Power distribution management machine for airborne equipment

Abstract

The invention provides a power distribution management machine for airborne equipment, and belongs to the technical field of airborne equipment. The power distribution management circuit comprises an input interface unit, an input control unit, a DC / DC power conversion module, a main bus bar output control unit, a key bus bar output control unit and an MCU control unit. The input interface unit is connected with the DC / DC charging module through the input control unit, the DC / DC power supply conversion module is connected with the main bus bar output control unit and the key bus bar output control unit, the main bus bar output control unit is connected with the main bus bar output interface, the key bus bar output control unit is connected with the key bus bar output interface, and the main bus bar output interface is connected with the key bus bar output interface. The MCU control unit is connected with the input control unit, the main bus bar output control unit and the key bus bar output control unit. The system is small in size and light in weight, has the characteristics of multi-channel power utilization, monitoring, feedback and real-time control, and meets the requirements of power consumption distribution, priority level and the like for different tasks in combination with flight.

Description

Technical Field

[0001] The present invention belongs to the technical field of airborne equipment, and in particular relates to a power distribution management machine for airborne equipment. Background Art

[0002] As an airborne device, the power distribution management machine forms the power distribution network of the drone by cross-linking the power supply equipment and the load equipment. Its main function is to distribute power to the airborne equipment and implement the power distribution management of the airborne equipment according to the instructions of the host computer. However, the existing power distribution management machine has the following defects:

[0003] 1. Based on the traditional power distribution concept, the existing power distribution machine uses power wires to transmit current and voltage signals for the specified input power supply, and is mostly used for single-channel wired direct, manual or relay control. That is, the power supply for the external power supply (such as ground fixed or mobile power supply, equipment with built-in battery, etc.) must correspond to the power-consuming equipment. Generally, power filtering, shaping and voltage-stabilized output processing are not adopted. The structure is simple, and the downstream power-consuming equipment is prone to damage and breakdown due to surge impact (such as some accessories with lower voltage), and is only suitable for power demand in simple forms;

[0004] 2. In the above structure, if power filtering, shaping and voltage stabilization output processing are added, some relays (switches), single-chip controllers, power controllers and separate DC / DC modules will be added, which will increase the weight and volume of the original motor and is not suitable for the lightness requirements of airborne equipment;

[0005] 3. The existing power distribution machine has a single function. When the external power supply is disconnected, the power distribution stops. It has no energy storage capacity and lacks safe endurance.

[0006] 4. It cannot meet the requirements of multi-task real-time management; it does not have the function of self-checking and fault diagnosis when powered on. In addition, it cannot monitor the voltage / current changes in real time when the load is working. If the voltage changes, it will cause work interruption to some sensitive devices such as detection radar.

[0007] In view of the above-mentioned problems, it is urgent to design a new type of power distribution management machine to meet the use requirements of airborne equipment. Summary of the invention

[0008] The technical problem solved by the present invention is to provide a power distribution management machine for airborne equipment. The purpose of the present invention is to make the power distribution management machine small in size and light in weight, with the characteristics of multi-channel power consumption and monitoring, feedback, and real-time control, as well as the ability to allocate power consumption, priority levels, etc. to different tasks during flight.

[0009] In order to achieve the above object, the technical solution adopted by the present invention is:

[0010] A power distribution management machine for airborne equipment, including a housing of the power distribution management machine. Inside the housing of the power distribution management machine, there is a power distribution management circuit, which includes an input interface unit, an input control unit, a DC / DC power conversion module, a main busbar output control unit, a main busbar output interface, a critical busbar output control unit, a critical busbar output interface, and an MCU control unit;

[0011] The input interface unit is connected to the DC / DC charging module through the input control unit. The DC / DC power conversion module is connected to the main busbar output control unit and the critical busbar output control unit. The main busbar output control unit is connected to the main busbar output interface. The critical busbar output control unit is connected to the critical busbar output interface. The MCU control unit is connected to the input control unit, the main busbar output control unit, and the critical busbar output control unit. An SSPC solid-state power controller is adopted in the main busbar output control unit.

