A helicopter AC-DC hybrid power supply system and an aircraft

Abstract

The application belongs to the technical field of helicopter power supply system design, and particularly relates to a helicopter AC-DC hybrid power supply system and an aircraft. A 1# main reduction AC generator is connected with a 1# AC bus bar through a 1# main reduction AC generator contactor; a 1# AC starting generator contactor is connected with a 1# voltage transformer rectifier at a common end, connected with a 1# AC starting generator at a 1A end, and connected with the 1# AC bus bar at a 1B end; the 1# voltage transformer rectifier is connected with a 1# general bus bar through a 1# voltage transformer rectifier contactor; a 3# AC starting generator contactor is connected with a 3# voltage transformer rectifier at a common end, connected with a 3# AC starting generator at a 3A end, and connected with a 2# AC bus bar at a 3B end; the 3# voltage transformer rectifier is connected with a 3# general bus bar through a 3# voltage transformer rectifier contactor; an APU AC generator contactor is connected with an emergency voltage transformer rectifier at a common end, connected with an APU AC generator at a 4A end, and connected with the 2# AC bus bar at a 4B end; and the emergency voltage transformer rectifier is connected with an important bus bar through an emergency voltage transformer rectifier contactor.

Description

Technical Field

[0001] This invention belongs to the field of helicopter power system design technology, and specifically relates to a helicopter AC / DC hybrid power supply system and an aircraft. Background Technology

[0002] The helicopter's power system consists of an AC power system and a DC power system. The AC power system mainly consists of a main reducer AC generator, providing 115V, 400Hz AC power to the aircraft. The DC power system mainly consists of a DC starter generator or transformer rectifier, providing 28V DC power to the aircraft.

[0003] Traditional helicopter power systems have low interconnectivity between power sources and relatively simple inputs, resulting in low power margin and poor reliability. Summary of the Invention

[0004] Purpose of the invention: This invention proposes a hybrid AC / DC power supply system for helicopters. Through a redundant design approach, various power sources can be switched between each other, resulting in a high degree of interconnection and thus improving the reliability of the power supply system.

[0005] Technical solution

[0006] A helicopter AC / DC hybrid power supply system comprises the following components:

[0007] The No. 1 main reducer AC generator is connected to the No. 1 AC busbar via the No. 1 main reducer AC generator contactor;

[0008] The No. 2 main reducer AC generator is connected to the No. 2 AC busbar via the No. 2 main reducer AC generator contactor;

[0009] The common terminal of the #1 AC starter generator contactor is connected to the #1 transformer rectifier, terminal 1A is connected to the #1 AC starter generator, and terminal 1B is connected to the #1 AC busbar; the #1 transformer rectifier is connected to the #1 general busbar through the #1 transformer rectifier contactor.

[0010] The common terminal of the #2 AC starter generator contactor is connected to the #2 transformer rectifier, terminal 2A is connected to the #2 AC starter generator, and terminal 2B is connected to the #1 AC busbar; the #2 transformer rectifier is connected to the #2 general busbar through the #2 transformer rectifier contactor.

[0011] The common terminal of the #3 AC starter generator contactor is connected to the #3 transformer rectifier, terminal 3A is connected to the #3 AC starter generator, and terminal 3B is connected to the #2 AC busbar; the #3 transformer rectifier is connected to the #3 general busbar through the #3 transformer rectifier contactor.

[0012] The APU AC generator contactor's common terminal connects to the emergency transformer rectifier, terminal 4A connects to the APU AC generator, and terminal 4B connects to the #2 AC busbar; the emergency transformer rectifier connects to the important busbars via the emergency transformer rectifier contactor.

[0013] The main reducer AC generator is installed on the main reducer and mainly supplies power to AC loads. When the AC starter generator is not working, it can also supply power to the DC power system through the transformer rectifier.

[0014] An AC starter generator is mounted on the engine. When the engine is stopped, it acts as an AC motor to start the engine. When the engine is running, it acts as an AC generator to power the transformer rectifier. An APU AC generator is mounted on the auxiliary engine (APU). When on the ground, it can be used to start the engine. In an emergency in-flight situation, it can power the emergency transformer rectifier.

