Aircraft power supply switching device and method

Abstract

The invention relates to the technical field of power supply switching, in particular to an aircraft power supply switching device and method. The aircraft power supply switching device comprises a comparison module, a first control module, a second control module and a comparison module, the non-inverting input end of the comparison module is connected with a first power supply, the inverting input end of the comparison module is connected with a second power supply, and the output end of the comparison module is used for outputting a control signal; the first control module is connected with the output end of the comparison module; the second control module is connected with the output end of the comparison module; the comparison module is used for controlling the output of the first control module and the second control module according to the control signal so as to control one of the first power supply and the second power supply as an aircraft power supply; the input end of the load is connected with the output ends of the first control module and the second control module. According to the aircraft power supply switching device and method, automatic switching of the power supply can be realized, the control performance is reliable, the control logic is simple, and the electric energy loss is less.

Description

Technical Field

[0001] The present invention relates to the technical field of power switching, and in particular to an aircraft power switching device and method. Background Art

[0002] The power supply of an aircraft is usually divided into an external power supply and an internal power supply. The external power supply is mainly used for debugging during the aircraft development stage and pre-aircraft testing. The internal power supply starts working before the aircraft takes off and ensures the power required for the aircraft after takeoff. Therefore, reliable control logic is required to ensure the flight process and reduce unnecessary internal power consumption to ensure the flight safety and flight distance of the aircraft.

[0003] The existing aircraft power supply switching method has complex control logic and cumbersome procedures, and cannot solve the situation where both external power supply and internal power supply exist at the same time. Dual-path Schottky diodes are usually used to solve this problem. However, due to the high power consumption of the aircraft, the dual-path Schottky diodes will consume more power, affecting the performance of the battery, resulting in the aircraft's flight distance being limited. Therefore, there is an urgent need to provide an aircraft power supply switching device and method with reliable control performance, simple control logic, and less power loss. Summary of the invention

[0004] In view of the above-mentioned shortcomings of the prior art, an object of the present invention is to provide an aircraft power switching device and method, which realizes automatic switching of power supply, and has reliable control performance, simple control logic and less power loss.

[0005] To achieve the above objectives and other related objectives, the present invention provides an aircraft power switching device, comprising:

[0006] A comparison module, wherein a non-phase input terminal of the comparison module is connected to a first power supply, an inverting input terminal of the comparison module is connected to a second power supply, and an output terminal of the comparison module is used to output a control signal;

[0007] A first control module connected to the output end of the comparison module;

[0008] A second control module connected to the output end of the comparison module;

[0009] The comparison module is used to control the outputs of the first control module and the second control module according to the control signal, so as to control one of the first power supply and the second power supply to serve as the aircraft power supply;

[0010] A load, whose input end is connected to the output ends of the first control module and the second control module.

[0011] In one embodiment of the present invention, it further includes:

[0012] A DC-DC power supply module, whose output end is connected to the comparison module, and whose input end is connected to the output ends of the first control module and the second control module.

[0013] In one embodiment of the present invention, the comparison module includes:

[0014] A voltage comparator, wherein a positive input terminal thereof is connected to a first power supply, and an inverting input terminal thereof is connected to a second power supply;

[0015] A first resistor, one end of which is connected to a first power supply, and the other end of the first resistor is connected to an inverting input end of the voltage comparator;

[0016] A second resistor, one end of which is connected to the inverting input terminal of the voltage comparator, and the other end of the second resistor is grounded;

[0017] A third resistor, one end of which is connected to the second power supply, and the other end of the third resistor is connected to the non-inverting input end of the voltage comparator;

[0018] A fourth resistor has one end connected to the non-inverting input terminal of the voltage comparator, and the other end of the fourth resistor is grounded.

[0019] In one embodiment of the present invention, the DC-DC power supply module comprises:

[0020] A DC-DC power conversion chip, whose output end is connected to the input end of the comparison module;

[0021] A first capacitor connected between a power input pin and a ground pin of the DC-DC power conversion chip;

[0022] The second capacitor is connected between the power output pin and the ground pin of the DC-DC power conversion chip.

[0023] In one embodiment of the present invention, the first control module includes:

[0024] A first photoelectric coupler, a first end of which is connected to the output end of the voltage comparator, and a second end of which is grounded;

[0025] A first P-channel field effect transistor, whose source is connected to the fourth end of the first photocoupler, whose gate is connected to the third end of the first photocoupler, and whose drain is used to output the first power supply.

