure, reduces the weight and complexity of the aircraft electrical system, improves the reuse and safety of components in the aircraft electrical system, and simplifies the power management system, making the power control method more concise. The system includes a power lithium battery system, a fuel cell system, an auxiliary battery system, a low-voltage battery system and a power distribution system.

Description

Technical Field

[0001] The present invention relates to the field of aviation electrical systems, and in particular to a power distribution system for an aircraft. Background Art

[0002] With the development of new green energy technologies such as hydrogen fuel and lithium batteries, the aviation field is currently focusing more and more on all-electric technology research. Compared with traditional fuel-powered aircraft, all-electric aircraft have linear decoupling of energy and power systems, and their power is relatively size-independent. At the same time, they have low noise, zero emissions, and low aircraft operating costs, representing the future development direction of aircraft. Summary of the invention

[0003] The power distribution system for aircraft disclosed in the present invention is applicable to a new energy vertical take-off and landing aircraft developed by the applicant. The aircraft adopts a composite wing layout of fixed wings combined with multi-rotor wings, and the appearance diagram is shown in the attached figure. Figure 1 As shown. The working modes of the vertical take-off and landing aircraft are divided into vertical take-off and landing mode and fixed-wing mode, and the power system is divided into a four-axis eight-propeller electric rotor part and an electric tail thrust part. In the vertical take-off and landing mode, the four-axis eight-propeller electric rotor provides power for vertical take-off and landing; in the fixed-wing mode, the electric tail thruster (tail propulsion system) provides power for aircraft cruising. In the new energy vertical take-off and landing aircraft, lithium batteries and fuel cells are used as power sources.

[0004] In order to reduce the complexity and system weight of the power supply system of the new energy vertical take-off and landing aircraft, improve the system safety, and take into account the voltage and power characteristics of lithium batteries and fuel cells, the present application provides a power distribution system for aircraft. On the basis of providing a power source for the new energy vertical take-off and landing aircraft, the system simplifies the power supply structure compared to existing aircraft, reduces the weight and complexity of the aircraft electrical system, improves the reuse and safety of components in the aircraft electrical system, and simplifies the power management system, making the power control method simpler.

[0005] The present invention provides a power distribution system for an aircraft, the system comprising the following parts:

[0006] A power lithium battery system, comprising at least one group of power lithium batteries, for supplying power to the vertical take-off and landing system;

[0007] A fuel cell system, comprising a fuel cell, wherein the fuel cell stack adopts a distributed design and is used to supply power to a cruise power system;

[0008] An auxiliary battery system, comprising at least one group of lithium batteries, connected in parallel with the fuel cell system, for assisting the power lithium battery system and / or the fuel cell system in supplying power, wherein the voltage of the lithium batteries of the auxiliary battery system is consistent with that of the lithium batteries in the power lithium battery system;

[0009] A low-voltage battery system, comprising at least one set of low-voltage lithium batteries, wherein the fuel cell system provides low-voltage power to the aircraft together with the low-voltage battery system by converting the voltage;

[0010] The power distribution system includes a power bus, a communication bus, and a power controller, which are used to distribute, control, and manage the power provided by the battery system. Since the lithium battery and the fuel cell in the system are both arranged in a distributed manner, the current source characteristics of the fuel cell and the voltage source characteristics of the lithium battery are used for direct parallel power supply, which reduces the weight and complexity of the system, and the auxiliary lithium battery method is used to improve the system reuse and safety.

[0011] The power battery system only provides power for the vertical take-off and landing system and does not participate in the power supply of the cruise power system, thereby ensuring the safety of the rotor system.

[0012] The auxiliary battery system is clamped by diodes to realize power supply for both vertical take-off and landing and fixed-wing modes, thereby achieving functional reuse, reducing system weight, and ensuring the safety of the power lithium battery system. The voltage of the auxiliary battery system is consistent with that of the power lithium battery system, simplifying the energy management of the power supply system.