[0012] For further limitation of the above solution, the input interface unit includes a DC generator input interface, a ground power input interface, and an airborne battery input interface. The input control unit includes a generator control module, a ground power control module, and a battery control module. The DC generator input interface, the ground power input interface, and the airborne battery input interface are respectively connected to the generator control module, the ground power control module, and the battery control module. The generator control module, the ground power control module, and the battery control module are connected to the DC / DC power conversion module.

[0013] For further limitation of the above solution, the main busbar output control unit includes a main busbar. The main busbar output interface includes an A mission power supply output interface, a B mission power supply output interface, and a general power supply output interface. The A mission power supply output interface, the B mission power supply output interface, and the general power supply output interface are all connected to the main busbar.

[0014] For further limitation of the above solution, the critical busbar output control unit includes a critical busbar. The critical busbar output interface includes a critical power supply output interface, a rudder control 1 power supply output interface, and a rudder control 2 power supply output interface. The critical power supply output interface, the rudder control 1 power supply output interface, and the rudder control 2 power supply output interface are all connected to the critical busbar.

[0015] For further limitation of the above solution, the MCU control unit includes an MCU control board and an auxiliary power supply. The MCU control board is connected to the generator control module, the ground power control module, and the battery control module, as well as to the main busbar and the critical busbar. The auxiliary power supply is connected to the MCU control board and the DC / DC power conversion module.

[0016] Further limitation of the above solution also includes a download and communication interface unit, which is connected to the MCU control board.

[0017] Further limitation of the above solution also includes a ground inspection control box, which is connected to a general power supply output interface, a key power supply output interface, a rudder control 1 power supply output interface, a rudder control 2 power supply output interface, and a key busbar.

[0018] Advantages of the present invention compared with the prior art:

[0019] 1. The power distribution management machine of this solution has the characteristics of small volume, light weight, multi-channel power consumption, monitoring, feedback, and real-time control, and can meet the requirements of allocating power consumption and priority levels for different tasks during flight.

[0020] 2. In the circuit design of this solution, a method of reasonable hierarchical matching, local and overall processing, reducing connection points, sealing, facilitating heat dissipation, and effectively isolating each device is adopted to meet the requirements of anti-interference, mechanical vibration, and impact.

[0021] 2. This solution can monitor the power grid status in real time, collect power grid electrical parameters, fault identification, and data upload; it has a data caching function, and after power failure recovery, the system status does not reset, maintaining the state before power failure until receiving the latest instruction.

[0022] 3. In this solution, due to the large output power and small size and weight requirements, in order to improve the conversion efficiency and actual use situation, the voltage stabilization module adopts a non-isolated DC / DC conversion module to reduce power consumption, reduce the weight of the whole machine and the volume of the whole machine; a multi-module shunt output scheme is adopted to reduce the circuit loss caused by a single high-power conversion module. Description of the Drawings

[0023] Figure 1 is the circuit schematic diagram of the present invention;

[0024] Figure 2 is the principle block diagram of the present invention;

[0025] Figure 3 is the circuit diagram of the input interface unit in the present invention;

[0026] Figure 4 is the circuit diagram of the input control unit in the present invention;

[0027] Figure 5 is the circuit diagram of the DC / DC power conversion module in the present invention;

[0028] Figure 6 is the circuit diagram of the main busbar output control unit in the present invention. Detailed Embodiments

[0029] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0030] It should be noted that in this article, the terms "include", "comprise" or any other variant thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements not only includes those elements but also includes other elements not expressly listed, or further includes elements inherent to such process, method, article or device. Without further limitation, an element defined by the phrase "including one..." does not exclude the existence of additional identical elements in the process, method, article or device including the said element.

[0031] Please refer to Figures 1-6 , and detail the embodiments of the present invention.

[0032] Embodiment: A power distribution management machine for airborne equipment, refer to Figures 1-2 as shown, including a power distribution management machine housing, a power distribution management circuit is provided inside the power distribution management machine housing, and the power distribution management circuit includes an input interface unit 1, an input control unit 2, a DC / DC power conversion module 3, a main busbar output control unit 4, a main busbar output interface 5, a critical busbar output control unit 6, a critical busbar output interface 7, and an MCU control unit 8; the input interface unit 1 is connected to the DC / DC power conversion module 3 through the input control unit 2, the DC / DC power conversion module 3 is connected to the main busbar output control unit 4 and the critical busbar output control unit 6, the main busbar output control unit 4 is connected to the main busbar output interface 5, the critical busbar output control unit 6 is connected to the critical busbar output interface 7, the MCU control unit 8 is connected to the input control unit 2, the main busbar output control unit 4, and the critical busbar output control unit 6, and an SSPC solid-state power controller is adopted in the main busbar output control unit 4.