[0026] In one embodiment of the present invention, the first control module further includes:

[0027] a fifth resistor, one end of which is connected to the output end of the voltage comparator, and the other end of which is connected to the first end of the first photoelectric coupler;

[0028] a sixth resistor, one end of which is grounded, and the other end of which is connected to the second end of the first photoelectric coupler;

[0029] a seventh resistor, one end of which is connected to the source of the first P-channel field effect transistor, and the other end of which is connected to the third end of the first photocoupler;

[0030] an eighth resistor, one end of which is connected to the third end of the first photoelectric coupler, and the other end of the eighth resistor is grounded;

[0031] A third capacitor, one end of which is connected to the fourth end of the first photoelectric coupler, and the other end of the third capacitor is grounded;

[0032] A fourth capacitor, one end of which is used to connect the drain of the first P-channel field effect transistor, and the other end of the fourth capacitor is grounded.

[0033] In one embodiment of the present invention, the second control module includes:

[0034] A second photoelectric coupler, a first end of which is connected to the output end of the DC-DC power supply module, and a second end of the second photoelectric coupler is connected to the output end of the voltage comparator;

[0035] A second P-channel field effect transistor, whose source is connected to the fourth end of the second photocoupler, whose gate is connected to the third end of the second photocoupler, and whose drain is used to output the second power supply.

[0036] In one embodiment of the present invention, the second control module further includes:

[0037] a ninth resistor, one end of which is connected to the output end of the DC-DC power supply module, and the other end of which is connected to the first end of the second photoelectric coupler;

[0038] a tenth resistor, one end of which is connected to the output end of the voltage comparator, and the other end of which is connected to the second end of the second photoelectric coupler;

[0039] an eleventh resistor, one end of which is connected to the source of the second P-channel field effect transistor, and the other end of the eleventh resistor is connected to the third end of the second photocoupler;

[0040] a twelfth resistor, one end of which is connected to the third end of the second photoelectric coupler, and the other end of the twelfth resistor is grounded;

[0041] a fifth capacitor, one end of which is connected to the fourth end of the second photoelectric coupler, and the other end of the fifth capacitor is grounded;

[0042] A sixth capacitor, one end of which is used to connect the drain of the second P-channel field effect transistor, and the other end of the sixth capacitor is grounded.

[0043] In one embodiment of the present invention, the model of the voltage comparator is AD8397ARDZ.

[0044] The present invention provides an aircraft power switching method, comprising:

[0045] Outputting a control signal via an output terminal of the comparison module;

[0046] According to the control signal, the outputs of the first control module and the second control module are controlled, thereby controlling one of the first power supply and the second power supply to serve as the aircraft power supply.

[0047] As described above, an aircraft power switching device and method of the present invention have the following beneficial effects:

[0048] (1) The aircraft power switching device and method of the present invention can realize automatic switching of power supply, and has reliable control performance, simple control logic and less power loss.

[0049] (2) The aircraft power switching device and method of the present invention solves the problem of power consumption by the Schottky diode when an external power supply and an internal power supply exist at the same time, and also avoids power switching anomalies caused by power switching circuit failure, so that the system can operate more reliably and stably.

[0050] (3) The aircraft power switching device and method of the present invention are more reliable and intelligent, and also solve the problem of two traditional power sources supplying power at the same time and the diode voltage drop consuming power. BRIEF DESCRIPTION OF THE DRAWINGS

[0051] Figure 1 A block diagram of the structural principles of an aircraft power switching device provided in an embodiment of the present application.

[0052] Figure 2 A circuit schematic diagram of an aircraft power switching device provided in an embodiment of the present application.

[0053] Figure 3 A flowchart of an aircraft power switching method provided in an embodiment of the present application.

[0054] Component number description:

[0055] 10-Comparison Module

[0056] 20-First power supply

[0057] 30- Second power supply

[0058] 40-First control module

[0059] 50- Second control module

[0060] 60-Load

[0061] 70-DC-DC Power Module DETAILED DESCRIPTION

[0062] The following describes the embodiments of the present invention by specific examples, and those skilled in the art can easily understand other advantages and effects of the present invention from the contents disclosed in this specification. The present invention can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present invention. It should be noted that the following embodiments and features in the embodiments can be combined with each other without conflict.