[0013] In the above power supply system, the power controller specifically includes a high voltage distribution box, a low voltage distribution box, a fuel cell distribution box, and a battery management system;

[0014] Among them, the high-voltage distribution box includes:

[0015] At least one port for connecting a power lithium battery system;

[0016] at least one port for connecting an auxiliary battery system;

[0017] at least one port for connection to a vertical take-off and landing system;

[0018] a port for connecting the fuel cell system;

[0019] The at least one port connected to the power lithium battery system and the at least one port connected to the auxiliary battery system are connected to the at least one port connected to the vertical take-off and landing system through a first bus;

[0020] The at least one port connected to the auxiliary battery system is connected to the at least one port connected to the auxiliary battery system through a second bus.

[0021] Among them, the low voltage distribution box includes:

[0022] at least one input port for connection to a low voltage battery system;

[0023] at least one input port connected to a fuel cell system;

[0024] At least one output port for connecting to an aircraft low-pressure load;

[0025] at least one voltage converter;

[0026] The input port of the at least one low-voltage battery system is connected to at least one low-voltage load output via a bus;

[0027] The fuel cell input is connected to at least one low-voltage load output through the bus bar.

[0028] Among them, the fuel cell distribution box includes:

[0029] at least one fuel cell stack input port;

[0030] at least one auxiliary battery system input port;

[0031] at least one tail thruster electronic speed governor port;

[0032] At least one low voltage output port;

[0033] at least one voltage converter;

[0034] The at least one fuel cell stack input port and the at least one auxiliary battery system input port are connected to the at least one tail thruster electronic speed governor through a manifold;

[0035] The at least one fuel cell stack input port and the at least one auxiliary battery system input port are connected to the at least one low-voltage output port through the busbar and the at least one voltage converter;

[0036] The battery management system includes a sub-battery management system and a unit battery management system. The sub-battery management system manages the use of each battery pack, and the unit battery management system manages the use of all battery packs connected to the power distribution box.

[0037] The battery management system adopts a master-slave mode, and a single battery group is controlled by a corresponding controller to ensure fault isolation and system safety. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings required for use in the description of the embodiments of the present invention will be briefly introduced below. Obviously, the accompanying drawings in the following description are only some embodiments of the present invention. For ordinary technicians in this field, other accompanying drawings can be obtained based on these accompanying drawings without paying creative labor.

[0039] Figure 1It is an appearance diagram of a new energy vertical take-off and landing aircraft using the power distribution system of the present invention;

[0040] Figure 2 is a schematic diagram of a power distribution system for an aircraft in one embodiment of the present invention, wherein the solid line in the diagram represents a power bus;

[0041] Figure 3 This is a schematic diagram of a high-voltage distribution box in one embodiment of the present invention. The port names, devices, and functions in the figure are detailed in the following table:

[0042]

[0043]

[0044] Figure 4 This is a schematic diagram of a low-voltage distribution box in an embodiment of the present invention. The port names, devices, and functions in the figure are detailed in the following table:

[0045] Port Name Port Device Port Function B0 Low voltage lithium battery 00 Low voltage battery system input B01 Low voltage lithium battery 01 Low voltage battery system input L01 Fuel cell distribution box Fuel cell 28V low voltage input Z01 Aircraft low pressure load Powering 28V low voltage loads Z02 Aircraft low pressure load Powering 28V low voltage loads Z03 Aircraft low pressure load Powering 12V low voltage loads

[0046] Figure 5 Schematic diagram of a fuel cell power distribution box in one embodiment of the present invention. The port names, devices, and functions in the figure are detailed in the table below:

[0047]

[0048]

[0049] Figure 6 This is the connection relationship of the battery control system in one embodiment of the present invention, and the dotted line in the figure is the pass bus. DETAILED DESCRIPTION

[0050] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0051] In one embodiment of the present invention, a power distribution system for an aircraft is provided. Figure 2 .

