Airplane single-phase emergency alternating current power supply system and switching method

Abstract

The invention belongs to the technical field of aircraft power supply systems, and particularly relates to an aircraft single-phase emergency alternating current power supply system and a switching method. Comprising an AC power distribution box, an emergency AC power control box, a DC power distribution box, a power control and display module and a static converter. The alternating current power distribution box is used for connecting an onboard main alternating current power supply or an auxiliary alternating current power supply or a static converter power supply, supplying power to alternating current electric equipment and transmitting a single-phase normal alternating current bus bar power supply to the emergency alternating current power supply control box; the emergency AC power supply control box is used for carrying out real-time power loss monitoring on a single-phase normal AC bus bar in the AC power supply distribution box, connecting the single-phase normal AC bus bar in the AC power supply distribution box with a single-phase emergency AC bus bar when power loss is monitored, and connecting the single-phase emergency AC bus bar with the single-phase normal AC bus bar in the AC power supply distribution box when power loss is monitored. The static converter is connected with the single-phase emergency AC bus bar, and self state information and output power information of the static converter are fed back to the power control and display module; the direct-current power supply distribution box is used for accessing an airplane direct-current power supply, providing an emergency direct-current power supply for the power supply control and display module and the static converter, and realizing power supply input control and short-circuit protection of the static converter; and the static converter is used for converting the emergency direct-current power supply output by the direct-current power supply distribution box into a single-phase alternating-current power supply and feeding back state information of the static converter to the power supply control and display module. The problem of reliable and automatic conversion of the single-phase emergency alternating current power supply under the condition that the airplane loses a main power supply system and an auxiliary power supply system and a normal alternating current bus bar loses power is solved.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft power supply systems, and in particular relates to an aircraft single-phase emergency alternating current power supply system and a switching method. Background Art

[0002] With the development of aircraft platforms and mission systems, onboard electrical equipment has become more and more numerous and more and more critical. A single power source is not enough to meet the requirements of power supply reliability, and redundant power supply is often set up to improve power supply reliability. According to the different forms of power sources, there are generally main power systems, auxiliary power systems, and emergency power systems. Under normal circumstances, the main power system supplies power to the power network of the entire aircraft; when the main power system fails, the power system function is downgraded and the auxiliary power system supplies power to the power network of the entire aircraft; when both the main power system and the auxiliary power system fail, the emergency power system supplies power to electrical equipment that is critical to the flight safety of the aircraft. According to the type of power supply, the emergency power supply system can be divided into emergency DC power supply system and emergency AC power supply system, which supply power to DC critical equipment and AC critical equipment respectively.

[0003] The existence of multiple power subsystems will inevitably introduce the problem of reliable conversion of different power subsystems, especially the emergency AC power system, which guarantees the reliable operation of single-phase AC important electrical equipment in emergency situations. Under the premise that the conversion cannot introduce additional faults, the conversion time requirements are also quite stringent. Unlike DC power supply, AC power supply is difficult to connect in parallel, especially emergency AC power supply, which has low capacity requirements, but simple system architecture requirements and high reliability requirements. The architecture of ensuring the power supply margin of important electrical equipment by connecting single-phase AC power in parallel is completely abandoned; relying on flight personnel to manually switch power subsystems in the event of power system failure is difficult to meet the requirements of power supply interruption time for important equipment; setting up multiple power supply management computers to collect the power network status of the entire aircraft, and controlling the on and off of the power supply contactor of the power network can also realize power conversion, but the development and procurement costs of this solution are relatively high. New aircraft models with sufficient funds can use this solution to control the power network of the entire aircraft. For improved models or cost-sensitive models, the cost of this solution is difficult to match the benefits.

[0004] Therefore, there is an urgent need for a single-phase emergency AC power supply system and switching method with high reliability, short conversion time and good economy. Summary of the invention

[0005] Purpose of the invention: The present invention solves the problem of reliable automatic conversion of single-phase emergency AC power supply when the aircraft loses the main power supply system, auxiliary power supply system and the normal AC bus loses power, while compressing the conversion time as much as possible, timely connecting to the emergency AC power supply network, meeting the power supply needs of single-phase AC important electrical equipment, ensuring the reliable operation of the power supply redundancy of important equipment, and effectively improving the survivability of the aircraft in an emergency state of the power supply system.