[0063] It should be noted that the illustrations provided in the following embodiments are only used to illustrate the basic concept of the present invention in a schematic manner, and thus the illustrations only show components related to the present invention rather than being drawn according to the number, shape and size of components in actual implementation. In actual implementation, the type, quantity and proportion of each component may be changed arbitrarily, and the component layout may also be more complicated.

[0064] Terms such as first or second can be used to describe various components, but these components are not limited by the above terms. The above terms are used to distinguish one component from another component, for example, without departing from the scope of the concept according to the present disclosure, a first component can be referred to as a second component, and similarly, a second component can be referred to as a first component.

[0065] In addition, "connected / coupled" means that one component is directly electrically coupled to another component or is indirectly electrically coupled through another component. The singular form may include the plural form unless explicitly stated in the sentence. In addition, "include / comprise" or "includes / comprises" used in this specification indicates that one or more components, steps, operations, and elements exist or have been added. The specific structural or functional descriptions of the examples of the implementation of the concepts disclosed in this specification are only illustrated to describe the examples of the implementation of the concepts, and the examples of the implementation of the concepts can be implemented in various forms, but these descriptions are not limited to the examples of the implementation described in this specification.

[0066] According to the concept, various modifications and changes can be applied to the examples of the embodiments, so that the examples of the embodiments will be illustrated in the drawings and described in the specification. However, the examples of the embodiments according to the concept are not limited to the specific embodiments, but include all changes, equivalents or replacements included in the spirit and technical scope of the present disclosure.

[0067] It should be understood that when an element is described as being "coupled" or "connected" to another element, the element may be directly coupled or directly connected to the other element, or may be coupled or connected to the other element through a third element. Conversely, it should be understood that when an element is referred to as being "directly coupled to" or "directly coupled to" another element, no other element is placed between them. Other expressions describing the relationship between components (i.e., "between" and "directly between" or "adjacent to" and "directly adjacent to") need to be interpreted in the same manner.

[0068] The terms used in this specification are only used to describe specific examples of the embodiments and are not intended to limit the present disclosure. If there is no clear opposite meaning in the context, the singular form may include the plural form. In this specification, it should be understood that the term "including" or "having" indicates the presence of the features, quantities, steps, operations, components, parts or combinations thereof described in the specification, but the possibility of the presence or addition of one or more other features, quantities, steps, operations, components, parts or combinations thereof cannot be precluded.

[0069] If there is no contrary definition, all terms (including technical terms or scientific terms) used herein have the same meaning as those generally understood by ordinary technicians in the field. If the terms defined in the commonly used dictionary are not clearly defined in this specification, they should be interpreted as having the same meaning as in the context of the relevant technology, and not interpreted as ideal or overly formal meanings.

[0070] Descriptions of well-known components and processing techniques may be omitted so as not to unnecessarily obscure the embodiments of the disclosure.

[0071] Throughout the specification, the same reference numerals refer to the same elements. Thus, even if a reference numeral is not mentioned or described with reference to one figure, it may be mentioned or described with reference to another figure. Furthermore, even if a reference numeral is not shown in one figure, it may be mentioned or described with reference to another figure.

[0072] In addition, the logic level of the signal may be different or opposite to the described logic level. For example, a signal described as having a logic "high" level may alternatively have a logic "low" level, and a signal described as having a logic "low" level may alternatively have a logic "high" level.

[0073] The following will describe the various embodiments of the present disclosure in detail with reference to the accompanying drawings. However, it will be appreciated by those skilled in the art that in the various embodiments of the present disclosure, many technical details are provided in order to enable the reader to better understand the present disclosure. However, even without these technical details and various changes and modifications based on the following embodiments, the technical solutions claimed in the present disclosure can be implemented.

