Power supply circuit of airplane, airplane distribution box and airplane

Abstract

The utility model provides a power supply circuit of an airplane, an airplane distribution box and the airplane. The power supply circuit comprises a generator control circuit, a generator, a storage battery circuit, a main switch circuit, a storage battery switch circuit, a generator switch, a mode change-over switch, a first relay switch, a second relay switch, a third relay switch, a central bus bar and an emergency bus bar, through cooperative arrangement of a main switch circuit, a storage battery switch circuit, a generator switch, a mode change-over switch, a first relay switch, a second relay switch and a third relay switch, when a second switch path of the mode change-over switch is switched on, only the storage battery circuit supplies power to an emergency bus bar initially, and after a generator is started, the emergency bus bar is switched on. And the generator is automatically changed to supply power to the central bus bar and the emergency bus bar and charge the storage battery at the same time. According to the utility model, the power supply can be automatically switched in the flight process, and the power supply loss of the storage battery in normal use is reduced.

Description

Technical Field

[0001] The utility model relates to the technical field of power supply of aircraft, in particular to a power supply circuit of an aircraft, an aircraft power distribution box using the power supply circuit, and an aircraft using the aircraft power distribution box. Background Art

[0002] The power distribution boxes currently used on normal aircraft have a single function and are difficult to switch power supply modes during flight. Batteries are also used as a power source for emergency loads under normal circumstances, which will affect their power supply capabilities in emergency situations.

[0003] Therefore, it is necessary to consider a more optimized power supply structure to reduce the power loss of the battery during normal use. Utility Model Content

[0004] The first purpose of the utility model is to provide a power supply circuit for an aircraft which can realize automatic switching of power supply during flight and reduce power loss of a battery during normal use.

[0005] The second purpose of the utility model is to provide an aircraft power distribution box which can realize automatic switching of power supply during flight and reduce the power loss of the battery during normal use.

[0006] The third object of the utility model is to provide an aircraft which can realize automatic switching of power supply during flight and reduce power loss of the battery during normal use.

[0007] In order to achieve the above-mentioned first purpose, the power supply circuit of the aircraft provided by the utility model includes a generator control circuit, a generator, a battery circuit, a main switch circuit, a battery switch circuit, a generator switch, a mode switching switch, a first relay switch, a second relay switch, a third relay switch, a central bus and an emergency bus. The generator control circuit is electrically connected to the control end of the generator, the output end of the generator is electrically connected to the central bus through the main switch circuit, and the branch between the output end of the generator and the main switch circuit is electrically connected to the enable end of the generator control circuit through the switch path of the first relay switch; the first end of the generator switch is electrically connected to the emergency bus, and the second end of the generator switch is grounded through the electromagnetic path of the first relay switch; the output end of the battery circuit is electrically connected to the emergency bus through the battery switch circuit; the central bus is electrically connected to the emergency bus through the switch path of the second relay switch; the first electromagnetic end of the second relay switch is electrically connected to the common end of the mode switching switch, the first switch path of the mode switching switch is grounded, and the second switch path of the mode switching switch is grounded through the first switch path of the third relay switch; the first electromagnetic end of the third relay switch is electrically connected to the emergency bus, and the second electromagnetic end of the third relay switch is electrically connected to the generator control circuit.

[0008] It can be seen from the above scheme that the power supply circuit of the aircraft of the utility model can make the mode switch in the "automatic" position through the coordinated setting of the main switch circuit, the battery switch circuit, the generator switch, the mode switch, the first relay switch, the second relay switch, and the third relay switch, that is, when the second switch path of the mode switch is turned on, initially only the battery circuit supplies power to the emergency bus, and after the generator is started, it automatically changes to the generator supplying power to the central bus and the emergency bus, and charging the battery at the same time; when the generator fails, it automatically changes to the battery supplying power to the emergency bus. In this way, it can realize the automatic switching of power supply during flight and reduce the power loss of the battery during normal use.

[0009] In a further scheme, the main switch circuit includes a first switch and a fourth relay switch, the first electromagnetic end of the fourth relay switch is electrically connected to the central bus, and the second electromagnetic end of the fourth relay switch is grounded through the first switch; the output end of the generator is electrically connected to the central bus through the switch path of the fourth relay switch.

[0010] It can be seen from this that the main switch circuit can achieve dual switch control and improve the safety of switch control by setting the first switch to control the on and off of the fourth relay switch.

[0011] In a further embodiment, the power supply terminal of the generator control circuit is electrically connected to the emergency bus bar.

[0012] It can be seen that the power supply end of the generator control circuit is electrically connected to the emergency bus bar, so that the generator control circuit can obtain power when it is powered by a battery or a generator.