[0033] In a specific embodiment: Refer to Figures 3-5As shown, the input interface unit 1 includes a DC generator input interface 1-1, a ground power input interface 1-2, and an airborne battery input interface 1-3. The input control unit 2 includes a generator control module, a ground power control module, and a battery control module. The DC generator input interface 1-1, the ground power input interface 1-2, and the airborne battery input interface 1-3 are respectively connected to the generator control module, the ground power control module, and the battery control module. The generator control module, the ground power control module, and the battery control module are connected to the DC / DC power conversion module 3.

[0034] In a specific embodiment: Refer to Figure 6 As shown, the main busbar output control unit 4 includes a main busbar. The main busbar output interface 5 includes a mission A power supply output interface 5-1, a mission B power supply output interface 5-2, and a general power supply output interface 5-3. The mission A power supply output interface 5-1, the mission B power supply output interface 5-2, and the general power supply output interface 5-3 are all connected to the main busbar.

[0035] In this embodiment, TA1 to TA23 in the main busbar are used to feedback the input current of the lines where TA1 to TA23 are located to the PA1 MCU control board. The controller of the main busbar adopts an SSPC solid-state power controller. The solid-state power controller is a non-contact switch component composed of semiconductor devices that combines various protection, status indication, and reset functions, and has the ability to control power on and off. It is an intelligent switch component that integrates the switching function of a relay and the circuit protection function of a circuit breaker. The traditional thermal circuit breaker and relay are replaced by the new SSPC solid-state power controller, which has the advantages of small size, fast switching speed, no arc, strong anti-interference ability, high reliability, light weight, and can realize digital control, facilitating the control of the upper computer, and greatly saving the weight and volume of the original airborne power distribution management machine. It is modular and easy to replace and maintain, with a high-integration current detection function (real-time monitoring of up to 30 channels of current through TA1 to TA30 current sensors), and greatly improves the safety and reliability of the power distribution system. Each signal can realize real-time detection and fault alarm through the communication bus or other airborne communication protocols to form a status report on the master control panel, realizing real-time status monitoring.

[0036] In a specific embodiment: The critical busbar output control unit 6 includes a critical busbar. The critical busbar output interface 7 includes a critical power supply output interface 7-1, a steering control 1 power supply output interface 7-2, and a steering control 2 power supply output interface 7-3. The critical power supply output interface 7-1, the steering control 1 power supply output interface 7-2, and the steering control 2 power supply output interface 7-3 are all connected to the critical busbar.

[0037] In a specific embodiment: the MCU control unit 8 includes an MCU control board and an auxiliary power supply. The MCU control board is connected to the generator control module, the ground power control module, the battery control module, and the main bus bar and the critical bus bar. The auxiliary power supply is connected to the MCU control board and the DC / DC power conversion module 3.

[0038] In a specific embodiment: it further includes a download and communication interface unit 9, and the download and communication interface unit 9 is connected to the MCU control board.

[0039] In a specific embodiment: it further includes a ground inspection control box 10, and the ground inspection control box 10 is connected to the general power supply output interface 5-3, the critical power supply output interface 7-1, the steering control 1 power supply output interface 7-2, the steering control 2 power supply output interface 7-3, and the critical bus bar.

[0040] In this solution, the power distribution management machine is responsible for voltage conversion, function management, status monitoring, etc. of the required power supply. The ground power supply is responsible for providing power input to the power distribution management machine, and after input filtering, power control, and power conversion, it provides power to each load of the aircraft to meet the use during the overall aircraft test on the ground. The aircraft generator is responsible for providing power input to the power distribution management machine when the aircraft is in the air, and after input filtering, power control, and power conversion, it provides power to each load of the aircraft to meet the overall power supply during the flight of the aircraft. The emergency power supply is responsible for the overall power supply of the aircraft when the aircraft generator fails during flight. It is controlled by the flight control computer instruction and continuously supplies power to the aircraft emergency system to meet the power consumption during aircraft recovery; since the battery is connected in parallel to the DC bus bar of the aircraft generator, the generator, the battery, and the ground power supply are connected in parallel together after being isolated by an ideal diode. When the aircraft generator fails or has insufficient power in the air, the emergency power supply (battery) automatically connects to the aircraft power grid to supply power to the power distribution management machine.

