Avionics system of aircraft and aircraft

Abstract

The avionics system comprises a plurality of power battery boxes, a motor, a temperature manager, a power supply manager, a power distribution controller and an avionics host, the power battery boxes, the temperature manager and the power supply manager are arranged in a battery cabin of the aircraft, and the power distribution controller is arranged in a battery cabin of the aircraft. The power battery box is connected with the motor through the power manager, the power battery box comprises a plurality of battery cells, a plurality of temperature detection pieces, a heat dissipation assembly and a fire extinguishing assembly, and the temperature manager is connected with the temperature detection pieces, the heat dissipation assembly, the fire extinguishing assembly and the power manager. The avionics host is connected with the temperature manager, the power manager and the power distribution controller, the power distribution controller is connected with the power manager, and the power distribution controller is arranged in an equipment compartment of the aircraft. According to the utility model, the model of the aircraft can be conveniently changed, and the safety and the reliability are enhanced.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft, and in particular to an avionics system of an aircraft and the aircraft. Background Art

[0002] With the development of aviation technology, electric aircraft powered by power batteries are becoming increasingly popular. Electric aircraft have higher requirements for safety and reliability than traditional aircraft. The avionics system in existing electric aircraft includes a power system containing a power battery pack and other systems such as a power distribution controller, flight control and navigation unit. The existing avionics system cannot achieve rapid design and development of aircraft of different models with different flight times. At the same time, since the power battery has strict requirements on voltage, temperature and current, improper use may cause smoke, combustion, explosion and other phenomena, causing thermal runaway. The existing avionics system lacks preventive measures for the above phenomena and lacks safety and reliability. Utility Model Content

[0003] In order to solve at least one of the problems mentioned in the above background technology, the utility model provides an avionics system of an aircraft and an aircraft, which can facilitate the model replacement of the aircraft and enhance safety and reliability.

[0004] The specific technical solutions provided by the utility model are as follows:

[0005] In a first aspect, an avionics system of an aircraft is provided, comprising a plurality of power battery boxes, a motor, a temperature manager, a power manager, a power distribution controller and an avionics host, wherein the power battery box, the temperature manager and the power manager are arranged in a battery compartment of the aircraft, the power battery box is connected to the motor via the power manager, the motor is connected to a rotor of the aircraft, the power battery box comprises a plurality of battery cells, a plurality of temperature detection components, a heat dissipation component and a fire extinguishing component, the plurality of temperature detection components are used to detect the temperature of the battery cells at different positions, the temperature manager connects the temperature detection components, the heat dissipation component, the fire extinguishing component and the power manager, the avionics host is connected to the temperature manager, the power manager and the power distribution controller, the power distribution controller is connected to the power manager, the power distribution controller is arranged in the equipment compartment of the aircraft, and the avionics host is arranged in the cockpit of the aircraft.

[0006] As a preferred embodiment of the above scheme, the power battery box also includes a box body, the battery cell, the temperature detection component and the fire extinguishing assembly are arranged in the box body, the fire extinguishing assembly includes a trigger component and a fire extinguishing component connected to each other, the heat dissipation assembly is used to dissipate heat from the battery cell, and a power supply connector and a control connector are provided on the box body, one end of the control connector is respectively connected to the temperature detection component, the trigger component and the heat dissipation assembly, the other end of the control connector is connected to the temperature manager, and one end of the power supply connector is connected to the battery cell, and the other end is connected to the power manager.

[0007] As a preferred embodiment of the above solution, the temperature manager is connected to the control connector and the avionics host through a CAN bus.

[0008] As a preferred embodiment of the above scheme, the avionics system of the aircraft also includes a flight control and navigation unit, which is connected to the power distribution controller and the motor, and is connected to the avionics host via a CAN bus, and is arranged in the equipment compartment.

[0009] As a preferred embodiment of the above solution, the motor is connected to an electronic speed regulator, the electronic speed regulator is connected to the power manager, and the flight control and navigation unit are connected to the electronic speed regulator via a CAN bus.

[0010] As a preferred embodiment of the above solution, the avionics system of the aircraft further includes an emergency parachute unit and a lighting unit, both of which are connected to the power distribution controller, and the emergency parachute unit is arranged in the cockpit.

