Small power distribution management machine for airborne equipment
By using a reasonable hierarchical circuit design and the SSPC solid-state power controller and non-isolated DC/DC conversion module, the problems of large size and heavy weight of existing power distribution management units have been solved. This enables multi-task power management and real-time monitoring of onboard equipment, ensuring stable operation of the equipment during voltage fluctuations.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-03-11
- Publication Date
- 2026-03-13
AI Technical Summary
Existing power distribution management units are large in size and heavy in weight, have limited functions, cannot meet the multi-task management needs of airborne equipment, cannot achieve real-time multi-task management, and lack power filtering, shaping and voltage stabilization processing, which leads to easy damage to electrical equipment and voltage fluctuation interruption problems.
A small power distribution management unit for airborne equipment was designed. It adopts a reasonable hierarchical circuit design, uses an SSPC solid-state power controller and a non-isolated DC/DC conversion module, and combines multi-channel power consumption and monitoring. It has real-time control and fault diagnosis functions, self-testing and data caching capabilities, and realizes power filtering, shaping and voltage regulation.
It achieves miniaturization and lightweight design of the power distribution management unit, has multi-task power management and real-time monitoring capabilities, can maintain stable operation of the equipment when voltage fluctuates, and has self-test and data upload functions, meeting the needs of airborne equipment for lightweight and real-time management.
Smart Images
Figure CN223993591U_ABST
Abstract
Description
Technical Field
[0001] This utility model belongs to the field of airborne equipment technology, specifically relating to a small power distribution management unit for airborne equipment. Background Technology
[0002] The power distribution management unit, as an airborne device, forms the UAV's power distribution network by connecting power supply equipment and load equipment. Its main function is to distribute power to the airborne equipment and manage the power distribution according to instructions from the host computer. However, existing power distribution management units have the following drawbacks: [Drawbacks of existing power distribution units are listed here.]
[0003] 1. Based on the traditional power distribution concept, existing power distribution machines use power wires to transmit current and voltage signals for a specified input power source. They are mostly used for single-channel wired direct connection, manual or relay control. That is, the power input for external power sources (such as ground fixed or mobile power sources, equipment built-in batteries, etc.) must correspond to the power-consuming equipment. Generally, power filtering, shaping and voltage regulation are not adopted. The structure is simple, and downstream power-consuming equipment is easily damaged by surge impacts (such as some accessories using low voltage). It is only suitable for simple power demand.
[0004] 2. In the above structure, if power filtering, shaping and voltage regulation are added, some relays (switches), single-chip controllers, power controllers and separate DC / DC modules will be added, which will increase the weight and size of the original motor and is not suitable for the lightweight requirements of airborne equipment.
[0005] 3. The existing power distribution motor has a relatively simple function. It stops distributing power when the external power supply is disconnected. It has no energy storage capacity and lacks safe and long-lasting power.
[0006] 4. It cannot meet the requirements of multi-task real-time management; it does not have the function of power-on self-test fault diagnosis. In addition, it cannot monitor the voltage / current changes in real time when the load is working. If the voltage changes, it will cause some sensitive devices such as detection radar to be interrupted.
[0007] In view of the above-mentioned problems, there is an urgent need to design a new type of power distribution management unit to meet the usage requirements of airborne equipment. Utility Model Content
[0008] The technical problem solved by this utility model is to provide a small power distribution management unit for airborne equipment. The purpose of this utility model is to make the power distribution management unit small in size and light in weight, with the characteristics of multi-channel power consumption, monitoring, feedback and real-time control, as well as the ability to combine the requirements of power consumption allocation and priority level for different tasks in flight.
[0009] To achieve the above objectives, the technical solution adopted by this utility model is as follows:
[0010] A small power distribution management unit for airborne equipment includes a power distribution management unit housing. Inside the housing 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 via the input control unit. The DC / DC power conversion module is connected to the main busbar output control unit and the key busbar output control unit. The main busbar output control unit is connected to the main busbar output interface. The key busbar output control unit is connected to the key busbar output interface. The MCU control unit is connected to the input control unit, the main busbar output control unit, and the key busbar output control unit.
[0012] Further defining the above scheme, 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] Further defining the above scheme, the main busbar output control unit includes a main busbar, and the main busbar output interfaces are a task power supply output interface A, a task power supply output interface B, and a general power supply output interface, all of which are connected to the main busbar.