[0052] The power lithium battery system includes at least one set of high-power lithium batteries, which are mainly used for vertical take-off and landing systems ( Figure 1In one embodiment of the present invention, the number of high-power lithium battery packs is 6. To ensure the safety of the vertical take-off and landing system, the power lithium battery system does not participate in the power supply of the cruise power system, and the fuel cell power is supplemented by the auxiliary lithium battery.

[0053] The fuel cell system includes a fuel cell and adopts a distributed stack method to supply the cruise power system ( Figure 1 The propeller at the tail of the aircraft) is used to power the fixed-wing cruise function. In one embodiment provided by the present invention, the fuel cell is a hydrogen fuel cell. The fuel cell system and the auxiliary battery system are directly connected in parallel to supply power to the cruise power system. The fuel cell is redundantly connected with the low-voltage battery system through DCDC conversion to supply power to the low-voltage electrical equipment of the aircraft.

[0054] The auxiliary battery system includes at least one group of lithium batteries, which mainly realizes parallel power supply of lithium batteries and fuel cells. In one embodiment provided by the present invention, the auxiliary battery system includes two groups of lithium batteries. The auxiliary battery system, together with the power battery system, supplies power to the vertical take-off and landing system during vertical take-off and landing. In the fixed-wing mode, it supplies power to the cruise power system together with the fuel cell. In this architecture, the lithium batteries in the auxiliary battery system are clamped by diodes to ensure unidirectional current flow, realize power supply for both vertical take-off and landing and fixed-wing modes, realize functional reuse of the auxiliary battery system, and reduce the weight of the system. At the same time, as a backup for the power battery system, the safety of the power battery system is guaranteed. The voltage of the lithium batteries in the auxiliary battery system is consistent with that of the lithium batteries in the power battery system, which simplifies the energy management of the system.

[0055] The low-voltage battery system includes at least one group of low-voltage lithium batteries. The fuel cell system provides low-voltage power to the aircraft together with the low-voltage battery system by converting the voltage, forming a redundant power supply system to ensure safety.

[0056] The electric energy distribution system includes a power bus, a communication bus, and a power controller, which are used to distribute, control, and manage the electric energy provided by the battery system. In one embodiment provided by the present invention, the power controller includes a high-voltage distribution box, a low-voltage distribution box, a fuel cell distribution box, and a battery management system. The distribution box mainly completes the distribution, control, and management of electric energy to ensure the operation of the power system. The battery management system adopts a master-slave mode in control. A single group of batteries is controlled by the corresponding sub-battery control system. The unit battery control system in the low-voltage distribution box and the high-voltage distribution box centrally controls the battery system at the input end of the distribution box to ensure fault isolation and system safety. The battery management system is connected to the aircraft's onboard electronic equipment through a communication bus.

[0057] In one embodiment provided by the present invention, the structure of the high voltage distribution box is as follows: Figure 3 As shown in the figure, the port information marked in the figure is as follows:

[0058] Port Name Port Device Port Function B1 Power lithium battery 1 Power lithium battery system input B2 Power lithium battery 2 Power lithium battery system input B3 Power lithium battery 3 Power lithium battery system input B4 Power lithium battery 4 Power lithium battery system input B5 Power lithium battery 5 Power lithium battery system input B6 Power lithium battery 6 Power lithium battery system input B7 Auxiliary lithium battery 1 Auxiliary battery system input B8 Auxiliary lithium battery 2 Auxiliary battery system input M1 Electronic speed controller Powering vertical take-off and landing systems M2 Electronic speed controller Powering vertical take-off and landing systems M3 Electronic speed controller Powering vertical take-off and landing systems M4 Electronic speed controller Powering vertical take-off and landing systems M5 Electronic speed controller Powering vertical take-off and landing systems M6 Electronic speed controller Powering vertical take-off and landing systems M7 Electronic speed controller Powering vertical take-off and landing systems M8 Electronic speed controller Powering vertical take-off and landing systems H01 Fuel cell distribution box Auxiliary battery system output