[0013] In a further scheme, the power supply circuit also includes a fifth relay switch and a power supply detection terminal, the first electromagnetic end of the fifth relay switch is electrically connected to the emergency bus, the second electromagnetic end of the fifth relay switch is electrically connected to the generator control circuit, and the power supply detection terminal is electrically connected to the emergency bus through the switch path of the fifth relay switch.

[0014] It can be seen that by providing the fifth relay switch and the power supply detection terminal, a control signal can be sent to the fifth relay switch when the generator control circuit obtains power and works, thereby connecting the circuit of the power supply detection terminal to provide power supply indication.

[0015] In a further scheme, the battery switch circuit includes a second switch and a sixth relay switch, the first electromagnetic end of the sixth relay switch is electrically connected to the output end of the battery circuit, and the second electromagnetic end of the sixth relay switch is grounded through the second switch; the output end of the battery circuit is electrically connected to the emergency bus through the switch path of the sixth relay switch.

[0016] It can be seen that the battery switch circuit can achieve dual switch control and improve the safety of switch control by setting the second switch to control the on and off of the sixth relay switch.

[0017] In a further solution, the power supply circuit also includes a generator starting circuit power supply end, which is electrically connected to the switch path of the sixth relay switch and the branch between the emergency bus bar.

[0018] It can be seen from this that when the battery circuit is powered, power can be provided to the generator starting circuit through the generator starting circuit power supply end to start the generator to work.

[0019] In order to achieve the above second purpose, the aircraft power distribution box provided by the utility model is provided with a power supply circuit, and the power supply circuit adopts the above power supply circuit.

[0020] In order to achieve the third objective, the aircraft provided by the utility model is provided with an aircraft power distribution box, and the aircraft power distribution box adopts the above-mentioned aircraft power distribution box. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 The utility model is a circuit principle diagram of an embodiment of a power supply circuit of an aircraft.

[0022] The present invention will be further described below with reference to the accompanying drawings and embodiments. DETAILED DESCRIPTION

[0023] Example of power supply circuit for aircraft:

[0024] In this embodiment, Figure 1 As shown, the power supply circuit of the aircraft includes a generator control circuit 1, a generator 2, a battery circuit 3, a main switch circuit 4, a battery switch circuit 5, a generator switch 6, a mode switching switch 7, a first relay switch 8, a second relay switch 9, a third relay switch 10, a central bus 11 and an emergency bus 12. The central bus 11 is used to supply power to circuit components when the normal generator 2 is working normally, and the emergency bus 12 is used to supply power to circuit components that need emergency work.

[0025] The generator control circuit 1 is electrically connected to the control end of the generator 2, the output end of the generator 2 is electrically connected to the central bus 11 through the main switch circuit 4, and the branch between the output end of the generator 2 and the main switch circuit 4 is electrically connected to the enable end of the generator control circuit 1 through the switch path of the first relay switch 8.

[0026] In this embodiment, the main switch circuit 4 includes a first switch 41 and a fourth relay switch 42, the first electromagnetic end of the fourth relay switch 42 is electrically connected to the central bus 11, and the second electromagnetic end of the fourth relay switch 42 is grounded through the first switch 41. The output end of the generator 2 is electrically connected to the central bus 11 through the switch path of the fourth relay switch 42. The main switch circuit 4 controls the on and off of the fourth relay switch 42 by setting the first switch 41, so as to realize double switch control and improve the safety of switch control.

[0027] The first end of the generator switch 6 is electrically connected to the emergency bus 12 through the instrument panel emergency bus 13, and the second end of the generator switch 6 is grounded through the electromagnetic path of the first relay switch 8. In this embodiment, the power supply circuit also includes the instrument panel emergency bus 13, the instrument panel emergency bus 13 is electrically connected to the emergency bus 12, and the first end of the generator switch 6 is electrically connected to the emergency bus 12 through the instrument panel emergency bus 13. The instrument panel emergency bus 13 is used to provide emergency power supply to aircraft instruments.

[0028] In this embodiment, the power supply end of the generator control circuit 1 is electrically connected to the emergency bus 12. The power supply end of the generator control circuit 1 is electrically connected to the emergency bus 12, so that the generator control circuit 1 can obtain power when using the battery or the generator 2 for power supply.