[0011] As a preferred embodiment of the above solution, the power manager includes a fuse, and the power distribution controller includes a relay.

[0012] As a preferred embodiment of the above solution, the avionics system of the aircraft further includes a display screen, which is connected to the power distribution controller and is arranged in the cockpit.

[0013] As a preferred embodiment of the above solution, the avionics host is connected to the power manager, the power distribution controller and the display screen via a CAN bus respectively.

[0014] By means of the above technical scheme, the avionics system of the aircraft of the utility model is provided with multiple power battery boxes, motors, temperature managers, power managers, power distribution controllers and avionics hosts. The power battery boxes are connected to the motors through the power managers and drive the motors to rotate, thereby driving the rotors to rotate. Multiple power battery boxes adopt the same architecture and voltage design, which is convenient for rapid replacement and quantitative production, and realizes rapid design of aircraft with different flight times. The temperature manager collects the temperature of the power battery boxes to manage the temperature of the power battery boxes to ensure the safety of the aircraft. The power manager monitors the various working states of the battery cells in the power battery boxes to prevent overcharging or over-discharging. The power distribution controller provides power to the avionics host and other equipment. The avionics host is used for aircraft status display and emergency processing. The modular design of the above-mentioned various components facilitates the development and design of aircraft of different models and the replacement of aircraft models. In addition, multiple temperature detection The temperature manager can detect the temperature of the battery cells at different positions in the power battery box. Since the heat dissipation conditions of the battery cells in the middle of the power battery box are worse than those of the battery cells in the outer layer, the temperature manager collects the temperature of the battery cells in each part of the power battery box through multiple temperature detection components, and intelligently adjusts the heat dissipation of the heat dissipation components according to the temperature, so as to ensure that the battery cells work in a healthy and stable ambient temperature, and fully ensure the stable operation of the power battery box. At the same time, when the temperature detection component detects that the temperature of the battery cell is too high and causes smoke or burning, the temperature manager controls the fire extinguishing component to start the fire extinguishing function, and controls the fault inside the power battery box, which greatly ensures the safety of the aircraft. At the same time, the temperature manager can display the temperature of the battery cell on the avionics host, and the voltage, current and charge and discharge status of the battery cell can be displayed through the power manager, so as to monitor the status of the battery cell in real time and perform emergency processing through the avionics host, further ensuring the safety of the aircraft and enhancing safety and reliability.

[0015] In a second aspect, an aircraft is provided, comprising the avionics system, equipment compartment, battery compartment, cockpit and rotor of the aircraft as described above, wherein an avionics host and an operating console are provided in the cockpit, the avionics host is arranged on the operating console, a power distribution controller is provided in the equipment compartment, a plurality of power battery boxes as well as a temperature manager and a power manager are provided in the battery compartment, and the rotor is driven to rotate by a motor.

[0016] By means of the above technical scheme, the aircraft of the utility model arranges the avionics host and the operating console in the cockpit, arranges the power distribution controller in the equipment compartment, and arranges the power battery box, the temperature manager and the power manager in the battery compartment. In this way, the different accommodation spaces on the aircraft are fully utilized to meet the position allocation of various parts of the avionics system. At the same time, the various parts of the avionics system are placed in appropriate positions on the aircraft, so that the role of each part can be fully exerted, further enhancing the reliability of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0018] Figure 1 It is a schematic diagram of the structure of the aircraft of the utility model;

[0019] Figure 2 This is a schematic diagram of the structure of the CAN bus connection of the utility model;

[0020] Figure 3 It is a schematic diagram of the connection structure of the utility model;

[0021] Figure 4 This is a schematic diagram of the structure of the temperature manager of the utility model connected to the power battery box;

[0022] Figure 5 This is a schematic diagram of the structure between the power battery box and the rotor of the utility model;

[0023] Figure 6 This is a schematic diagram of the structure of the power battery box of the utility model;

[0024] Figure 7 for Figure 6 Schematic diagram of the structure after removing the box cover;

[0025] Figure 8 for Figure 6 Another structural diagram after removing the box cover. DETAILED DESCRIPTION