[0074] See also Figure 1 , Figure 2 , Figure 1 A block diagram of the structural principles of an aircraft power switching device provided in an embodiment of the present application. Figure 2 A circuit schematic diagram of an aircraft power switching device provided in an embodiment of the present application. The present invention provides an aircraft power switching device, comprising a comparison module 10, a first power supply 20, a second power supply 30, a first control module 40, a second control module 50 and a load 60, wherein the positive input end of the comparison module 10 is connected to the first power supply 20, the negative input end of the comparison module 10 is connected to the second power supply 30, and the output end of the comparison module 10 is used to output a control signal; the first control module 40 is connected to the output end of the comparison module 10; the second control module 50 is connected to the output end of the comparison module 10; the comparison module 10 is used to control the output of the first control module 40 and the second control module 50 according to the control signal, so as to control one of the first power supply 20 and the second power supply 30 as the aircraft power supply; the input end of the load 60 is connected to the output end of the first control module 40 and the second control module 50.

[0075] An aircraft power switching device of the present invention can enable the aircraft to automatically switch the power supply, solving the problem of Schottky diode consuming electric energy when the external power supply and the internal power supply exist at the same time, and also avoiding power switching abnormalities caused by power switching circuit failure, so that the system can operate more reliably and stably.

[0076] In some embodiments of the present invention, the first power supply 20 refers to one of the external power supply of the aircraft or the internal power supply of the aircraft, and the second power supply 30 refers to the other of the external power supply of the aircraft or the internal power supply of the aircraft. Specifically, in this embodiment, the first power supply 20 refers to the external power supply of the aircraft, and the voltage value is rated at 28V; the second power supply 30 refers to the internal power supply of the aircraft, which is generally a thermal battery or a lithium battery, and the voltage value is 20V to 36V, and 28V is the actual power supply of the system.

[0077] In some embodiments of the present invention, the present invention provides an aircraft power switching device, further comprising: a DC-DC power supply module 70, whose output end is connected to the comparison module 10, and the input end of the DC-DC power supply module 70 is connected to the output ends of the first control module 40 and the second control module 50.

[0078] Specifically, the DC-DC power supply module 70 includes a DC-DC power supply conversion chip, a first capacitor C1, and a second capacitor C2, wherein the output end of the DC-DC power supply conversion chip is connected to the input end of the comparison module 10; the first capacitor C1 is connected between the power input pin and the ground pin of the DC-DC power supply conversion chip; and the second capacitor C2 is connected between the power output pin and the ground pin of the DC-DC power supply conversion chip.

[0079] Specifically, the model of the DC-DC power conversion chip is K7805MT-1000R4. The DC-DC power module 70 outputs a 5V voltage to power the comparator.

[0080] Specifically, the first capacitor C1 is a 10 uF capacitor, which plays an input filtering role for the entire DC-DC power supply module 70 .

[0081] Specifically, the second capacitor C2 is a 22uF capacitor, which plays an output filtering role for the entire DC-DC power supply module 70 .

[0082] In some embodiments of the present invention, the comparison module 10 includes a voltage comparator, a first resistor R1, a second resistor R2, a third resistor R3, and a fourth resistor R4, wherein the non-phase input terminal of the voltage comparator is connected to the first power supply 20, and the inverting input terminal is connected to the second power supply 30; one end of the first resistor R1 is connected to the first power supply 20, and the other end of the first resistor R1 is connected to the inverting input terminal of the voltage comparator; one end of the second resistor R2 is connected to the inverting input terminal of the voltage comparator, and the other end of the second resistor R2 is grounded; one end of the third resistor R3 is connected to the second power supply 30, and the other end of the third resistor R3 is connected to the non-phase input terminal of the voltage comparator; one end of the fourth resistor R4 is connected to the non-phase input terminal of the voltage comparator, and the other end of the fourth resistor R4 is grounded.

[0083] Specifically, the model of the voltage comparator is AD8397ARDZ. The voltage comparator is powered by 5V output by the DC-DC power supply module 70, the inverting input terminal is connected to the voltage at the second power supply 30, and the non-inverting input terminal is connected to the voltage at the first power supply 20. When the voltage at the first power supply 20 is greater than the voltage at the second power supply 30, the voltage comparator outputs a high level, otherwise the voltage comparator outputs a low level.

[0084] Specifically, the first resistor R1 is a 100KΩ resistor, and the second resistor R2 is a 10KΩ resistor. The first resistor R1 and the second resistor R2 are used to divide the voltage of the second power supply 30 .

[0085] Specifically, the third resistor R3 is a 100KΩ resistor, the fourth resistor R4 is a 15KΩ resistor, and the third resistor R3 and the fourth resistor R4 are used to divide the voltage of the first power supply 20 .

