Integrated control method for aircraft power supply system
By integrating the engine controller to monitor and protect the transformer rectifier and battery status, the problem of waste of controller functions in the aircraft power supply system is solved, and equipment reduction and economic improvement are achieved.
Patent Information
- Application Number
- CN202510590586.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-05-08
- Publication Date
- 2025-07-25
AI Technical Summary
In the existing aircraft power system, the functions and computing power of each controller are large, resulting in waste of performance and increasing the weight of onboard equipment and maintenance costs.
Directly electrically connect the engine controller to the generator output contactor, variable-regular output contactor, and battery output contactor. The engine controller monitors the status of the transformer rectifier and battery in real time, performs output control and fault protection, and replaces the original DC protection controller and battery controller functions.
It reduces the types and quantity of airborne equipment, reduces the equipment weight and installation space requirements, and improves the economics of the development and maintenance stages.
Smart Images
Figure CN120377406A_ABST
Abstract
Description
Technical Field
[0001] This application belongs to the field of aircraft power system design, and particularly relates to an integrated control method for an aircraft power system. Background Art
[0002] Among military and civilian aircraft, the AC main power supply is the most widely used main power supply system. At this time, the aircraft power supply system usually includes the following types of power supplies: 1) 115V AC main power supply, which uses a generator to convert mechanical energy into electrical energy to supply power to high-power aircraft electrical equipment. 2) 28V DC secondary power supply, which uses a transformer-rectifier to convert the 115V AC power supply into a 28V low-voltage DC power supply to supply power to electronic devices such as computers and instruments. 3) 28V DC emergency power supply, which uses a battery as an emergency power supply to supply power to critical electrical equipment that affects flight safety when the 28V DC normal power supply fails. In the design of previous aircraft power supply systems, the controllers of different power supplies were usually set independently to complete functions such as control of each subsystem, status monitoring, fault protection, and data reporting.
[0003] According to the working characteristics of the aircraft power supply system, each controller only needs to control the on / off of the contactor during the initial power-on of the system and perform power-on self-checks on each component. During the steady-state operation of the system, for the vast majority of the time after the generator in the main power supply starts to work, each controller is only used for status monitoring and reporting of the subsystem where it is located. At this time, the functions and computing power margins of each controller are very large, resulting in performance waste. In addition, the dedicated controllers separately set for different subsystems also increase the weight and volume requirements of aircraft on-board equipment, leading to increased research and development costs as well as later use and maintenance costs.
[0004] Therefore, how to optimize the types and quantities of controllers and achieve integrated control is a problem that needs to be solved. Summary of the Invention
[0005] The purpose of this application is to provide an integrated control method for an aircraft power system to solve the problem of large function and computing power margins of existing controllers, resulting in performance waste.
[0006] The technical solution of this application is: an integrated control method for an aircraft power system, including: directly electrically connecting the engine controller to the generator output contactor, the variable rectifier output contactor, the battery output contactor, the transformer-rectifier, and the battery; the engine controller receives the temperature signal, output voltage signal, and output current signal of the transformer-rectifier in real time, judges the working state of the transformer-rectifier, and performs output control and fault protection on the transformer-rectifier according to the working state of the transformer-rectifier.
[0007] The generator controller receives the temperature signal, voltage signal and current signal of the battery in real time, judges the working state of the battery, and performs output control and fault protection on the battery according to the working state of the battery.
[0008] Preferably, a rectification control unit is arranged in the engine controller, and a line protection module, a power management module and a health monitoring module are arranged in the rectification control unit; the line protection module is used for overcurrent protection and short-circuit protection of the voltage rectifier, the power management module is used for priority power supply control of the voltage rectifier, and the health monitoring module is used for health management of the voltage rectifier.
[0009] Preferably, an overcurrent detection circuit and a short-circuit protection circuit are arranged in the line protection module. The overcurrent detection circuit includes a Hall effect sensor and a relay. When the output current signal exceeds the limit, the Hall effect sensor detects the circuit and triggers the relay to disconnect; the short-circuit protection circuit includes an IGBT circuit, which disconnects when the IGBT circuit detects a short circuit.
[0010] Preferably, different connected loads are respectively marked in the power management module, and then the different loads are sorted according to priority. When the power supply in the aircraft is insufficient, power-off is performed in turn in the order from low to high priority.