[0006] Technical solution of the present invention: In order to achieve the above-mentioned purpose of the invention, according to the first aspect of the present invention, a single-phase emergency AC power supply system is proposed, including an AC power distribution box, an emergency AC power control box, a DC power distribution box, a power control and display module and a static converter; the AC power distribution box is used to access the main AC power or auxiliary AC power or static converter power on the machine to supply power to AC power-consuming equipment, and transmit the single-phase normal AC bus power to the emergency AC power control box; the emergency AC power control box is used to perform real-time power failure monitoring on the single-phase normal AC bus in the AC power distribution box, and when it is detected that there is no power failure, the single-phase normal AC bus in the AC power distribution box is connected to the AC power distribution box. The two-phase normal AC bus is connected with the single-phase emergency AC bus. When power failure is detected, the static converter is connected with the single-phase emergency AC bus, and its own status information and the output power information of the static converter are fed back to the power control and display module; the DC power distribution box is used to access the aircraft DC power supply, provide emergency DC power to the power control and display module and the static converter, and realize power supply input control and short-circuit protection of the static converter; the static converter is used to convert the emergency DC power output by the DC power distribution box into a single-phase AC power, and has over / under voltage, over / under frequency, overheating and other protection functions, and feeds back its own status information to the power control and display module.

[0007] The power control and display module is used for the operation start-up control of the static converter, and displays the status information and output power information of the static converter, the power supply channel information of the DC power distribution box, and the status information of the emergency AC power control box; and sends a control signal of the emergency power conversion module to the emergency AC power control box.

[0008] In a possible embodiment, the emergency AC power control box includes a power failure monitoring module, an emergency power conversion module and a power information acquisition module; the power failure monitoring module is used to monitor whether the normal AC bus in the AC power distribution box loses power. If the power fails, the power failure monitoring module is in an on state, and the emergency power conversion module is converted to connect the static converter to supply power to the single-phase emergency AC bus in the AC distribution box; if the power does not fail, the power failure monitoring module is in a disconnected state, the emergency power conversion module remains on, and the single-phase normal AC bus in the AC power distribution box is in a state of supplying power to the single-phase emergency AC bus; the power information acquisition module is used to collect the output voltage and current of the static converter and feed it back to the power control and display module. The power information acquisition module is interconnected with the output of the static converter through analog quantity to collect the voltage, current and frequency of the output power of the static converter; the power information acquisition module is interconnected with the power control and display module through analog quantity to send the output voltage, current and frequency of the static converter to the power control and display module, so that the aircrew / ground crew can grasp the working status of the static converter and make operation or maintenance in time.

[0009] In a possible embodiment, the DC power distribution box includes an emergency DC bus and a power supply input control module; the emergency DC bus is connected to the onboard emergency DC power supply, the emergency DC bus is electrically connected to the power supply input control module, the power supply input module is controlled by the power control and display module, and is used to realize the on-off control of the power supply input of the static converter, has the function of realizing short circuit / overcurrent protection, and feeds back its own status information to the power control interaction and display module.

[0010] In a possible embodiment, the AC power distribution box includes a single-phase normal AC bus and a single-phase emergency AC bus; wherein the single-phase normal AC bus is connected to the onboard AC power supply.

[0011] According to a second aspect of the present invention, a single-phase emergency AC power supply system switching method is proposed, which adopts the above-mentioned single-phase emergency AC power supply system. When the emergency AC power supply control box detects that the single-phase normal AC bus in the AC power distribution box is in a power-off state, the power supply from the single-phase normal AC bus to the single-phase emergency AC bus is automatically converted into the power supply from the static inverter to the single-phase emergency AC bus.

[0012] In a possible embodiment, a control signal is sent to the DC power control box through the power control and display module, the power input control module in the DC power distribution box is turned on, and the static converter starts to work.