[0041] Specifically, the functions of this power distribution management machine are as follows:

[0042] 1. Aircraft ground power supply

[0043] a) Connect the ground power supply to the aircraft power grid.

[0044] b) When the polarity of the ground power supply is reversed, it can prevent the ground power supply from accessing the aircraft power grid and protect the on-board power grid.

[0045] c) When the ground power supply is turned on, it can automatically disconnect the connection between the generator and the on-board battery and the aircraft power grid to prevent the ground power supply from being supplied in parallel with the on-board power supply.

[0046] 2. Generator power generation and grid-connected power supply

[0047] a) After the engine starts successfully and the power supply of the generator is stable during the power supply operation, the power supply of the generator is output through the control module and connected to the aircraft power grid. At this time, the ground power supply can be cut off from the aircraft power grid.

[0048] b) During the power supply of the generator, the system has generator protection functions such as overvoltage protection and overcurrent protection. When a fault occurs in the engine power supply, it can report the fault status to the flight control computer and seamlessly connect the emergency power supply.

[0049] c) When the generator resumes normal power supply, it can be restored from the emergency power supply state to the generator power supply state.

[0050] 3. Emergency power supply of the battery

[0051] a) In the ground working state, when the ground power supply does not supply power to the aircraft and the engine is not working, the on-board battery can be used to supply power to the aircraft power grid.

[0052] b) In the air, when the power of the generator is insufficient, the on-board battery is automatically connected to the aircraft power grid as an emergency power supply for supplementary power supply.

[0053] 4. Power conversion

[0054] a) The power distribution management machine can convert the input emergency power supply into three DC voltages of 28V, 12V, 5V, etc., and output power supply to the subsequent key loads.

[0055] b) The flight control computer 2, the main inertial navigation, the standby inertial navigation, the signal acquisition box, the brake controller, the landing gear controller, the fire control machine, and the ground inspection control box are directly connected to the electrical busbar wires through the power supply interface without any control switch devices; the servo controller 1, the servo controller 2, the L link, and the U link are manually controlled by the ground crew for output; the rest are controlled by the flight control computer instructions for output.

[0056] Since the key loads are relatively important, when powered by the emergency power supply, due to the relatively wide voltage range of the lithium battery, it is difficult to meet the power supply requirements of the key loads. At the same time, to reduce the mutual influence and improve the conversion efficiency, an independent non-isolated DC / DC module conversion output is adopted. The battery DC19 - 27.2V is converted to a stable DC28V through DC / DC to meet the power consumption requirements of the key loads.

[0057] Advantages of the on-board power distribution machine of this aircraft:

[0058] 1. Innovative design, adopting a new design method that integrates the self-developed SSPC (Solid State Power Controller) with a relay switch, a single-chip microcomputer, and power output. Under the condition of greatly reducing the weight and volume of the equipment, multi-task power management can be achieved by reading programmable control instructions;

[0059] 2. The new airborne power distribution unit is built with a self-powered energy storage module with a minimum voltage of 5V, which can ensure that when the external power supply suddenly cuts off, the equipment can still retain the power supply for safe operation, such as emergency signal transmission, warning lights and other equipment can work for about 0.5 hours;

[0060] 3. The new airborne power distribution unit is designed with a self-charging surge protection at the battery input end. That is, for the charging input of a 28V battery, it has a built-in anti-buffer design with a maximum of 7V. The output end uses a voltage-stabilized DC / DC module to output different voltages such as 28V, 14V, and 5V, which can avoid impact surges and meet the needs of different electrical equipment;

[0061] 4. The new airborne power distribution unit establishes a connection with the airborne host computer (airborne computer) through a communication protocol. In advance, according to the actual situation of the flight mission, real-time task control can be transmitted through the host computer, and it can execute different task requirements, with strong scalability;

[0062] 5. It has power-on self-check and simulation function tests before use. In the design, high-performance current sensors are designed for key power lines, which can monitor the power consumption of the load in real time and control the stable power supply demand through SSPS to ensure the execution rate of the task.