[0011] Preferably, the health monitoring module collects the temperature signal, output voltage signal and output current signal of the voltage rectifier in real time and sends them to the flight control system. The aircraft system obtains the temperature signal, output voltage signal and output current signal in the latest period of time, obtains the maximum values of the temperature signal, output voltage signal and output current signal for matching with the health management algorithm, selects the most suitable algorithm to calculate the aging degree of the current voltage rectifier, and outputs and saves the calculation result; after predicting that the aging degree of the voltage rectifier is greater than a certain value, an output alarm is given.
[0012] Preferably, a line protection module, a temperature compensation module and a priority control module are arranged in the generator controller. Temperature protection thresholds, overvoltage protection thresholds and overcurrent protection thresholds are respectively arranged in the line protection module; the obtained temperature signal, output voltage signal and output current signal are respectively compared with the temperature protection threshold, overvoltage protection threshold and overcurrent protection threshold. After judging that any one of the temperature, pressure and temperature exceeds the corresponding threshold, the battery output contactor is controlled to disconnect; the temperature compensation module is used for temperature compensation of the battery when the battery temperature is detected to be too high; the priority control module is used for controlling the battery to disconnect some loads through the flight control system when the aircraft electrical energy is insufficient.
[0013] Preferably, a temperature-voltage control table is provided in the temperature compensation module. Different charging parameters are respectively set in the temperature-voltage control table corresponding to different temperatures. After obtaining the current temperature signal of the storage battery, the corresponding charging parameters are found through the temperature-voltage control table, and then the voltage of the storage battery is controlled by the charging parameters.
[0014] The integrated control method of the aircraft power supply system of the present application has the following advantages:
[0015] 1. Reduce the types and quantities of airborne equipment. Merge three different types of controllers, namely the generator controller, the DC control protector, and the storage battery controller, into one, improving the economy in the research and development stage, as well as in the field use and maintenance stage.
[0016] 2. Reduce the requirement for layout and installation space. The number of controllers is significantly reduced, reducing the equipment weight and significantly saving the precious installation space on the aircraft.
[0017] 3. Reduce the interface requirements for other systems such as the remote interface unit and data recording on the aircraft, and at the same time save the corresponding wires, further reducing the system weight and improving the economy.
[0018] 4. This solution is easy to implement. Except that the generator controller has a separate voltage regulation function, since the functions of the three controllers are highly similar, it only needs to adaptively increase the interface of the generator controller to achieve, and only minor improvements to the software and hardware of the generator controller are required. Description of the Drawings
[0019] In order to more clearly illustrate the technical solutions provided by the present application, the drawings will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application.
[0020] Figure 1 is the control architecture diagram of the conventional power supply system;
[0021] Figure 2 is the control architecture diagram of the power supply system of the present application. Detailed Embodiments
[0022] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the 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 of 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.
[0023] Such as Figure 1, in a conventional 115V AC power supply subsystem, the generator control unit (GCU) mainly has functions such as voltage regulation, control, protection, communication, and status monitoring. During the operation of the AC power supply subsystem, it feedback-regulates the output voltage of the generator, simultaneously controls the on / off of the generator output contactor (GC) according to commands and the system operating status, performs fault protection when the system malfunctions, and reports the system status to the remote interface unit via a bus and accepts self-test and other commands.
[0024] In a conventional 28V DC power supply subsystem, the DC power control and protection device mainly has functions such as control, protection, communication, and status monitoring. During the operation of the subsystem, it monitors status information such as the output voltage, current, and temperature of the transformer-rectifier, controls the transformer-rectifier output contactor, performs fault protection and isolation when the input or output power quality of the transformer-rectifier does not meet requirements or the transformer-rectifier malfunctions, and reports the 28V DC power supply system status to the remote interface unit via a bus and accepts self-test and other commands.
[0025] In a conventional aircraft power supply system, the battery controller mainly has functions such as control, protection, communication, and status monitoring. During the operation of the system, it measures status information such as the battery output voltage, current, and internal temperature of the battery, controls the battery output contactor, disconnects when the battery voltage or output current does not meet quality requirements, and reports the system status to the remote interface unit via a bus and accepts self-test and other commands.
[0026] Under normal circumstances of the aircraft power supply system, the generator output contactor, transformer-rectifier output contactor, and battery output contactor are all in the closed position. The main common functions of the three types of controllers, namely the generator controller, DC control and protection device, and battery controller, are equipment status monitoring, periodic detection, and system protection. Their working contents are similar and the working timing is basically the same. The functional requirements for the controllers are similar, and the performance requirements are not high.