[0015] Furthermore, the #1 AC busbar is also connected to an external AC power source via an external AC power contactor. When the external AC power source is on the ground, it can supply AC power to the aircraft, supply power to the DC power system through a transformer and rectifier, and can also be used for engine starting. When the external DC power source is on the ground, it can supply DC power to the aircraft, start the APU via the #3 contactor, and start the engine via the APU generator.

[0016] Furthermore, the #2 AC busbar is also connected to the APU AC generator via an AC contactor. If both the #1 main reducer AC generator contactor 7 and the #2 main reducer AC generator contactor 10 are in the open state, the APU should be started immediately, connecting the APU AC generator 3. The APU AC generator contactor 17 should be set to point A, and the APU AC generator 3 should supply power to the emergency transformer rectifier 21 to ensure that the emergency power supply duration is not limited by the battery capacity.

[0017] Furthermore, AC busbar #1 and AC busbar #2 are interconnected via AC connection contactors. The two AC busbars can supply power to each other, improving redundancy.

[0018] Furthermore, general busbar #1 and general busbar #2 are interconnected via contactor #1, general busbar #2 and general busbar #3 are interconnected via contactor #2, and general busbar #3 and the critical busbar are interconnected via contactor #3. The three general busbars can supply power to each other, improving redundancy.

[0019] Furthermore, the power diode is connected in parallel with contactor #3, with the anode of the power diode connected to the general busbar #3 and the cathode connected to the critical busbar. By employing a combination circuit of time-delay relays and diodes, uninterrupted power supply to the critical busbar is ensured when the DC external power supply transformer rectifier is providing power. When the helicopter enters emergency power supply mode, since contactor #32 is already in the open state when the DC external power supply stops supplying power to the helicopter, the power diode 37 will prevent current from flowing from the critical busbar 29 to the general busbar #3 28, thereby ensuring that the battery pack 33 and the emergency transformer rectifier 21 supply power to the critical equipment on the helicopter, while the remaining equipment is unloaded.

[0020] Furthermore, key busbars are connected to the battery via battery contactors. The battery bank provides emergency power to the DC power system and can also be used to start the APU when on the ground.

[0021] Furthermore, the #3 general busbar is connected to an external DC power supply via a DC external power contactor. When the external DC power supply is transformed into a voltage rectifier, uninterrupted power supply to critical busbars can be achieved.

[0022] An aircraft comprising the aforementioned helicopter AC / DC hybrid power supply system.

[0023] In summary, the beneficial effects of the present invention are as follows:

[0024] 1. Whether it is a transformer rectifier or a general busbar, it has two power inputs, and the power system has high reliability;

[0025] 2. Multiple engine starting methods can reduce the burden on helicopter support resources, while also ensuring that engine starting in the air is not limited by the power system;

[0026] 3. By setting up mutual backup modes among multiple power supplies, the reliability of the power system is improved with the existing number of power supplies, resulting in good economic efficiency;

[0027] 4. Because the critical busbars provide uninterrupted power, the electrical equipment on the critical busbars can operate normally during power conversion without the need for energy storage capacitors, thereby reducing the weight and cost of the electrical equipment. Attached Figure Description

[0028] Figure 1 This is a schematic diagram of a helicopter AC / DC hybrid power supply system.

[0029] Figure 2 This is a schematic diagram showing the local connection relationships of important busbars. Detailed Implementation

[0030] To enable those skilled in the art to better understand the present application, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present application, and not all embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative effort should fall within the scope of protection of the present application.

[0031] In this application, the terms "upper," "lower," "left," "right," "front," "rear," "top," "bottom," "inner," "outer," "middle," "vertical," "horizontal," "lateral," and "longitudinal" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. These terms are primarily for the purpose of better describing this application and its embodiments, and are not intended to limit the indicated device, element, or component to having a specific orientation, or to be constructed and operated in a specific orientation.

[0032] Furthermore, the terms "installation," "setup," "equipped with," "connection," "linking," and "socketing" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral structure; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium, or an internal connection between two devices, components, or parts. Those skilled in the art can understand the specific meaning of these terms in this application based on the specific circumstances.