[0014] Further defining the above scheme, the key busbar output control unit includes a key busbar, and the key busbar output interface includes a key power supply output interface, a rudder control 1 power supply output interface, and a rudder control 2 power supply output interface, all of which are connected to the key busbar.
[0015] Further defining the above scheme, 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 key busbar. The auxiliary power supply is connected to the MCU control board and the DC / DC power conversion module.
[0016] Further limitations of the above scheme include a download and communication interface unit, which is connected to the MCU control board.
[0017] Further limitations on the above scheme include a ground control box, which is connected to a general power output interface, a critical power output interface, a rudder control 1 power output interface, a rudder control 2 power output interface, and a critical busbar.
[0018] Advantages of this utility model compared to the prior art:
[0019] 1. The power distribution management unit of this solution is characterized by its small size, light weight, multi-channel power consumption, monitoring, feedback, and real-time control, and can be combined with the requirements of power consumption and priority level for different tasks during flight;
[0020] 2. This solution adopts a reasonable layered design, localized overall processing, reduced connection points, sealing, heat dissipation, and effective isolation of each component in the circuit design to meet the requirements of anti-interference, mechanical vibration, and shock.
[0021] 2. This solution can monitor the power grid status in real time, collect power grid electrical parameters, identify faults, and upload data; it has a data caching function, so the system status is not reset after power failure and is maintained in the state before power failure until the latest instructions are received;
[0022] 3. In this solution, due to the large output power and small size and weight requirements, a non-isolated DC / DC converter module is adopted for the voltage regulator module to improve conversion efficiency and actual use, reduce power consumption, reduce the weight and size of the whole machine; a multi-module branch output scheme is adopted to reduce the circuit loss caused by a single high-power conversion module. Attached Figure Description
[0023] Figure 1 This is the circuit schematic diagram of this utility model;
[0024] Figure 2 This is a schematic diagram of the principle of this utility model;
[0025] Figure 3 This is a circuit diagram of the input interface unit in this utility model;
[0026] Figure 4 This is a circuit diagram of the input control unit in this utility model;
[0027] Figure 5 This is a circuit diagram of the DC / DC power conversion module in this utility model;
[0028] Figure 6 This is a circuit diagram of the main busbar output control unit in this utility model. Detailed Implementation
[0029] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present utility model.
[0030] It should be noted that, in this document, the terms "comprising," "including," or any other variations thereof are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.
[0031] Please see Figure 1-6 The embodiments of this utility model are described in detail below.
[0032] Example: Small power distribution management unit for airborne equipment, see reference. Figure 1-2 As shown, the device includes a power distribution management unit housing. Inside the housing is a power distribution management circuit, which 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 via 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, and 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.
[0033] In one specific implementation: See Figure 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 one specific implementation: See Figure 6 As shown, the main busbar output control unit 4 includes a main busbar, and the main busbar output interface 5 includes 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. 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 busbar.
[0035] In this embodiment, TA1 to TA23 in the main busbar are used to feed back the input current of the lines where TA1 to TA23 are located to the PA1 MCU control board. The main busbar controller adopts the SSPC solid-state power controller. A solid-state power controller is a contactless switching component composed of semiconductor devices, integrating various protection, status indication, and reset functions into one unit. It is an intelligent switching component that combines the switching function of a relay and the circuit protection function of a circuit breaker. The new SSPC solid-state power controller replaces traditional thermal circuit breakers and relays, offering advantages such as small size, fast switching speed, no electric arc, strong anti-interference capability, high reliability, light weight, and digital control capabilities. It facilitates control by a host computer and significantly reduces the weight and volume of the original airborne power distribution management unit. Its modular design facilitates replacement and maintenance. The highly integrated current detection function (real-time monitoring of up to 30 current channels via TA1~TA30 current sensors) greatly improves the safety and reliability of the power distribution system. Each signal can be detected in real-time via a communication bus or other airborne communication protocols, and fault alarms generate status reports on the main control panel, achieving real-time status monitoring.
[0036] In one specific implementation: the critical busbar output control unit 6 includes a critical busbar, and the critical busbar output interface 7 includes a critical power supply output interface 7-1, a rudder control 1 power supply output interface 7-2, and a rudder control 2 power supply output interface 7-3. The critical power supply output interface 7-1, the rudder control 1 power supply output interface 7-2, and the rudder control 2 power supply output interface 7-3 are all connected to the critical busbar.