[0027] Based on the above problems, this application designs an integrated control method for an aircraft power supply system, including the following steps:
[0028] Step S100, as Figure 2 , directly electrically connect the engine controller to the generator output contactor, transformer-rectifier output contactor, battery output contactor, transformer-rectifier, and battery; the engine controller receives the temperature signal, output voltage signal, and output current signal of the transformer-rectifier in real time, judges the working state of the transformer-rectifier, and performs output control and fault protection on the transformer-rectifier according to the working state of the transformer-rectifier to completely replace the functions of the original DC protection controller.
[0029] The generator controller is connected to the flight control system through the remote interface unit.
[0030] Preferably, a plurality of hardware acquisition and output interfaces are provided on the engine controller and electrically connected to the variable rectifier output contactor, the battery output contactor, the transformer rectifier, and the battery.
[0031] Meanwhile, an additional functional unit is provided on the engine controller to manage and control the transformer rectifier. Specifically, a variable rectification control unit is provided in the engine controller, and a line protection module, a power management module, and a health monitoring module are provided in the variable rectification control unit. The line protection module is used to perform overcurrent protection and short-circuit protection on the transformer rectifier. The power management module is used to perform priority power supply control on the transformer rectifier. The health monitoring module is used to perform health management on the transformer rectifier.
[0032] An overcurrent detection circuit and a short-circuit protection circuit are provided in the line protection module. The overcurrent detection circuit includes a Hall effect sensor and a relay. When the output current signal exceeds the limit, the Hall effect sensor detects the circuit and triggers the relay to disconnect. The short-circuit protection circuit includes an IGBT circuit, which disconnects when a short circuit is detected by the IGBT circuit.
[0033] Preferably, different loads connected to the power management module are respectively marked, and then the different loads are sorted according to priority. When the power supply in the aircraft is insufficient, power is cut off in turn in the order from low to high priority to meet the power supply requirements of the loads with higher priority. The priorities from low to high are the entertainment system, the life system, the lighting system, the communication and navigation equipment, and the flight control system, etc.
[0034] Preferably, the health monitoring module continuously collects the temperature signal, output voltage signal, and output current signal of the transformer rectifier and sends them to the flight control system. The aircraft system obtains the temperature signal, output voltage signal, and output current signal in the most recent period of time, obtains the maximum values of the temperature signal, output voltage signal, and output current signal, matches them with the health management algorithm, selects the most suitable algorithm to calculate the aging degree of the current transformer rectifier, and outputs and saves the calculation result. After predicting that the aging degree of the transformer rectifier is greater than a certain value, an output alarm is given.
[0035] Step S200, the generator controller continuously receives the temperature signal, voltage signal, and current signal of the battery, and judges the working state of the battery, and performs output control and fault protection on the battery according to the working state of the battery to completely replace the functions of the original battery.
[0036] Preferably, a line protection module, a temperature compensation module, and a priority control module are provided in the generator controller. Temperature protection thresholds, overvoltage protection thresholds, and overcurrent protection thresholds are respectively set in the line protection module. The acquired temperature signal, output voltage signal, and output current signal are respectively compared with the temperature protection threshold, overvoltage protection threshold, and overcurrent protection threshold. After it is determined that any one of the temperature, voltage, and current exceeds the corresponding threshold, the battery output contactor is controlled to disconnect. The temperature compensation module is used to perform temperature compensation on the battery when the battery temperature is detected to be too high. The priority control module is used to control the battery to disconnect some loads through the flight control system when the aircraft electrical energy is insufficient. The priority order of the priority control module is the same as the control method of the power management module, and will not be elaborated here.
[0037] Preferably, a temperature-voltage control table is provided in the temperature compensation module. Different charging parameters are respectively set in the temperature-voltage control table corresponding to different temperatures. After acquiring the current temperature signal of the battery, the corresponding charging parameters are found through the temperature-voltage control table, so as to control the voltage of the battery through the charging parameters to prevent thermal runaway.
[0038] Through the above design, the advantages of this application are as follows:
[0039] 1. Reduce the types and quantities of airborne equipment. Combine three different types of controllers, namely the generator controller, the DC control protector, and the battery controller, into one, improving the economy in the research and development stage, as well as in the field use and maintenance stage.