[0086] Specifically, the resistance values ​​of the first resistor R1 , the second resistor R2 , the third resistor R3 , and the fourth resistor R4 must be selected in accordance with the requirement that the voltage at the first power supply 20 is greater than the minimum voltage at the second power supply 30 .

[0087] In some embodiments of the present invention, the first control module 40 includes: a first photocoupler and a first P-channel field effect transistor, wherein the first end of the first photocoupler is connected to the output end of the voltage comparator, and the second end of the first photocoupler is grounded; the source of the first P-channel field effect transistor is connected to the fourth end of the first photocoupler, the gate of the first P-channel field effect transistor is connected to the third end of the first photocoupler, and the drain of the first P-channel field effect transistor is used to output the first power supply 20.

[0088] In some embodiments of the present invention, the first control module 40 also includes: a fifth resistor R5, a sixth resistor R6, a seventh resistor R7, an eighth resistor R8, a third capacitor C3, and a fourth capacitor C4, wherein one end of the fifth resistor R5 is connected to the output end of the voltage comparator, and the other end of the fifth resistor R5 is connected to the first end of the first photoelectric coupler; one end of the sixth resistor R6 is grounded, and the other end of the sixth resistor R6 is connected to the second end of the first photoelectric coupler; one end of the seventh resistor R7 is connected to the source of the first P-channel field effect transistor, and the other end of the seventh resistor R7 is connected to the third end of the first photoelectric coupler; one end of the eighth resistor R8 is connected to the third end of the first photoelectric coupler, and the other end of the eighth resistor R8 is grounded; one end of the third capacitor C3 is connected to the fourth end of the first photoelectric coupler, and the other end of the third capacitor C3 is grounded; one end of the fourth capacitor C4 is used to connect the drain of the first P-channel field effect transistor, and the other end of the fourth capacitor C4 is grounded.

[0089] Specifically, the model of the first photocoupler is TLP521-1.

[0090] Specifically, the fifth resistor R5 is a 270Ω resistor, and the sixth resistor R6 is a 100Ω resistor, which play a current limiting role.

[0091] Specifically, the model of the first P-channel field effect transistor is BUK6Y33-60P, and the seventh resistor R7 and the eighth resistor R8 are both 5.1KΩ resistors, and the purpose is to divide the voltage of the first power supply 20 .

[0092] Specifically, the third capacitor C3 is a 0.1uF capacitor, which plays a role of voltage stabilization, and the fourth capacitor C4 is a 10uF capacitor, which plays a role of output filtering.

[0093] In some embodiments of the present invention, the second control module 50 includes: a second photocoupler and a second P-channel field effect transistor, wherein the first end of the second photocoupler is connected to the output end of the DC-DC power supply module 70, and the second end of the second photocoupler is connected to the output end of the voltage comparator; the source of the second P-channel field effect transistor is connected to the fourth end of the second photocoupler, the gate of the second P-channel field effect transistor is connected to the third end of the second photocoupler, and the drain of the second P-channel field effect transistor is used to output the second power supply 30.

[0094] In some embodiments of the present invention, the second control module 50 further includes: a ninth resistor R9, a tenth resistor R10, an eleventh resistor R11, a twelfth resistor R12, a fifth capacitor C5, and a sixth capacitor C6, wherein one end of the ninth resistor R9 is connected to the output end of the DC-DC power supply module 70, and the other end of the ninth resistor R9 is connected to the first end of the second photoelectric coupler; one end of the tenth resistor R10 is connected to the output end of the voltage comparator, and the other end of the tenth resistor R10 is connected to the second end of the second photoelectric coupler; one end of the eleventh resistor R11 is connected to the source of the second P-channel field effect transistor, and the other end of the eleventh resistor R11 is connected to the third end of the second photoelectric coupler; one end of the twelfth resistor R12 is connected to the third end of the second photoelectric coupler, and the other end of the twelfth resistor R12 is grounded; one end of the fifth capacitor C5 is connected to the fourth end of the second photoelectric coupler, and the other end of the fifth capacitor C5 is grounded; one end of the sixth capacitor C6 is used to connect the drain of the second P-channel field effect transistor, and the other end of the sixth capacitor C6 is grounded.

[0095] Specifically, the model of the second photocoupler is TLP521-1.