[0026] In order to make the purpose, technical solution and advantages of the utility model clearer, the technical solution in the embodiment of the utility model will be clearly and completely described below in conjunction with the drawings in the embodiment of the utility model. Obviously, the described embodiment is only a part of the embodiment of the utility model, not all of the embodiments. Based on the embodiment of the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0027] As described in the background technology, electric aircraft have a wide range of flight times and models, and the speed of model change is fast. At the same time, compared with traditional aircraft, higher requirements are placed on safety and reliability. Electric vertical take-off and landing aircraft (EVTOL) is a type of electric aircraft. The avionics system of existing electric vertical take-off and landing aircraft cannot realize the rapid design and development of aircraft of different models with different flight times. At the same time, since the power battery has strict requirements on voltage, temperature and current, improper use may cause smoke, combustion, explosion and other phenomena, causing thermal runaway. The existing avionics system lacks preventive measures for the above phenomena and lacks safety and reliability. The avionics system and aircraft of the aircraft of the utility model can facilitate the model change of the aircraft, while enhancing safety and reliability. The embodiments of the present invention are explained in detail below.

[0028] Embodiment 1

[0029] like Figures 1 to 4 As shown, the utility model provides an avionics system of an aircraft, comprising a plurality of power battery boxes 4, a motor 7, a temperature manager 5, a power manager 6, a power distribution controller 2 and an avionics host 3, wherein the power battery box 4, the temperature manager 5 and the power manager 6 are arranged in a battery compartment 102 of the aircraft 1, the power battery box 4 is connected to the motor 7 through the power manager 6, and the motor 7 is connected to a rotor 72 of the aircraft 1, the power battery box 4 comprises a plurality of battery cells 41, a plurality of temperature detection components 42, a heat dissipation component 43 and a fire extinguishing component 44, the plurality of temperature detection components 42 are used to detect the temperature of the battery cells 41 at different positions, the temperature manager 5 is connected to the temperature detection component 42, the heat dissipation component 43, the fire extinguishing component 44 and the power manager 6, the avionics host 3 is connected to the temperature manager 5, the power manager 6 and the power distribution controller 2, the power distribution controller 2 is connected to the power manager 6, the power distribution controller 2 is arranged in the equipment compartment 101 of the aircraft 1, and the avionics host 3 is arranged in the cockpit 103 of the aircraft 1. The power manager 6 is also called BMS (battery management system). The power manager 6 monitors the various working conditions of the battery cells 41 by collecting and sampling information of the battery cells 41, including key parameters such as voltage, current and temperature, so as to prevent overcharging and over-discharging. At the same time, it can control various conditions of the battery cells 41 to ensure their safe use during the charging and discharging process, and monitor the voltage, current, health value and other information of each battery cell 41, and has a battery balancing function to maintain the consistency of each battery cell 41. The power manager 6 is connected to the charging interface 61, and the battery cells 41 can be charged through the charging interface 61.

[0030] like Figure 4 , Figures 6 to 8As shown, the power battery box 4 also includes a box body 45 and a box cover 46, the battery cell 41, the temperature detection member 42 and the fire extinguishing assembly 44 are arranged in the box body 45, the box cover 46 covers the temperature detection member 42 and the fire extinguishing assembly 44, the fire extinguishing assembly 44 includes a trigger member 441 and a fire extinguishing member 442 connected to each other, the heat dissipation assembly 43 is used to dissipate heat for the battery cell 41, the heat dissipation assembly 43 is arranged on the box body 45, and the heat dissipation assembly 43 includes a fan (not shown) and a heat dissipation fin 431, the fan and The heat dissipation fins 431 can effectively achieve air-cooling heat dissipation for the battery cell 41. The box body 45 is provided with a power supply connector 451 and a control connector 452. One end of the control connector 452 is respectively connected to the temperature detection component 42, the trigger component 441 and the fan, and the other end of the control connector 452 is connected to the temperature manager 5. One end of the power supply connector 451 is connected to the battery cell 41, and the other end is connected to the power manager 6. The battery cell 41 supplies power to the motor 7, the power distribution controller 2 and other equipment through the power manager 6. In this embodiment, the temperature detection component 42 is a temperature sensor, the fire extinguishing component 442 is a hot aerosol device, and a jet outlet 443 is provided on one side of the fire extinguishing component 442. When the temperature detection component 42 detects that the temperature of the battery cell 41 is too high and causes smoking or burning, the temperature manager 5 triggers the fire extinguishing component 442 through the trigger component 441 to start the fire extinguishing function, and performs jet aerosol fire extinguishing on the burning battery cell 41 through the jet outlet 443. The fan is powered by the battery cell 41. The temperature manager 5 can intelligently control the speed of the fan through its internal intelligent controller to adjust the heat dissipation of the battery cell 41. This ensures that the battery cell 41 works at a healthy and stable ambient temperature and prevents unnecessary heat dissipation from wasting electricity. The saved electricity can increase the flight time of the aircraft.