[0033] A helicopter AC / DC hybrid power supply system mainly consists of: 1# main reducer AC generator, 2# main reducer AC generators, 3# APU AC generator, 4# external AC power supply, 5# AC busbar, 6# AC busbar, 7# main reducer AC generator contactor, 8# external AC power supply contactor, 9# AC connection contactor, 10# main reducer AC generator contactor, 11# AC starter generator, 12# AC starter generator, 13# AC starter generator, 14# AC starter generator contactor, 15# AC starter generator contactor, 16# AC starter generator contactor, 17# APU AC generator contactor, and 18# AC starter generator contactor. Composed of: #18, #2, #3, #2, #3, #21, #1, #2, #2, #3 ...4, #3, #3, #3, #3, #3, #3, #3, #3, #3, #3, #3, #4, #3, #3, #3, #3, #3, #3, #3, #4, #3, #3, #3, #3, #3, #3, #4, #3, #3, #3, #3, #3, #4, #3, #3, #3, #3, #3, #4, #3, #3, #3, #3, #4, #3, #3, #3, #3, #4, #3, #

[0034] The main reducer alternator is installed on the main reducer and primarily supplies power to AC loads. When the AC starter generator is not operating, it can also supply power to the DC power system via a transformer rectifier. The AC starter generator is installed on the engine and functions as an AC motor to start the engine when it is stopped, and as an AC generator to supply power to the transformer rectifier when the engine is running. The APU alternator is installed on the auxiliary engine (APU) and can be used to start the engine on the ground, and to supply power to the emergency transformer rectifier in an emergency in-flight situation.

[0035] Transformer rectifiers #1, #2, and #3 convert the AC power supplied by the AC starter generator or AC busbar into DC power and supply it to the corresponding general busbar. When the transformer rectifiers are not operating, the general busbars can be powered by adjacent busbars.

[0036] Emergency transformer rectifiers convert AC power supplied by AC busbars or APU AC generators into DC power and supply power to critical busbars.

[0037] When the external AC power supply is on the ground, it can provide AC power to the aircraft, supply power to the DC power system through a transformer and rectifier, and can also be used for engine starting. When the external DC power supply is on the ground, it can provide DC power to the aircraft, start the APU through contactor #3, and start the engine through the APU generator.

[0038] When powered by an external DC power supply converter and rectifier, uninterrupted power supply to critical busbars can be achieved. The battery bank provides emergency power to the DC power system and can also be used to start the APU when on the ground.

[0039] When AC external power supply 4 supplies power to the helicopter, AC external power supply contactor 8 is turned on, AC connection contactor 9 is turned on, and AC external power supply supplies power to the helicopter. AC starter generator contactors 14, 15, 16, and 17 are all set to point B. AC power loads and transformer rectifiers start working. The transformer rectifier switch is turned on, and transformer rectifier contactors 22, 23, 24, and 25 are turned on. 28V DC power is supplied to general busbars 26, 27, 28, and 29, and DC power loads start working. At this time, the AC power on AC busbar 5 (1#) and AC busbar 6 (2#) can be used to supply power to AC starter generator 11 (1#), AC starter generator 12 (2#), and AC starter generator 13 (3#) for engine starting.

[0040] When the DC external power supply 35 supplies power to the helicopter, the DC external power supply contactor 36 is activated, and contactors 30 (connected to #1), 31 (connected to #2), and 32 (connected to #3) are also activated. The battery contactor 34 is deactivated, and the DC external power supply supplies power to general busbars 26 (#1), 27 (#2), 28 (#3), and 29 (critical busbar). Because contactor 32 (#3) is activated, the power diode 37 is short-circuited to prevent damage caused by the large current flowing through it during APU startup.

[0041] The positive terminal of the control coil of time delay relay 39 is connected to the external power supply, and the negative terminal is connected to the auxiliary contact of TRU contactor 24. When TRU contactor 24 is energized, the negative terminal of time delay relay 39 is disconnected from ground, and time delay relay 39 is released; this is a delayed release. When time delay relay 39 is released, its main control contact is disconnected from ground, and the negative terminals of connected contactor 32 and external power contactor 36 are also disconnected from ground, and connected contactor 32 and external power contactor 36 are released.

[0042] After the APU starts successfully, the APU alternator 3 begins to work, AC contactor 38 is activated, and AC connecting contactor 9 is activated. The APU alternator 3 supplies power to AC busbar 5 (#1) and AC busbar 6 (#2). When the engine starts, the AC power from AC busbars 5 (#1) and 6 (#2) can be used to supply power to AC starter generators 11 (#1), 12 (#2), and 13 (#3) for engine starting.