[0013] In a possible embodiment, a control signal is sent to the emergency AC power control box through the power control and display module, and the emergency power conversion module is controlled through the power failure monitoring module. When the power failure monitoring module detects that the single-phase normal AC bus in the AC power distribution box has lost power, the working power of the emergency power conversion module is turned on, and the static inverter is switched to supply power to the single-phase emergency AC bus in the AC power distribution box. When it is detected that there is no power failure, the single-phase normal AC bus is kept supplying power to the single-phase emergency AC bus.

[0014] Thanks to the setting of the power failure monitoring module and the emergency power conversion module in the emergency AC power control box, it is ensured that even if the static inverter is turned on, it cannot be connected to the power grid when the single-phase normal AC bus of the AC power distribution box is in normal state, and can be in hot backup state. When the single-phase normal AC bus of the AC power distribution box loses power, it is automatically converted to the static inverter to supply power to the single-phase emergency AC bus in the AC power distribution box, so as to meet the power demand of single-phase heavy AC power-consuming equipment.

[0015] The advantages of the present invention are:

[0016] 1. Ensure the isolation of the two AC power supplies to avoid short circuit between the power supplies and eliminate the hidden dangers of failure caused by system operation.

[0017] The particularity of the operating conditions of the emergency AC power conversion system requires the simplicity of the system and the reliability of the operation and conversion process. This system has only two states: the normal AC bus (115V) and the static inverter output AC 115V are neither powered at the same time nor disconnected at the same time. This eliminates the possibility of a short circuit between the normal AC 115V and the static inverter output AC 115V power supply, while also ensuring a reliable power supply for the single-phase emergency AC bus, providing a prerequisite for the hot backup working state of the static inverter.

[0018] 2. It has the advantages of automatic, accurate and high consistency in the timing of emergency power supply conversion, which reduces the emergency power supply conversion time and improves the response time when the system fails.

[0019] In the described single-phase emergency AC power switching method for an aircraft, the same normal AC bus is selected for power failure detection and power supply to the emergency AC bus, which can effectively avoid erroneous conversion caused by false faults such as acquisition by the upper power supply and distribution system; the default state of the power failure monitoring module without control power is utilized to solve the working problem of the power failure monitoring module without drive power, and the emergency power conversion module is controlled to achieve conversion. Thanks to the settings of the power failure monitoring module and the emergency power conversion module, the static converter can be in a hot backup state. After the normal AC bus loses power, the power failure monitoring module returns to the default state, and the emergency power conversion module moves to the normally open position. The static converter can supply power to the single-phase emergency AC 115V bus. The measured conversion time is about 20ms, which is much better than the GJB181 requirement.

[0020] 3. It has the function of detecting status information such as fault information alarm of static converter, which is convenient for timely finding fault information, eliminating hidden faults, and improving the safety, stability and maintainability of system operation.

[0021] The described single-phase emergency AC power switching method for aircraft detects the fault information of the static inverter, the status information of the power input control module, the power failure monitoring module, and the emergency power conversion module, and is displayed uniformly by the power control and display module to achieve timely troubleshooting of hidden faults. The timely discovery of hidden faults is crucial to the safe and stable operation of the system, especially the backup emergency system. To ensure reliability during emergency use, hidden faults are difficult to be discovered if power system fault simulation is not performed to check the conversion of the emergency AC power supply. This method can detect hidden faults in a timely manner by collecting and displaying the status information of key components, ensuring the good operation of the system and improving the maintainability of the system. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 The present invention is a cross-link diagram of a single-phase emergency AC power supply switching method for an aircraft. DETAILED DESCRIPTION

[0023] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0024] The features and illustrative embodiments of various aspects of the present invention will be described in detail below. In the detailed description below, many specific details are proposed to provide a comprehensive understanding of the present invention. However, it is obvious to those skilled in the art that the present invention can be implemented without the need for some of these specific details. The following description of the embodiments is only to provide a better understanding of the present invention by illustrating examples of the present invention. The present invention is by no means limited to any specific settings and methods proposed below, but covers any improvements, replacements and modifications of structures, methods, devices without departing from the spirit of the present invention. In the accompanying drawings and the following description, known structures and technologies are not shown to avoid unnecessary ambiguity in the present invention.