[0031] like Figures 1 to 3As shown, the avionics system of the aircraft also includes a flight control and navigation unit 8, an emergency parachute unit 9, a lighting unit 10 and a display screen 20. The flight control and navigation unit 8 is connected to the power distribution controller 2 and the motor 7. The flight control and navigation unit 8 is connected to the avionics host 3 via a CAN bus. The flight control and navigation unit is arranged in the equipment compartment 101. The emergency parachute unit 9 and the lighting unit 10 are both connected to the power distribution controller 2. The emergency parachute unit is arranged in the cockpit. The display screen 20 is connected to the power distribution controller 2. The display screen 20 is connected to the avionics host 3 via a CAN bus. The display screen is arranged in the cockpit 103. In this embodiment, the display screen 20 includes a main display screen 21, a sub-display screen 22 and an intermediate information display screen 23. The main display screen 21, the sub-display screen 22 and the intermediate information display screen 23 are respectively connected to the avionics host 3 through a CAN bus. The lighting unit 10 includes navigation lights of the aircraft, decorative lights in each cabin and landing lights. The flight control and navigation unit 8 collects data from various sensors on the aircraft, such as a gyroscope, an accelerometer and a barometer, to monitor the motion state of the aircraft in real time, and adjusts the speed of the motor 7 according to a predetermined program or ground control instructions to maintain the stability of the flight attitude and heading. The flight control and navigation unit 8 can also use satellite positioning systems such as GPS and Beidou and other auxiliary sensors to provide the aircraft with accurate position and heading information, and control the aircraft by adjusting the speed of the motor 7.

[0032] The temperature manager 5 is connected to the control connector 452 and the avionics host 3 through the CAN bus. The motor 7 is connected to the electronic speed regulator 71 and the rotor 72, and the electronic speed regulator 71 is connected to the power manager 6. The electronic speed regulator 71 is connected to the flight control and navigation unit 8 through the CAN bus. The flight control and navigation unit 8 controls the aircraft by adjusting the speed of the motor 7 by communicating with the electronic speed regulator 71. Compared with traditional signal control, CAN bus control can improve safety and anti-interference ability to reduce control errors between different motors 7. In this embodiment, the power manager 6 includes a fuse (not shown), and the power distribution controller 2 includes a relay (not shown). The fuse serves as a short circuit and overcurrent protector to ensure the safe operation of each unit. The relay is used as a control switch of the circuit to ensure that the power manager 6 provides power to the flight control and navigation unit 8, the avionics host 3, the emergency parachute unit 9 and the lighting unit. In other embodiments, the power distribution controller 2 may also include a fuse to further ensure the safe operation of each unit. Figure 2As shown, the avionics host 3 is connected to the power manager 6 and the power distribution controller 2 through the CAN bus. The CAN bus is an asynchronous serial data communication protocol. The physical layer and data link layer functions of the CAN protocol are integrated in its communication interface, and the framing processing of the communication data can be completed, including bit filling, data block encoding, cyclic redundancy check, priority determination, etc. The CAN bus transmits signals through two lines: CAN high line (corresponding to Figure 2 CAN_1_H and CAN_2_H), CAN low line (corresponding to Figure 2 In the example, CAN_1_L and CAN_2_L are connected, and the signal is converted into a digital signal by the potential difference of the two lines. In this embodiment, except for the above-mentioned CAN bus connection, other connections are connected by power lines ( Figure 1 The dotted line is the CAN bus, and the solid line is the power line).