[0029] The power supply circuit also includes a fifth relay switch 14 and a power supply detection terminal 15. The first electromagnetic end of the fifth relay switch 14 is electrically connected to the emergency bus 12, the second electromagnetic end of the fifth relay switch 14 is electrically connected to the generator control circuit 1, and the power supply detection terminal 15 is electrically connected to the emergency bus 12 through the switch path of the fifth relay switch 14. By providing the fifth relay switch 14 and the power supply detection terminal 15, a control signal can be sent to the fifth relay switch 14 when the generator control circuit 1 obtains power to work, thereby conducting the circuit of the power supply detection terminal 15 for power supply indication.

[0030] In this embodiment, the output end of the battery circuit 3 is electrically connected to the emergency bus 12 through the battery switch circuit 5. In this embodiment, the battery switch circuit 5 includes a second switch 51 and a sixth relay switch 52, the first electromagnetic end of the sixth relay switch 52 is electrically connected to the output end of the battery circuit 3, and the second electromagnetic end of the sixth relay switch 52 is grounded through the second switch 51. The output end of the battery circuit 3 is electrically connected to the emergency bus 12 through the switch path of the sixth relay switch 52. The battery switch circuit 5 controls the conduction and closing of the sixth relay switch 52 by setting the second switch 51, so as to realize double switch control and improve the safety of switch control.

[0031] In this embodiment, for the convenience of control, the second switch 51 and the generator switch 6 are integrated with a double-pole double-throw switch, which can realize simultaneous control of the second switch 51 and the generator switch 6.

[0032] In this embodiment, the central bus 11 is electrically connected to the emergency bus 12 through the switch path of the second relay switch 9. The first electromagnetic end of the second relay switch 9 is electrically connected to the common end of the mode switching switch 7, the first switch path of the mode switching switch 7 is grounded, and the second switch path of the mode switching switch 7 is grounded through the first switch path of the third relay switch 10. The first electromagnetic end of the third relay switch 10 is electrically connected to the emergency bus 12, and the second electromagnetic end of the third relay switch 10 is electrically connected to the generator control circuit 1. The first end of the second switch path of the third relay switch 10 is electrically connected to the emergency bus 12, and the second end of the second switch path of the third relay switch 10 is electrically connected to the indication detection terminal 101. Through the indication detection terminal 101, the on or off state of the first switch path of the third relay switch 10 can be indicated by light so that the user can know.

[0033] In addition, the power supply circuit also includes a generator starting circuit power supply terminal 16, which is electrically connected to a branch between the switch path of the sixth relay switch 52 and the emergency bus 12. When the battery circuit 3 supplies power, the generator starting circuit power supply terminal 16 can provide power to the generator 2 starting circuit, so as to start the generator 2 to work.

[0034] In this embodiment, when the power supply circuit of the aircraft is working, the main switch circuit 4, the battery switch circuit 5, and the generator switch 6 are closed in sequence, and then the working mode is selected through the mode switch 7. When the mode switch 7 is in the "neutral" position, that is, the mode switch 7 is not connected to the first switch path and is not connected to the second switch path, the switch path of the second relay switch 9 is connected to the central bus 11 and the emergency bus 12, and the battery circuit 3 supplies power to the central bus 11 and the emergency bus 12 at the same time. When the mode switch 7 is in the "automatic" position, that is, the mode switch 7 is connected to the second switch path, the battery circuit 3 supplies power to the emergency bus 12. At this time, the generator control circuit 1 controls the third relay switch 10 to turn on the first switch path of the third relay switch 10, so that the second relay switch 9 disconnects the central bus 11 and the emergency bus 12. The battery circuit 3 only supplies power to the emergency bus 12 to save power. At the same time, the first relay switch 8 connects the output end of the generator 2 with the enable end of the generator control circuit 1; after the generator 2 is started, when the enable end of the generator control circuit 1 detects the power supply voltage at the output end of the generator 2 ... The three relay switches 10 disconnect the first switch path of the third relay switch 10, so that the second relay switch 9 conducts the central bus 11 and the emergency bus 12, and realizes the automatic change to the generator 2 supplying power to the central bus 11 and the emergency bus 12, and charges the battery in the battery circuit 3 at the same time; when the generator 2 fails, the enable end of the generator control circuit 1 detects that the power supply voltage at the output end of the generator 2 is abnormal, and the generator control circuit 1 controls the third relay switch 10 to conduct the first switch path of the third relay switch 10, so that the second relay switch 9 disconnects the central bus 11 and the emergency bus 12, and automatically changes to the battery circuit 3 supplying power to the emergency bus 12. When the mode switch 7 is in the "manual" position, that is, the mode switch 7 connects the first switch path, the second relay switch 9 disconnects the central bus 11 and the emergency bus 12, the battery circuit 3 only supplies power to the emergency bus 12, and the generator 2 only supplies power to the central bus 11.