[0037] In one specific implementation: 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, and the battery control module, as well as to the main busbar and the key busbar. The auxiliary power supply is connected to the MCU control board and the DC / DC power conversion module 3.
[0038] In one specific implementation: it also includes a download and communication interface unit 9, which is connected to the MCU control board.
[0039] In one specific implementation: it also includes a ground control box 10, which is connected to a general power output interface 5-3, a critical power output interface 7-1, a rudder control 1 power output interface 7-2, a rudder control 2 power output interface 7-3, and a critical busbar.
[0040] In this solution, the power distribution management unit is responsible for voltage conversion, function management, and status monitoring of the required power supply. The ground power supply provides power input to the power distribution management unit, and after input filtering, power control, and power conversion, supplies power to the various loads on the aircraft to meet the needs of the aircraft during ground-based testing. The aircraft generator provides power input to the power distribution management unit while the aircraft is in the air, and after input filtering, power control, and power conversion, supplies power to the various loads on the aircraft to meet the overall power supply needs of the aircraft during flight. The emergency power supply is responsible for the overall power supply of the aircraft when the aircraft generator fails in flight. Controlled by the flight control computer, it continuously supplies power to the aircraft's emergency system to meet the power needs during aircraft recovery. Since the battery is connected in parallel to the aircraft generator's DC bus, the generator, battery, and ground power supply are connected in parallel after isolation via ideal diodes. When the aircraft generator fails or has insufficient power in flight, the emergency power supply (battery) automatically connects to the aircraft's electrical grid to supply power to the power distribution management unit.
[0041] The specific functions of this power distribution management unit are as follows:
[0042] 1. Aircraft ground power supply
[0043] a) Connect the ground power supply to the aircraft's electrical grid.
[0044] b) When the polarity of the ground power supply is reversed, it can prevent the ground power supply from being connected to the aircraft's electrical grid, thus protecting the aircraft's electrical grid.
[0045] c) When ground power is connected, it can automatically disconnect the generator and onboard battery from the aircraft's electrical grid to prevent the ground power and onboard power from being connected in parallel.
[0046] 2. Generator power generation and grid connection for power supply
[0047] a) After the engine starts successfully and the generator power supply is stable, the generator power supply is output to the aircraft electrical network via the control module. At this time, the ground power supply can be disconnected from the aircraft electrical network.
[0048] (b) During generator power supply, the system has generator protection functions such as overvoltage protection and overcurrent protection. In the event of an engine power transmission failure, the system 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, the power supply status can be restored from the emergency power supply status to the generator power supply status.
[0050] 3. Emergency power supply from storage batteries
[0051] a) When the aircraft is in a ground-based operating state and the ground power supply is not supplying power to the aircraft and the engine is not running, the onboard battery can be used to supply power to the aircraft's electrical grid.
[0052] b) In the air, when the generator power is insufficient, the onboard battery will automatically connect to the aircraft's electrical grid as an emergency power source to replenish the power.
[0053] 4. Power conversion
[0054] a) The power distribution management unit can convert the input emergency power supply into three DC voltages: 28V, 12V, and 5V, and output power to downstream critical loads.
[0055] b) Flight control computer 2, main inertial navigation system, backup inertial navigation system, signal acquisition box, brake controller, landing gear controller, fire control unit, and ground control box are directly connected to the electrical busbar wires through the power supply interface, without any control switching devices; servo controller 1, servo controller 2, L-link, and U-link are manually controlled by ground crew; the rest are controlled by commands from the flight control computer.
[0056] Because critical loads are important, the wide voltage range of lithium batteries makes it difficult to meet their power supply requirements during emergency power supply. In order to reduce mutual interference and improve conversion efficiency, an independent non-isolated DC / DC module is used to convert the battery's DC19-27.2V to a stable DC28V to meet the power requirements of critical loads.
[0057] Advantages of this machine with its own motor:
[0058] 1. Innovative design: It adopts a new design method that integrates relay switch, microcontroller and power output into one self-developed SSPC (solid-state power controller). Under the condition of greatly reducing the weight and size of the equipment, it can realize multi-task power management by reading programmable control instructions.