[0096] Specifically, the ninth resistor R9 is a 270Ω resistor and the tenth resistor R10 is a 100Ω resistor, which play a role of current limiting.

[0097] Specifically, the model of the second P-channel field effect transistor is BUK6Y33-60P, the eleventh resistor R11 and the twelfth resistor R12 are both 5.1KΩ resistors, the purpose of which is to divide the second power supply 30, the fifth capacitor C5 is a 0.1uF capacitor, which plays a voltage stabilizing role, and the sixth capacitor C6 is a 10uF capacitor, which plays an output filtering role.

[0098] See also Figure 3 , Figure 3 The present invention is a flowchart of an aircraft power switching method provided in an embodiment of the present application. Similar to the principle of an aircraft power switching device of the present invention, the present invention also provides an aircraft power switching method, including:

[0099] Step S1 , outputting a control signal through the output terminal of the comparison module 10 .

[0100] Step S2: According to the control signal, control the output of the first control module 40 and the second control module 50, so as to control one of the first power supply 20 and the second power supply 30 to serve as the aircraft power supply.

[0101] Specifically, first, the first power supply 20 is powered on, the DC-DC power supply module 70 and the comparison module 10 do not work, the first photocoupler is not turned on, the VGS of the first P-channel field effect transistor is -14V, the first P-channel field effect transistor is turned on, and the output end of the first control module 40 outputs the first power supply 20. Then, the DC-DC power supply module 70 and the comparison module 10 work. Since the second power supply 30 is not powered on, the voltage at the first power supply 20 at the positive input end of the voltage comparator is greater than the voltage at the second power supply 30 at the inverting input end. The voltage comparator outputs a high level, the first photocoupler is turned on, the VGS of the first P-channel field effect transistor is 0V, the first P-channel field effect transistor is not turned on, and the first control module 40 has no output. When the second power supply 30 is powered on, the voltage at the first power supply 20 is lower than the voltage at the second power supply 30, the voltage comparator outputs a low level, the first photocoupler is not conducting, the VGS of the first P-channel field effect transistor is -14V, the first P-channel field effect transistor is conducting, and the first control module 40 outputs the first power supply 20. The second photocoupler is not conducting, the VGS of the first P-channel field effect transistor is -10V to -18V, the first P-channel field effect transistor is conducting, and the second control module 50 outputs the second power supply 30, thus realizing the switching of the power supply. When the second power supply 30 is powered off, it can be switched back to the first power supply 20.

[0102] In summary, the aircraft power switching device and method of the present invention can realize automatic switching of power supply, and has reliable control performance, simple control logic, and less power loss. The aircraft power switching device and method of the present invention solves the problem of Schottky diode consuming power when external power supply and internal power supply exist at the same time, and also avoids power switching abnormality caused by power switching circuit failure, so that the system can operate more reliably and stably.

[0103] The above embodiments are merely illustrative of the principles and effects of the present invention, and are not intended to limit the present invention. Anyone familiar with the art may modify or alter the above embodiments without departing from the spirit and scope of the present invention. Therefore, all equivalent modifications or alterations made by a person of ordinary skill in the art without departing from the spirit and technical concept disclosed by the present invention shall still be covered by the claims of the present invention.

Claims

1. An aircraft power switching device, characterized in that: include: A comparison module (10), wherein a non-phase input end of the comparison module (10) is connected to a first power supply (20), an inverting input end of the comparison module (10) is connected to a second power supply (30), and an output end of the comparison module (10) is used to output a control signal; A first control module (40) connected to the output end of the comparison module (10); A second control module (50) connected to the output end of the comparison module (10); The comparison module (10) is used to control the output of the first control module (40) and the second control module (50) according to the control signal, thereby controlling one of the first power supply (20) and the second power supply (30) to serve as the aircraft power supply; A load (60) having an input end connected to the output ends of the first control module (40) and the second control module (50).

2. An aircraft power switching device according to claim 1, characterized in that: Also includes: A DC-DC power supply module (70), whose output end is connected to the comparison module (10), and whose input end is connected to the output ends of the first control module (40) and the second control module (50).