[0040] 2. Reduce the requirement for layout and installation space. The number of controllers is significantly reduced, reducing the equipment weight and significantly saving the precious installation space on the aircraft.
[0041] 3. Reduce the interface requirements for other systems such as the remote interface unit and data recording on the aircraft, and at the same time save the corresponding wires, further reducing the system weight and improving the economy.
[0042] 4. This solution is easy to implement. Except that the generator controller has a separate voltage regulation function, since the functions of the three controllers are highly similar, it only needs to adaptively increase the interfaces of the generator controller to achieve, and only needs to make minor improvements to the software and hardware of the generator controller.
[0043] Finally, it should be noted that: in the drawings of the disclosed embodiments of the present invention, only the structures related to the disclosed embodiments are involved. Other structures can refer to the general design. Without conflict, the same embodiment and different embodiments of the present invention can be combined with each other;
[0044] Finally, the above are only the preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the present invention shall be included within the protection scope of the present invention.
Claims
1. An integrated control method for an aircraft power supply system, characterized in that, Including: Directly electrically connect the engine controller to the generator output contactor, variable rectifier output contactor, battery output contactor, variable voltage rectifier, and battery; The engine controller receives the temperature signal, output voltage signal, and output current signal of the variable voltage rectifier in real time, judges the working state of the variable voltage rectifier, and performs output control and fault protection on the variable voltage rectifier according to the working state of the variable voltage rectifier; The generator controller receives the temperature signal, voltage signal, and current signal of the battery in real time, judges the working state of the battery, and performs output control and fault protection on the battery according to the working state of the battery.
2. The integrated control method of the aircraft power supply system according to claim 1, wherein: A variable rectifier control unit is arranged in the engine controller, and a line protection module, a power management module, and a health monitoring module are arranged in the variable rectifier control unit; the line protection module is used for overcurrent protection and short-circuit protection of the variable voltage rectifier, the power management module is used for priority power supply control of the variable voltage rectifier, and the health monitoring module is used for health management of the variable voltage rectifier.
3. The integrated control method for aircraft power supply system according to claim 2, wherein: An overcurrent detection circuit and a short-circuit protection circuit are arranged in the line protection module. The overcurrent detection circuit includes a Hall effect sensor and a relay. When the output current signal exceeds the limit, the Hall effect sensor detects the circuit and triggers the relay to disconnect; the short-circuit protection circuit includes an IGBT circuit, which disconnects when the IGBT circuit detects a short circuit.
4. The integrated control method for the aircraft power supply system according to claim 2, wherein: The different loads connected to the power management module are respectively marked, and then the different loads are sorted by priority. When the power supply in the aircraft is insufficient, power is cut off in turn in the order from low to high priority.
5. The integrated control method of the aircraft power supply system according to claim 2, characterized in that: The health monitoring module collects the temperature signal, output voltage signal, and output current signal of the variable voltage rectifier in real time and sends them to the flight control system. The aircraft system obtains the temperature signal, output voltage signal, and output current signal in the most recent period of time, obtains the maximum values of the temperature signal, output voltage signal, and output current signal for matching with the health management algorithm, selects the most suitable algorithm to calculate the aging degree of the current variable voltage rectifier, and outputs and saves the calculation result; after predicting that the aging degree of the variable voltage rectifier is greater than a certain value, an output alarm is given.
6. The integrated control method for an aircraft power supply system according to claim 1, characterized in that: A line protection module, a temperature compensation module, and a priority control module are arranged in the generator controller. Temperature protection thresholds, overvoltage protection thresholds, and overcurrent protection thresholds are respectively arranged in the line protection module; the obtained temperature signal, output voltage signal, and output current signal are respectively compared with the temperature protection threshold, overvoltage protection threshold, and overcurrent protection threshold. After judging that any one of the temperature, pressure, and temperature exceeds the corresponding threshold, the battery output contactor is controlled to disconnect; the temperature compensation module is used for temperature compensation of the battery when the battery temperature is detected to be too high; the priority control module is used for controlling the battery to disconnect some loads through the flight control system when the aircraft electrical energy is insufficient.
7. The integrated control method of the aircraft power supply system according to claim 6, characterized in that: A temperature-voltage control table is provided inside the temperature compensation module. Different charging parameters are correspondingly set in the temperature-voltage control table for different temperatures. After obtaining the current temperature signal of the storage battery, the corresponding charging parameters are found through the temperature-voltage control table, and then the voltage of the storage battery is controlled by the charging parameters.