[0059] 2. The new airborne motor has a built-in self-powered energy storage module with a minimum voltage of 5V, which can ensure that the equipment can still maintain its safe power supply and continue to operate for about 0.5 hours when the external power supply is suddenly interrupted.
[0060] 3. The new airborne motor features a self-charging surge protection design at the battery input end. For a 28V battery charging input, it has a built-in anti-buffer design with a maximum voltage of 7V. The output end uses a voltage-regulating DC / DC module to output different voltages such as 28V, 14V, and 5V, which avoids surges and meets the needs of different electrical equipment.
[0061] 4. The new airborne generator and the airborne host computer (airborne computer) establish a communication protocol. Real-time task control can be transmitted to the host computer in advance according to the actual flight mission situation. It can perform different mission requirements and has strong scalability.
[0062] 5. It has the ability to perform power-on self-test and simulation function tests before use. The key power lines in the design are equipped with high-performance current sensors, which can monitor the power consumption of the load in real time and control the power supply demand through SSPS to ensure the execution rate of the task.
[0063] It will be apparent to those skilled in the art that this invention is not limited to the details of the exemplary embodiments described above, and that it can be implemented in other specific forms without departing from the spirit or essential characteristics of this invention. Therefore, the embodiments should be considered illustrative and non-limiting in all respects, and the scope of this invention is defined by the appended claims rather than the foregoing description. Thus, it is intended that all variations falling within the meaning and scope of equivalents of the claims be included within this invention. No reference numerals in the claims should be construed as limiting the scope of the claims.
[0064] Furthermore, it should be understood that although this specification describes embodiments, not every embodiment contains only one independent technical solution. This narrative style is merely for clarity. Those skilled in the art should consider 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 small power distribution management machine for an airborne equipment, characterized by: The power distribution management machine shell is internally provided with a power distribution management circuit, which comprises 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 key busbar output control unit (6), a key busbar output interface (7) and an MCU control unit (8); The input interface unit (1) is connected with the DC / DC power conversion module (3) through the input control unit (2), the DC / DC power conversion module (3) is connected with the main busbar output control unit (4) and the key busbar output control unit (6), the main busbar output control unit (4) is connected with the main busbar output interface (5), the key busbar output control unit (6) is connected with the key busbar output interface (7), and the MCU control unit (8) is connected with the input control unit (2), the main busbar output control unit (4) and the key busbar output control unit (6).
2. The small power distribution management device for an onboard device according to claim 1, characterized by: The input interface unit (1) comprises a direct-current 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) comprises a generator control module, a ground power control module and a battery control module, the direct-current generator input interface (1-1), the ground power input interface (1-2) and the airborne battery input interface (1-3) are connected with the generator control module, the ground power control module and the battery control module respectively, and the generator control module, the ground power control module and the battery control module are connected with the DC / DC power conversion module (3).
3. The small power distribution management device for an onboard device according to claim 2, characterized by: The main busbar output control unit (4) comprises a main busbar, and the main busbar 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), wherein 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 connected with the main busbar.
4. The small power distribution management device for an onboard apparatus according to claim 3, characterized by: The key busbar output control unit (6) comprises a key busbar, and the key busbar output interface (7) comprises a key power supply output interface (7-1), a rudder control 1 power supply output interface (7-2) and a rudder control 2 power supply output interface (7-3), wherein the key power supply output interface (7-1), the rudder control 1 power supply output interface (7-2) and the rudder control 2 power supply output interface (7-3) are connected with the key busbar.
5. The small power distribution management machine for an onboard device according to claim 4, characterized by: The MCU control unit (8) comprises an MCU control board and an auxiliary power supply, the MCU control board is connected with the generator control module, the ground power control module, the battery control module, the main busbar and the key busbar, and the auxiliary power supply is connected with the MCU control board and the DC / DC power conversion module (3).
6. The small power distribution management machine for an onboard device according to claim 5, characterized by: A download and communication interface unit (9) is further comprised, and the download and communication interface unit (9) is connected with the MCU control board.
7. The small power distribution management machine for an onboard device according to claim 5, characterized by: Also included is a ground check control box (10) that interfaces with the general power output interface (5-3), the critical power output interface (7-1), the rudder control 1 power output interface (7-2), the rudder control 2 power output interface (7-3), and the critical bus bar connection.