[0059] In this embodiment, the high voltage distribution box specifically includes:

[0060] 6 input ports B1-B6 connected to the power lithium battery system;

[0061] 2 input ports B7 and B8 connected to the auxiliary battery system;

[0062] 8 output ports M1-M8 connected to the electronic speed regulator of the vertical take-off and landing system;

[0063] A port H01 connected to the fuel cell system;

[0064] The six input ports B1-B6 connected to the power lithium battery system and the two input ports B7 and B8 connected to the auxiliary battery system are connected to the eight output ports M1-M8 connected to the electronic speed regulator in the vertical take-off and landing system through a first bus, so as to enable the power lithium battery system and / or the auxiliary battery system to supply power to the vertical take-off and landing system.

[0065] Two input ports B7 and B8 connected to the auxiliary battery system are connected to the port H01 connected to the fuel cell system through a second bus. The H01 port is connected to the fuel cell distribution box to supply power to the cruise power system.

[0066] The two input ports B7 and B8 connected to the auxiliary battery system are clamped with the first and second buses through diodes, thereby realizing two power supply modes of the auxiliary battery system supplying power to the vertical take-off and landing system and to the cruise power system, thereby realizing function reuse, reducing system weight and ensuring safety.

[0067] In one embodiment provided by the present invention, the structure of the low voltage distribution box is as follows: Figure 4 As shown in the figure, the port information marked in the figure is as follows:

[0068] Port Name Port Device Port Function B0 Low voltage lithium battery 00 Low voltage battery system input B01 Low voltage lithium battery 01 Low voltage battery system input L01 Fuel cell distribution box Fuel cell 28V low voltage input Z01 Aircraft low pressure load Powering 28V low voltage loads Z02 Aircraft low pressure load Powering 28V low voltage loads Z03 Aircraft low pressure load Powering 12V low voltage loads

[0069] In one embodiment provided by the present invention, the low-voltage distribution box specifically includes:

[0070] 2 input ports B0 and B01 connected to the low voltage battery system;

[0071] 1 28V input port L01 connected to the fuel cell system;

[0072] 3 output ports Z01-Z03 for connecting aircraft low-pressure loads;

[0073] 1 voltage converter, connected to the bus and Z03 port, used to convert 28V voltage into 12V voltage to power the aircraft's 12V low-voltage load;

[0074] Two input ports B0 and B01 connected to the low-voltage battery system are connected to three output ports Z01-Z03 connected to the aircraft low-voltage loads through a bus bar;

[0075] 1 28V input port L01 connected to the fuel cell system, connected to 3 output ports Z01-Z03 connected to the aircraft low-voltage loads through the bus;

[0076] In one embodiment provided by the present invention, the structure of the fuel cell distribution box is as follows: Figure 5 As shown in the figure, the port information marked in the figure is as follows:

[0077] Port Name Port Device Port Function FC1 Fuel cell stack Fuel cell stack input FC2 Fuel cell stack Fuel cell stack input FC3 Fuel cell stack Fuel cell stack input FC4 Fuel cell stack Fuel cell stack input FC5 Fuel cell stack Fuel cell stack input FC6 Fuel cell stack Fuel cell stack input H01 High voltage distribution box Auxiliary battery system input M9 Tail thrust electronic speed controller Power supply for tail thruster electronic speed controller L01 Low voltage distribution box Fuel cell 28V output

[0078] The fuel cell distribution box specifically comprises:

[0079] 6 fuel cell stack input ports FC1-FC6;

[0080] 1 auxiliary battery system input port H01, which is connected to the high-voltage distribution box;

[0081] 1 tail thruster electronic speed governor port M9;

[0082] 1 low voltage output port L01, which is connected to the low voltage distribution box;

[0083] 1 DCDC converter, used to convert the voltage output by the fuel cell into 28V, and supply power to the aircraft's low-voltage loads through a low-voltage distribution box;