[0033] The avionics system of the aircraft of the utility model is provided with multiple power battery boxes 4, motors 7, temperature managers 5, power managers 6, power distribution controllers 2 and avionics host computers 3. The power battery boxes 4 are connected to the motors 7 through the power managers 6 and drive the motors 7 to rotate, thereby driving the rotors 72 to rotate. The multiple power battery boxes 4 adopt the same architecture and voltage design, which is convenient for rapid replacement and quantitative production, and realizes the rapid design of aircraft with different flight times. The temperature manager 5 collects the temperature of the power battery boxes 4 to manage the temperature of the power battery boxes 4 to ensure the safety of the aircraft 1. The power manager 6 monitors the various working states of the battery cells 41 in the power battery boxes 4 to prevent overcharging or over-discharging. The power manager 6 is connected to the power distribution controller 2 to supply power to the power distribution controller 2. The power distribution controller 2 provides power to the avionics host computer 3, the flight control and navigation unit 8, the emergency parachute unit 9, the lighting unit and the display screen 20 and other equipment. The avionics host computer 3 is used for aircraft status display and emergency processing. The modular design of the above-mentioned various components is convenient for the development and design of aircraft of different models, and convenient for aircraft Model change; in addition, multiple temperature detection components 42 can detect the temperature of the battery cells 41 at different positions in the power battery box 4. Since the heat dissipation condition of the battery cells 41 in the middle of the power battery box 4 is worse than that of the outer battery cells 41, the temperature manager 5 collects the temperature of the battery cells 41 in each part of the power battery box 4 through multiple temperature detection components 42, and intelligently adjusts the heat dissipation of the heat dissipation component 43 according to the temperature, so as to ensure that the battery cells 41 work at a healthy and stable ambient temperature, and fully ensure the stable operation of the power battery box 4. At the same time, when the temperature detection component 42 detects that the temperature of the battery cell 41 is too high and causes smoke or combustion, the temperature manager 5 controls the fire extinguishing component 44 to start the fire extinguishing function, and controls the fault inside the power battery box 4, which greatly ensures the safety of the aircraft 1. At the same time, the avionics host 3 can display the temperature of the battery cell 41 through the temperature manager 5 and the voltage, current and charge and discharge status of the battery cell 41 through the power manager 6, so as to monitor the status of the battery cell 41 in real time and perform emergency processing through the avionics host 3, further ensuring the safety of the aircraft 1 and enhancing safety and reliability.

[0034] Embodiment 2

[0035] like Figure 3 , Figure 5As shown, the utility model provides an aircraft, including the avionics system, equipment compartment 101, battery compartment 102, cockpit 103, landing gear 104, rotor bracket 105 and rotor 72 of the aircraft as described in Example 1, wherein the cockpit 103 is provided with an avionics host 3, a display screen 20, an operating table 30 and an emergency parachute unit 9 which are interconnected, the avionics host 3 and the display screen 20 are arranged on the operating table 30, the pilot can intuitively understand the flight status and various flight parameters of the aircraft through the display screen 20, and can also perform various routine operations or emergency operations of the aircraft through the operating table 30, the equipment compartment 101 is provided with a power distribution controller 2 and a flight control and navigation unit 8, the The battery compartment 102 is provided with a plurality of power battery boxes 4, a temperature manager 5 and a power manager 6. In this embodiment, the battery compartment 102 is located at the bottom of the aircraft, the equipment compartment 101 is located on one side of the cockpit 103, and four rotor brackets 105 are fixed to the outside of the fuselage of the aircraft. Each rotor bracket 105 is connected to an electronic speed regulator 71, a motor 7 and a rotor 72. In other embodiments, each rotor bracket 105 can be connected to two electronic speed regulators 71, two motors 7 and upper and lower rotors 72. Each electronic speed regulator 71, motor 7 and rotor 72 form a group. The electronic speed regulator 71 controls the speed of the motor 7 so that the motor 7 works at the target speed, thereby ensuring the normal rotation of the rotor 72.