[0025] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other, and the embodiments can refer to and quote each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0026] like Figure 1 As shown, an aircraft single-phase emergency AC power system mainly includes an AC power distribution box, an emergency AC power control box, a DC power distribution box, a power control and display module and a static converter.

[0027] The AC power distribution box can be used with the one provided on the aircraft, and no separate configuration is required. Figure 1 As shown, a single-phase emergency AC bus (115V), a single-phase normal AC bus (115V) power failure monitoring channel, and a single-phase normal AC bus (115V) to single-phase emergency AC bus (115V) power supply channel are added to the AC power distribution box. The power failure monitoring position and the power supply to the single-phase emergency AC bus (115V) are the same C-phase normal AC bus (115V) (if the aircraft power supply system is a three-phase AC power supply system, a certain phase can be selected according to the distribution of the whole machine load. In this example, the C phase is selected). In this example, the main power supply and auxiliary power supply of the aircraft are both 115V three-phase AC power supplies. When the main power supply or auxiliary power supply is normal, the C-phase normal AC bus (115V) in the AC power distribution box is powered.

[0028] An aircraft single-phase emergency AC power supply system needs to be equipped with an emergency AC power supply control box, which mainly includes a power failure monitoring module, an emergency power supply conversion module and a power supply information acquisition module. The power failure monitoring module is used to monitor whether the normal AC bus (115V) of phase C in the AC power distribution box has lost power. At the same time, the monitored 115V power supply is used as the working power supply of the power failure monitoring module, and the emergency 28.5V power supply issued by the power control and display module is controlled. The default state of power failure is connected, and it also has the function of feeding back the status information of the power failure monitoring module to the power control and display module. The emergency power supply conversion module is used for the specific implementation of the conversion of the power supply source of the single-phase emergency AC bus (115V). The type and specification are selected according to the power required by the important AC power-consuming equipment. The power required in this example is 1kVA, and the corresponding current is 8.7A. According to the principle of derating, an emergency power supply conversion module with a rated current of 15A is selected; the emergency power supply conversion module has only two states, such as Figure 1 As shown, one is the default state of power failure: the normal AC busbar (115V) of phase C of the AC power distribution box supplies power to the single-phase emergency AC busbar (115V) through the emergency power conversion module; the other is the power-on state: the AC 115V power supply output by the static converter supplies power to the single-phase emergency AC busbar (115V), and at the same time has the function of feeding back its own state to the power control and display module. The power information acquisition module is used to collect the voltage, current and frequency information of the output power of the static converter, and feed it back to the power control and display module.

[0029] The DC power distribution box can be used with the one provided on the aircraft, and no separate configuration is required. Figure 1 As shown, a static converter power supply input control module and a power distribution channel for supplying power to the power control and display module are added to the DC power distribution box. The working power of the static converter and the power control and display module comes from the same emergency DC bus in the DC power distribution box. This bus is powered by an aviation battery in an emergency state of the power system. The type and specification of the power supply input control module are selected according to the rated power and efficiency of the static converter and the principle of derating. In this example, a power supply input control module with a rated current of 100A is selected. At the same time, the module also has the functions of overcurrent / short circuit protection and feedback of status information to the power control and display module.