[0043] Contactors 14, 15, and 16 of the AC starter generator are all placed at point B. Contactor 17 of the APU AC generator is placed at point A. Transformer rectifiers 18, 19, 20, 21 and 21 of the transformer rectifier begin to work.

[0044] If the transformer rectifier switch is turned on at this time, contactors 22 (1#), 23 (2#), 24 (3#), and 25 (emergency transformer rectifier) ​​will be connected. Since the contactor disconnection time is shorter than the connection time, to prevent the DC external power contactor 36 from disconnecting before contactor 24 (3#) is connected, causing a short-term power outage to the equipment on the critical busbar 29, a time-delay relay 39 disconnects after a delay during the connection process of contactor 24 (3#). This ensures that contactor 36 (3#) disconnects after contactor 24 (3#) is fully connected. After the time-delay relay 39 disconnects, contactors 36 (3#) and 32 (3#) are disconnected. Due to the presence of the power diode 37, the critical busbar 29 is guaranteed uninterrupted power supply during the period when the DC external power supply transformer rectifier is supplying power to the machine.

[0045] When only battery 33 supplies power to the helicopter, battery contactor 34 is engaged, while all other contactors are disengaged, and only the critical busbar 29 has power. At this time, the APU should be started as soon as possible to engage the APU alternator 3, which will then supply power to the entire helicopter.

[0046] After all three engines have started successfully, shut down APU alternator 3 and turn on alternators 1#, 2#, 1#, 2#, and 3#. Connect contactors 7 and 10 of alternators 1# and 2#, respectively. Disconnect contactor 9. Set contactors 14, 15, and 16 of alternators 1#, 2#, and 3# to point A. Set contactor 17 of APU alternator to point B. Alternators 11, 12, and 13 supply power to transformers 1#, 2#, and 3# respectively.

[0047] When the transformer rectifier switch is turned on, contactors 22, 23, 24, 25, and 34 of transformer rectifier 1, emergency transformer rectifier, and battery contactor 34 are connected. Contactors 30 and 31 of connected transformer 1 and 2 are disconnected. Transformer rectifier 18 supplies power to general busbar 26, transformer rectifier 19 supplies power to general busbar 27, transformer rectifier 20 supplies power to general busbar 28, and emergency transformer rectifier 21 supplies power to critical busbar 29.

[0048] When the contactor 22 of transformer rectifier #1 is disconnected, the contactor 30 of connected transformer #1 is connected, and the general busbar 27 of transformer #2 supplies power to the general busbar 26 of transformer #1.

[0049] When the contactor 23 of transformer rectifier #2 is disconnected, the contactor 30 of connected #1 is connected, and the general busbar 26 of #1 supplies power to the general busbar 27 of #1.

[0050] When the contactor 24 of transformer rectifier #3 is disconnected, the contactor 31 of connected transformer #2 is connected, and the general busbar 27 of transformer #2 supplies power to the general busbar 28 of transformer #3.

[0051] When contactor 22 of transformer rectifier #1 and contactor 23 of transformer rectifier #2 are disconnected, contactor 30 of connected transformer #1 and contactor 31 of connected transformer #2 are connected. General bus bar #3 23 supplies power to general bus bar #27, and general bus bar #27 supplies power to general bus bar #1 26.

[0052] When contactor 22 of transformer rectifier #1 and contactor 24 of transformer rectifier #3 are disconnected, contactor 30 of connected circuit #1 and contactor 31 of connected circuit #2 are connected, and general busbar #27 supplies power to general busbar #126 and general busbar #32.

[0053] When contactors 23 and 24 of transformer rectifier #2 are disconnected, contactors 30 and 31 of connected transformer #1 and connected transformer #2 are connected. General busbar #1 26 supplies power to general busbar #27, and general busbar #27 supplies power to general busbar #38.