[0084] Six fuel cell stack input ports FC1-FC6 and one auxiliary lithium battery input port H01 are connected to one tail thruster electronic speed governor port M9 through a manifold to supply power to the aircraft tail thruster;

[0085] Six fuel cell stack input ports FC1-FC6 and one auxiliary battery system input port H01 are connected to one low-voltage output port L01 through the manifold and one DCDC converter to supply power to the aircraft low-voltage load;

[0086] In one embodiment of the present invention, the connection relationship of the battery management system is as follows: Figure 6As shown, the dotted line in the figure is the communication bus, and the communication bus connects the sub-battery management system and the unit battery management system. The sub-battery management system manages the use of each battery pack, and the unit battery management system manages the use of all battery packs connected to the distribution box. The battery management system is connected to the electronic flight control system (electronic flight control system) in the aircraft recording electronic equipment through a communication line to control the use of the battery.

[0087] The above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit the same. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that the technical solutions described in the aforementioned embodiments may still be modified, or some of the technical features may be replaced by equivalents. Such modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention, and should be included in the protection scope of the present invention.

Claims

1. A power distribution system for an aircraft, characterized in that: The system comprises: A power lithium battery system, comprising at least one group of power lithium batteries, for supplying power to the vertical take-off and landing system; A fuel cell system, comprising a fuel cell, wherein the fuel cell system adopts a distributed design and is used to supply power to a cruise power system; An auxiliary battery system, comprising at least one group of lithium batteries, connected in parallel with the fuel cell system, for assisting the power lithium battery system and / or the fuel cell system in supplying power, wherein the voltage of the lithium batteries of the auxiliary battery system is consistent with that of the lithium batteries in the power lithium battery system; A low-voltage battery system, comprising at least one set of low-voltage lithium batteries, wherein the fuel cell system provides low-voltage power to the aircraft together with the low-voltage battery system by converting the voltage; An electric energy distribution system, including a power bus, a communication bus, and a power controller, for distributing, controlling, and managing the electric energy provided by the battery system; The power controller specifically includes: a high-voltage distribution box, a low-voltage distribution box, a fuel cell distribution box, and a battery management system; The high voltage distribution box comprises: At least one port for connecting a power lithium battery system; at least one port for connecting an auxiliary battery system; at least one port for connection to a vertical take-off and landing system; a port for connecting the fuel cell system; The at least one port connected to the power lithium battery system and the at least one port connected to the auxiliary battery system are connected to the at least one port connected to the vertical take-off and landing system through a first bus; The at least one port connected to the auxiliary battery system is connected to the at least one port connected to the auxiliary battery system through a second bus; The low voltage distribution box comprises: at least one input port for connection to a low voltage battery system; at least one input port connected to a fuel cell system; At least one output port for connecting to an aircraft low-pressure load; at least one voltage converter; The input port of the at least one low-voltage battery system is connected to at least one low-voltage load output via a bus; The fuel cell input is connected to at least one low-voltage load output through the bus bar; The fuel cell distribution box specifically comprises: at least one fuel cell stack input port; at least one auxiliary battery system input port; at least one tail thruster electronic speed governor port; At least one low voltage output port; at least one voltage converter; The at least one fuel cell stack input port and the at least one auxiliary battery system input port are connected to the at least one tail thruster electronic speed governor through a manifold; The at least one fuel cell stack input port and the at least one auxiliary battery system input port are connected to the at least one low-voltage output port through the busbar and the at least one voltage converter.

2. The power distribution system for an aircraft according to claim 1, characterized in that: The power bus connects the battery system, the power distribution system and the power-consuming equipment; the communication bus is connected to the power controller.

3. The power distribution system for an aircraft according to claim 1, characterized in that: The battery management system includes a sub-battery management system and a unit battery management system. The sub-battery management system manages the use of each battery pack, and the unit battery management system manages the use of all battery packs connected to the power distribution box.

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