[0030] The power control and display module is provided with a static converter switch and a static converter fault indicator light, and is installed on the power control board along with the power system switch as a whole; the DC power distribution box status information, the emergency AC power control box status information and the static converter output power information are processed and displayed by the power multi-function display processor along with the power system status information as a whole. The power supply of the power control and display module is supplied by the emergency DC bus bar (28.5V) in the DC power distribution box, and this emergency DC bus bar (28.5V) should be powered by an aviation battery to ensure the availability of the power system in an emergency state. The static converter switch is a two-position switch, which can be turned on or off. When turned on, it controls the power input control module in the DC power distribution box to be turned on, and the static converter starts to work, converting the 28.5V DC power supply into a 115V AC power supply; the static converter switch also sends a 28.5V control signal to the emergency AC power control box. When the C-phase normal AC busbar (115V) in the AC power distribution box loses power, the power failure monitoring module is in the default state, and the 28.5V control signal controls the emergency power conversion module to operate through the power failure monitoring module, and is converted to supply power to the single-phase emergency AC busbar (115V) by the static converter. The static converter fault indicator light is red. When the static converter fails, the red fault light is on, and the aircrew can choose to return or continue the mission according to the main power system, auxiliary power system and mission urgency. The power multi-function display processor displays the status information of the power input control module in the DC power distribution box, the status information of the power failure monitoring module and the emergency power conversion module in the emergency AC power control box, and the output power information of the static converter. The ground staff can timely discover hidden faults and eliminate potential fault hazards based on the status display information of the power input control module, the power failure monitoring module, the emergency power conversion module and the output power information of the static converter.

[0031] A set of static converters is required to convert the emergency 28.5V DC power provided by the DC power distribution box into a single-phase 115V AC power supply. The rated power of the static converter is determined according to the power required by the important AC power-consuming equipment. The rated power of the static converter selected in this example is 1kVA. The work start is controlled by the static converter switch on the power control and display module. The static converter has over / under voltage, over / under frequency, overheating and other protection functions. Once there is no output, a fault signal is sent to the power control and display module, and the red fault indicator light of the static converter is lit to warn. A single-phase emergency AC power supply system and a switching method are used. Before the aircraft takes off, when the aircraft power supply system is intact, the static converter switch on the power control panel of the power control and display module is turned on, and the fault indicator light on the power control and display module is observed to be off. The power input control module displayed by the power control and display module should be in the on position, the power failure monitoring module should be in the off position, the emergency power conversion module should be in the default position, the output voltage / frequency of the static converter should be within the normal range, the output current is 0, and the static converter is in the hot backup state and is not connected to the emergency AC power grid. At this time, the C-phase normal AC busbar (115V) in the AC power distribution box keeps supplying power to the single-phase emergency AC busbar (115V) through the emergency power conversion module. The phenomenon is consistent with the above description before the aircraft is allowed to take off. If an abnormality occurs, the ground staff can troubleshoot the fault according to the displayed information and eliminate the hidden dangers of the fault. When the main power supply and auxiliary power supply of the aircraft fail or the normal AC busbar (115V) of phase C in the AC power distribution box loses power due to other reasons, the power failure monitoring module in the emergency AC power control box loses working power and returns to the default state. Since the static converter switch of the power control and display module is already in the on state before takeoff, the 28.5V control signal sent by the static converter switch controls the emergency power conversion module through the power failure monitoring module in the emergency AC power control box, and automatically converts to the static converter to supply power to the single-phase emergency AC busbar (115V) in the AC power distribution box. At this point, the conversion of the single-phase emergency AC power system when the power system fails is completed. According to the measured results, the conversion time is about 20ms, which is much better than the requirements of GJB 181. At this time, the operator observes that the static inverter fault indicator light on the power control and display module should still be off, the power input control module displayed by the power multi-function display processor should be in the on position, the power failure monitoring module should be in the on position, the emergency power conversion module should be in the static inverter power supply state, the output voltage / frequency of the static inverter should be within the normal range, and the output current should be the load consumption current, confirming that the single-phase emergency AC power supply system is working normally.

[0032] The above describes the specific embodiments of the present invention. It should be noted that, for those skilled in the art, several improvements and modifications can be made without departing from the principles of the present invention. These improvements and modifications should also fall within the scope of protection of the present invention.