[0035] As can be seen from the above, the power supply circuit of the aircraft of the utility model can be configured through the coordination of the main switch circuit 4, the battery switch circuit 5, the generator switch 6, the mode switch 7, the first relay switch 8, the second relay switch 9, and the third relay switch 10, so that when the mode switch 7 is in the "automatic" position, that is, when the second switch path of the mode switch is turned on, initially only the battery circuit 3 supplies power to the emergency bus 12, and after the generator 2 is started, it automatically changes to the generator 2 supplying power to the central bus 11 and the emergency bus 12, and charging the battery at the same time; when the generator 2 fails, it automatically changes to the battery supplying power to the emergency bus 12. In this way, it can realize automatic switching of power supply during flight and reduce the power loss of the battery during normal use.

[0036] Aircraft power distribution box embodiment:

[0037] The aircraft power distribution box is used to supply power to the circuit system of the aircraft. In this embodiment, the aircraft power distribution box is provided with a power supply circuit, and the power supply circuit adopts the power supply circuit in the above embodiment.

[0038] Aircraft Example:

[0039] In this embodiment, the aircraft is provided with an aircraft power distribution box, and the aircraft power distribution box adopts the aircraft power distribution box of the above embodiment.

[0040] It should be noted that the above are only preferred embodiments of the present invention, but the design concept of the present invention is not limited thereto, and any non-substantial modifications made to the present invention using this concept also fall within the protection scope of the present invention.

Claims

1. A power supply circuit for an aircraft, comprising a generator control circuit, a generator, a battery circuit, a main switch circuit, a battery switch circuit, a generator switch, a central bus bar and an emergency bus bar, characterized in that: The power supply circuit also includes a mode switching switch, a first relay switch, a second relay switch and a third relay switch; The generator control circuit is electrically connected to the control end of the generator, the output end of the generator is electrically connected to the central bus bar through the main switch circuit, and the branch between the output end of the generator and the main switch circuit is electrically connected to the enable end of the generator control circuit through the switch path of the first relay switch; A first end of the generator switch is electrically connected to the emergency bus bar, and a second end of the generator switch is grounded through an electromagnetic path of the first relay switch; The output end of the battery circuit is electrically connected to the emergency bus bar through a battery switch circuit; The central bus bar is electrically connected to the emergency bus bar through the switch path of the second relay switch; The first electromagnetic end of the second relay switch is electrically connected to the common end of the mode switch, the first switch path of the mode switch is grounded, and the second switch path of the mode switch is grounded through the first switch path of the third relay switch; The first electromagnetic end of the third relay switch is electrically connected to the emergency bus bar, and the second electromagnetic end of the third relay switch is electrically connected to the generator control circuit.

2. The aircraft power supply circuit according to claim 1, characterized in that: The main switch circuit comprises a first switch and a fourth relay switch, wherein a first electromagnetic end of the fourth relay switch is electrically connected to the central bus bar, and a second electromagnetic end of the fourth relay switch is grounded through the first switch; The output end of the generator is electrically connected to the central bus bar through a switch path of the fourth relay switch.

3. The aircraft power supply circuit according to claim 1, characterized in that: The power supply end of the generator control circuit is electrically connected to the emergency bus bar.

4. The aircraft power supply circuit according to claim 3, characterized in that: The power supply circuit also includes a fifth relay switch and a power supply detection terminal, the first electromagnetic end of the fifth relay switch is electrically connected to the emergency bus, the second electromagnetic end of the fifth relay switch is electrically connected to the generator control circuit, and the power supply detection terminal is electrically connected to the emergency bus through the switch path of the fifth relay switch.

5. The power supply circuit of an aircraft according to any one of claims 1 to 4, characterized in that: The battery switch circuit comprises a second switch and a sixth relay switch, wherein a first electromagnetic end of the sixth relay switch is electrically connected to an output end of the battery circuit, and a second electromagnetic end of the sixth relay switch is grounded through the second switch; The output end of the battery circuit is electrically connected to the emergency bus bar through a switch path of the sixth relay switch.

6. The aircraft power supply circuit according to claim 5, characterized in that: The power supply circuit also includes a generator starting circuit power supply terminal, and the generator starting circuit power supply terminal is electrically connected to the switch path of the sixth relay switch and the branch between the emergency bus bar.

7. An aircraft power distribution box, provided with a power supply circuit, characterized in that: The power supply circuit adopts the power supply circuit according to any one of claims 1 to 6.

8. An aircraft, provided with an aircraft power distribution box, characterized in that: The aircraft power distribution box adopts the aircraft power distribution box according to claim 7.

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