[0036] The aircraft of the utility model arranges the avionics host 3, the display screen 20, the operating console 30 and the emergency parachute unit 9 in the cockpit 103, arranges the power distribution controller 2 and the flight control and navigation unit 8 in the equipment compartment 101, and arranges the power battery box 4 and the temperature manager 5 and the power manager 6 in the battery compartment 102. In this way, the different storage spaces on the aircraft are fully utilized to meet the position allocation of various parts of the avionics system. At the same time, the various parts of the avionics system are placed in appropriate positions on the aircraft, so that the role of each part can be fully exerted, and the reliability of the aircraft is further enhanced.

[0037] Although the preferred embodiments of the present invention have been described, those skilled in the art may make other changes and modifications to these embodiments once they have learned the basic creative concept. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments and all changes and modifications falling within the scope of the present invention.

[0038] Obviously, those skilled in the art can make various changes and modifications to the present invention without departing from the spirit and scope of the present invention. Thus, if these modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include these modifications and variations.

Claims

1. An avionics system for an aircraft, characterized in that: It includes multiple power battery boxes, motors, temperature managers, power managers, power distribution controllers and avionics hosts. The power battery boxes, the temperature manager and the power manager are arranged in the battery compartment of the aircraft. The power battery boxes are connected to the motors through the power manager, and the motors are connected to the rotors of the aircraft. The power battery boxes include multiple battery cells, multiple temperature detection components, heat dissipation components and fire extinguishing components. The multiple temperature detection components are used to detect the temperatures of the battery cells at different positions. The temperature manager connects the temperature detection components, the heat dissipation components, the fire extinguishing components and the power manager. The avionics host is connected to the temperature manager, the power manager and the power distribution controller. The power distribution controller is connected to the power manager. The power distribution controller is arranged in the equipment compartment of the aircraft, and the avionics host is arranged in the cockpit of the aircraft.

2. The avionics system of an aircraft according to claim 1, characterized in that: The power battery box also includes a box body, the battery cell, the temperature detection component and the fire extinguishing component are arranged in the box body, the fire extinguishing component includes a trigger component and a fire extinguishing component connected to each other, the heat dissipation component is used to dissipate heat from the battery cell, and a power supply connector and a control connector are provided on the box body, one end of the control connector is respectively connected to the temperature detection component, the trigger component and the heat dissipation component, the other end of the control connector is connected to the temperature manager, one end of the power supply connector is connected to the battery cell, and the other end is connected to the power manager.

3. The avionics system of an aircraft according to claim 2, characterized in that: The temperature manager is connected to the control connector and the avionics host through a CAN bus.

4. The avionics system of an aircraft according to claim 1, characterized in that: It also includes a flight control and navigation unit, which is connected to the power distribution controller and the motor, connected to the avionics host via a CAN bus, and is arranged in the equipment compartment.

5. The avionics system of an aircraft according to claim 4, characterized in that: The motor is connected to an electronic speed regulator, the electronic speed regulator is connected to the power manager, and the flight control and navigation unit is connected to the electronic speed regulator via a CAN bus.

6. The avionics system of an aircraft according to claim 1, characterized in that: It also includes an emergency parachute throwing unit and a lighting unit, both of which are connected to the power distribution controller, and the emergency parachute throwing unit is arranged in the cockpit.

7. The avionics system of an aircraft according to claim 1, characterized in that: The power manager includes a fuse and the power distribution controller includes a relay.

8. The avionics system of an aircraft according to claim 1, characterized in that: It also includes a display screen, which is connected to the power distribution controller and is arranged in the cockpit.

9. The avionics system of an aircraft according to claim 8, characterized in that: The avionics host is connected to the power manager, the power distribution controller and the display screen via a CAN bus respectively.

10. An aircraft, characterized in that: The invention comprises an avionics system, an equipment compartment, a battery compartment, a cockpit and a rotor of an aircraft as described in any one of claims 1 to 9, wherein an avionics host and an operating table are arranged in the cockpit, the avionics host is arranged on the operating table, a power distribution controller is arranged in the equipment compartment, a plurality of power battery boxes as well as a temperature manager and a power manager are arranged in the battery compartment, and the rotor is driven to rotate by a motor.

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