Claims

1. An aircraft single-phase emergency AC power supply system, characterized in that: It includes an AC power distribution box, an emergency AC power control box, a DC power distribution box, a power control and display module and a static converter; the AC power distribution box is used to access the main AC power or auxiliary AC power or static converter power on the machine to supply power to AC power-consuming equipment, and transmit the single-phase normal AC bus power to the emergency AC power control box; the emergency AC power control box is used to perform real-time power failure monitoring on the single-phase normal AC bus in the AC power distribution box, and when it is detected that there is no power failure, the single-phase normal AC bus in the AC power distribution box is connected to the single-phase emergency The AC bus is connected, and when power failure is detected, the static converter is connected to the single-phase emergency AC bus, and its own status information and the output power information of the static converter are fed back to the power control and display module; the DC power distribution box is used to access the aircraft DC power supply, provide emergency DC power to the power control and display module and the static converter, and realize power supply input control and short-circuit protection of the static converter; the static converter is used to convert the emergency DC power output by the DC power distribution box into a single-phase AC power, and feed back its own status information to the power control and display module.

2. The aircraft single-phase emergency AC power supply system according to claim 1, characterized in that: The power control and display module is used for the operation start-up control of the static converter, and displays the status information and output power information of the static converter, the power supply channel information of the DC power distribution box, and the status information of the emergency AC power control box; and sends a control signal of the emergency power conversion module to the emergency AC power control box.

3. The aircraft single-phase emergency AC power supply system according to claim 1, characterized in that: The emergency AC power control box includes a power failure monitoring module, an emergency power conversion module and a power information acquisition module; the power failure monitoring module is used to monitor whether the normal AC bus in the AC power distribution box loses power. If the power fails, the power failure monitoring module is in an on state, and the emergency power conversion module is converted to connect the static converter to supply power to the single-phase emergency AC bus in the AC distribution box; if the power does not fail, the power failure monitoring module is in a disconnected state, the emergency power conversion module remains on, and the single-phase normal AC bus in the AC power distribution box is in a state of supplying power to the single-phase emergency AC bus; the power information acquisition module is used to collect the output voltage and current of the static converter and feed it back to the power control and display module. The power information acquisition module is interconnected with the output of the static converter through analog quantity to collect the voltage, current and frequency of the output power of the static converter; the power information acquisition module is interconnected with the power control and display module through analog quantity to send the output voltage, current and frequency of the static converter to the power control and display module, so that the aircrew / ground crew can grasp the working status of the static converter and make operation or maintenance in time.

4. The aircraft single-phase emergency AC power supply system according to claim 1, characterized in that: The DC power distribution box includes an emergency DC bus and a power supply input control module; the emergency DC bus is connected to the onboard emergency DC power supply, the emergency DC bus is electrically connected to the power supply input control module, the power supply input module is controlled by the power control and display module, and is used to realize the on-off control of the power supply input of the static converter, has the function of realizing short circuit / overcurrent protection, and feeds back its own status information to the power control interaction and display module.

5. The aircraft single-phase emergency AC power supply system according to claim 1, characterized in that: The AC power distribution box comprises a single-phase normal AC bus bar and a single-phase emergency AC bus bar; wherein the single-phase normal AC bus bar is connected to the onboard AC power supply.

6. A single-phase emergency AC power supply system switching method, using a single-phase emergency AC power supply system according to any one of claims 1 to 5, characterized in that: When the emergency AC power control box detects that the single-phase normal AC bus in the AC power distribution box is in a power-off state, the power supply from the single-phase normal AC bus to the single-phase emergency AC bus is automatically converted to the power supply from the static converter to the single-phase emergency AC bus.

7. A single-phase emergency AC power system switching method according to claim 6, characterized in that: A control signal is sent to the DC power control box through the power control and display module, the power input control module in the DC power distribution box is turned on, and the static converter starts to work.

8. A single-phase emergency AC power system switching method according to claim 6, characterized in that: A control signal is sent to the emergency AC power control box through the power control and display module, and the emergency power conversion module is controlled through the power failure monitoring module. When the power failure monitoring module detects that the single-phase normal AC bus in the AC power distribution box has lost power, the working power of the emergency power conversion module is turned on, and the static inverter is switched to supply power to the single-phase emergency AC bus in the AC power distribution box. When it is detected that there is no power failure, the single-phase normal AC bus is kept supplying power to the single-phase emergency AC bus.

Images