[0054] When contactors 22, 23, and 24 of transformer rectifier #1 are all disconnected, the helicopter enters emergency power supply mode. Since contactor 32 of the connected #3 is already disconnected when the DC external power supply stops supplying power to the helicopter, power diode 37 will prevent current from flowing from the critical busbar 29 to the general busbar 28 of #3, thus ensuring that the battery pack 33 and emergency transformer rectifier 21 supply power to the important equipment on the helicopter, and the other equipment is unloaded. If contactors 7 of the main reducer AC generator #1 and 10 of the main reducer AC generator #2 are also disconnected at this time, the APU should be started immediately, and the APU AC generator 3 should be connected. The APU AC generator contactor 17 should be set to point A, and the APU AC generator 3 should supply power to the emergency transformer rectifier 21 to ensure that the emergency power supply duration is not limited by the battery capacity.

[0055] When the engine stops, the AC starter generator can be powered by the main reducer AC generator to restart the engine.

[0056] Transformer rectifiers #1, #2, and #3 each have two three-phase AC power inputs. The AC starting generator is the main power source, and the main reducing AC generator is the backup power source. The two inputs can be automatically switched, which improves the reliability of the DC power system.

[0057] The engine can be started using AC ground power, the main reducer alternator, or the APU alternator, providing multiple starting methods to ensure normal engine starting.

[0058] The use of an emergency transformer rectifier allows for power supply via the APU AC generator when common-mode faults occur in transformers #1, #2, and #3, or when the main reducer AC generator and AC starter generator are not permitted to draw power after both engines have stopped.

[0059] Ensure that the emergency power supply time for helicopters is unlimited.

[0060] By employing a combination circuit of time-delay relays and diodes, the critical busbars are ensured to be powered uninterrupted when the DC external power supply is transformed into a voltage rectifier.

[0061] The above description is merely a preferred embodiment of this application and is not intended to limit this application. Various modifications and variations can be made to this application by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this application should be included within the protection scope of this application.

Claims

1. A helicopter AC / DC hybrid power supply system, characterized in that: The system consists of the following components: The No. 1 main reducer AC generator is connected to the No. 1 AC busbar via the No. 1 main reducer AC generator contactor; The No. 2 main reducer AC generator is connected to the No. 2 AC busbar via the No. 2 main reducer AC generator contactor; The common terminal of the #1 AC starter generator contactor is connected to the #1 transformer rectifier, terminal 1A is connected to the #1 AC starter generator, and terminal 1B is connected to the #1 AC busbar; the #1 transformer rectifier is connected to the #1 general busbar through the #1 transformer rectifier contactor. The common terminal of the #2 AC starter generator contactor is connected to the #2 transformer rectifier, terminal 2A is connected to the #2 AC starter generator, and terminal 2B is connected to the #1 AC busbar; the #2 transformer rectifier is connected to the #2 general busbar through the #2 transformer rectifier contactor. The common terminal of the #3 AC starter generator contactor is connected to the #3 transformer rectifier, terminal 3A is connected to the #3 AC starter generator, and terminal 3B is connected to the #2 AC busbar; the #3 transformer rectifier is connected to the #3 general busbar through the #3 transformer rectifier contactor. The APU AC generator contactor's common terminal connects to the emergency transformer rectifier, terminal 4A connects to the APU AC generator, and terminal 4B connects to the #2 AC busbar; the emergency transformer rectifier connects to the important busbars via the emergency transformer rectifier contactor.

2. The system according to claim 1, characterized in that: The #1 AC busbar is also connected to an external AC power source via an external AC power contactor.

3. The system according to claim 2, characterized in that: The #2 AC busbar is also connected to the APU AC generator via an AC contactor.

4. The system according to claim 3, characterized in that: AC busbar #1 and AC busbar #2 are interconnected via AC connecting contactors.

5. The system according to claim 4, characterized in that: General busbar #1 and general busbar #2 are interconnected via contactor #1; general busbar #2 and general busbar #3 are interconnected via contactor #2; and general busbar #3 and important busbar are interconnected via contactor #3.

6. The system according to claim 5, characterized in that: The power diode is connected in parallel with contactor #3. The anode of the power diode is connected to the general busbar #3, and the cathode is connected to the important busbar.

7. The system according to claim 6, characterized in that: The important busbars are connected to the battery via battery contactors.

8. The system according to claim 7, characterized in that: The #3 busbar is generally connected to the external DC power supply via a DC external power contactor.

9. An aircraft, characterized in that: The aircraft includes the system according to any one of claims 1-8.

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