3. The aircraft power switching device according to claim 1, characterized in that: The comparison module (10) comprises: A voltage comparator, wherein a positive input terminal is connected to a first power supply (20), and an inverting input terminal is connected to a second power supply (30); A first resistor (R1), one end of which is connected to a first power supply (20), and the other end of which is connected to an inverting input end of the voltage comparator; a second resistor (R2), one end of which is connected to the inverting input terminal of the voltage comparator, and the other end of the second resistor (R2) is grounded; A third resistor (R3), one end of which is connected to the second power supply (30), and the other end of the third resistor (R3) is connected to the non-inverting input end of the voltage comparator; A fourth resistor (R4) has one end connected to the non-inverting input end of the voltage comparator, and the other end of the fourth resistor (R4) is grounded.

4. The aircraft power switching device according to claim 2, characterized in that: The DC-DC power supply module (70) comprises: A DC-DC power conversion chip, the output end of which is connected to the input end of the comparison module (10); A first capacitor (C1), connected between a power input pin and a ground pin of the DC-DC power conversion chip; The second capacitor (C2) is connected between the power output pin and the ground pin of the DC-DC power conversion chip.

5. The aircraft power switching device according to claim 3, characterized in that: The first control module (40) comprises: A first photoelectric coupler, a first end of which is connected to the output end of the voltage comparator, and a second end of which is grounded; A first P-channel field effect transistor, whose source is connected to the fourth end of the first photoelectric coupler, whose gate is connected to the third end of the first photoelectric coupler, and whose drain is used to output the first power supply (20).

6. The aircraft power switching device according to claim 5, characterized in that: The first control module (40) further comprises: a fifth resistor (R5), one end of which is connected to the output end of the voltage comparator, and the other end of the fifth resistor (R5) is connected to the first end of the first photoelectric coupler; a sixth resistor (R6), one end of which is grounded, and the other end of which is connected to the second end of the first photoelectric coupler; a seventh resistor (R7), one end of which is connected to the source of the first P-channel field effect transistor, and the other end of the seventh resistor (R7) is connected to the third end of the first photocoupler; an eighth resistor (R8), one end of which is connected to the third end of the first photoelectric coupler, and the other end of the eighth resistor (R8) is grounded; a third capacitor (C3), one end of which is connected to the fourth end of the first photoelectric coupler, and the other end of the third capacitor (C3) is grounded; A fourth capacitor (C4), one end of which is used to connect the drain of the first P-channel field effect transistor, and the other end of the fourth capacitor (C4) is grounded.

7. The aircraft power switching device according to claim 3, characterized in that: The second control module (50) comprises: A second photoelectric coupler, a first end of which is connected to the output end of the DC-DC power supply module (70), and a second end of the second photoelectric coupler is connected to the output end of the voltage comparator; A second P-channel field effect transistor, whose source is connected to the fourth end of the second photoelectric coupler, whose gate is connected to the third end of the second photoelectric coupler, and whose drain is used to output the second power supply (30).

8. The aircraft power switching device according to claim 7, characterized in that: The second control module (50) further comprises: a ninth resistor (R9), one end of which is connected to the output end of the DC-DC power supply module (70), and the other end of the ninth resistor (R9) is connected to the first end of the second photoelectric coupler; a tenth resistor (R10), one end of which is connected to the output end of the voltage comparator, and the other end of the tenth resistor (R10) is connected to the second end of the second photoelectric coupler; an eleventh resistor (R11), one end of which is connected to the source of the second P-channel field effect transistor, and the other end of the eleventh resistor (R11) is connected to the third end of the second photocoupler; a twelfth resistor (R12), one end of which is connected to the third end of the second photoelectric coupler, and the other end of the twelfth resistor (R12) is grounded; a fifth capacitor (C5), one end of which is connected to the fourth end of the second photoelectric coupler, and the other end of the fifth capacitor (C5) is grounded; A sixth capacitor (C6), one end of which is used to connect the drain of the second P-channel field effect transistor, and the other end of the sixth capacitor (C6) is grounded.

9. The aircraft power switching device according to claim 3, characterized in that: The model of the voltage comparator is AD8397ARDZ.

10. A method for switching power supply of an aircraft, characterized in that: include: Outputting a control signal through an output terminal of a comparison module (10); According to the control signal, the outputs of the first control module (40) and the second control module (50) are controlled, thereby controlling one of the first power supply (20) and the second power supply (30) to serve as the aircraft power supply.

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