[0063] For those skilled in the art, it is obvious that the present invention is not limited to the details of the above exemplary embodiments, and without departing from the spirit or basic characteristics of the present invention, the present invention can be implemented in other specific forms. Therefore, in any regard, the embodiments should be regarded as exemplary and non-limiting. The scope of the present invention is defined by the appended claims rather than the above description. Therefore, all changes falling within the meaning and scope of the equivalent elements of the claims are intended to be included in the present invention. Any reference signs in the claims should not be regarded as limiting the claims involved.

[0064] In addition, it should be understood that although this specification is described according to embodiments, not every embodiment only contains an independent technical solution. This narrative way of the specification is only for clarity. Those skilled in the art should regard the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. A power distribution management machine for airborne equipment, characterized in that: It comprises a power distribution management machine housing, wherein a power distribution management circuit is arranged inside the power distribution management machine housing, and the power distribution management circuit comprises an input interface unit (1), an input control unit (2), a DC / DC power conversion module (3), a main bus output control unit (4), a main bus output interface (5), a key bus output control unit (6), a key bus output interface (7) and an MCU control unit (8); The input interface unit (1) is connected to a DC / DC power conversion module (3) via an input control unit (2); the DC / DC power conversion module (3) is connected to a main bus output control unit (4) and a key bus output control unit (6); the main bus output control unit (4) is connected to a main bus output interface (5); the key bus output control unit (6) is connected to a key bus output interface (7); the MCU control unit (8) is connected to the input control unit (2), the main bus output control unit (4), and the key bus output control unit (6); an SSPC solid-state power controller is used in the main bus output control unit (4).

2. A power distribution management machine for airborne equipment according to claim 1, characterized in that: The input interface unit (1) comprises a DC generator input interface (1-1), a ground power input interface (1-2) and an onboard battery input interface (1-3); the input control unit (2) comprises a generator control module, a ground power control module and a battery control module; the DC generator input interface (1-1), the ground power input interface (1-2) and the onboard battery input interface (1-3) are respectively connected to the generator control module, the ground power control module and the battery control module; the generator control module, the ground power control module and the battery control module are connected to the DC / DC power conversion module (3).

3. A power distribution management machine for airborne equipment according to claim 2, characterized in that: The main bus output control unit (4) comprises a main bus, and the main bus output interface (5) comprises an A task power supply output interface (5-1), a B task power supply output interface (5-2) and a general power supply output interface (5-3), and the A task power supply output interface (5-1), the B task power supply output interface (5-2) and the general power supply output interface (5-3) are all connected to the main bus.

4. A power distribution management machine for airborne equipment according to claim 3, characterized in that: The key bus output control unit (6) comprises a key bus, the key bus output interface (7) comprises a key power supply output interface (7-1), a steering control 1 power supply output interface (7-2) and a steering control 2 power supply output interface (7-3), and the key power supply output interface (7-1), the steering control 1 power supply output interface (7-2) and the steering control 2 power supply output interface (7-3) are all connected to the key bus.

5. A power distribution management machine for airborne equipment according to claim 4, characterized in that: The MCU control unit (8) comprises an MCU control board and an auxiliary power supply. The MCU control board is connected to a generator control module, a ground power control module and a battery control module as well as a main bus bar and a key bus bar. The auxiliary power supply is connected to the MCU control board and a DC / DC power conversion module (3).

6. A power distribution management machine for airborne equipment according to claim 5, characterized in that: It also comprises a download and communication interface unit (9), wherein the download and communication interface unit (9) is connected to the MCU control board.

7. The power distribution management machine for airborne equipment according to claim 5, characterized in that: It also includes a ground inspection control box (10), which is connected to a general power supply output interface (5-3), a key power supply output interface (7-1), a steering control 1 power supply output interface (7-2), a steering control 2 power supply output interface (7-3), and a key bus bar.

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