Detection system and detection method for power supply of airplane direct-current power supply system

Abstract

The invention discloses a detection system and a detection method for power supply of an airplane direct-current power supply system. A detection test bed in the detection system is connected with a ground direct-current power supply through a direct-current input port, and is correspondingly connected with four airborne power supply feeder ports in the airplane direct-current power supply system through four direct-current power supply output ports; the positive end of the direct-current input port passes through the direct-current positive bus bar and then is divided into four paths, and the four paths are correspondingly connected to the positive ends of the four direct-current power supply output ports through direct-current contactors respectively to form a positive direct-current power supply circuit; the negative end of the direct-current input port is connected with the negative end of one direct-current power supply output port through a direct-current negative bus bar to form a negative direct-current power supply circuit; and the positive and negative direct-current power supply circuits form a direct-current power supply circuit. According to the invention, the functions of short-circuit prevention protection of first power supply of an aircraft direct-current power supply system, quick power failure in emergency, automatic positive and negative polarity conversion of power supply of left and right storage batteries and a ground direct-current power supply, positive and negative polarity power supply linkage, input and output display and the like are realized.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aircraft assembly, in particular to a detection system and a detection method for aircraft DC power supply system power supply. BACKGROUND

[0002] The first power supply of the aircraft DC power supply system is an important node of the aircraft assembly, and the qualified detection of the power supply of the aircraft DC power supply system is a prerequisite for the debugging of the airborne equipment. Because the left storage battery, the right storage battery and the auxiliary DC generator do not have working conditions at the assembly stage, the ground DC power supply is needed to simulate the working of them to supply power to the aircraft DC power supply system, and to detect the functions of the aircraft DC power supply system.

[0003] The traditional detection method is to use one ground DC power supply to simulate the power supply of the left storage battery, the right storage battery, the auxiliary DC generator and the ground DC power supply socket respectively. The number of ground DC power supplies required in the test is the same as the number of power supply ports of the aircraft DC power supply system, the equipment utilization is low, the cost is high, and the economy is poor. In addition, in the above-mentioned traditional detection method, because each port of the aircraft DC power supply system is supplied by multiple ground DC power supplies, when an emergency danger occurs, it is impossible to quickly disconnect all the ground DC power supplies supplying power to the aircraft DC power supply system at the same time. SUMMARY

[0004] The purpose of the present application is to provide a detection system and a detection method for the power supply of the aircraft DC power supply system, to solve the problems of low equipment utilization, high cost and poor economy of the existing detection method for the first power supply of the aircraft DC power supply system, and to solve the safety hazard that it is difficult to quickly disconnect all the ground DC power supplies supplying power to the aircraft DC power supply system at the same time in dangerous situations.

[0005] The technical solution of the present application is: in the first aspect, the present application provides a detection system for the power supply of the aircraft DC power supply system, the power supply forms of the four airborne power sources in the aircraft DC power supply system are: the left storage battery 3 and the right storage battery 4 on board provide emergency DC power supply, the auxiliary DC generator 5 on board provides auxiliary DC power supply, and the ground DC power supply socket 6 provides ground maintenance power supply, characterized in that the detection system for the first power supply of the aircraft DC power supply system comprises: a ground DC power supply 1 and a detection test bench 2; the ground DC power supply 1 is electrically connected with the four airborne power source feeder ports in the aircraft DC power supply system through the detection test bench 2 to provide detection power supply for the aircraft DC power supply system; The detection test bench 2 is connected with the ground DC power supply 1 through the DC input port 7 arranged on one side thereof, and is connected with the four airborne power source feeder ports in the aircraft DC power supply system through the four DC power supply output ports arranged on the other side thereof; The positive end of the direct current input port 7 is divided into four paths through the direct current positive bus bar 10, and the four paths are connected to the positive ends of the four direct current power output ports through a direct current contactor, respectively, to form a positive direct current power circuit. The negative end of the direct current input port 7 is connected to the negative end of one of the direct current power output ports through the direct current negative bus bar 26, to form a negative direct current power circuit. The direct current power circuit formed by the positive direct current power circuit and the negative direct current power circuit is used for positive polarity power supply to four airborne power supplies in the aircraft direct current power supply system.

[0006] Optionally, in the detection system for the power supply of the aircraft direct current power supply system as described above, the four direct current power output ports are respectively: a first direct current positive output port 12, a second direct current positive output port 16, a third direct current positive output port 20, and a fourth direct current positive and negative output port 22. The positive end of the direct current input port 7 is connected to the direct current positive bus bar 10 through the rated fuse 8, the shunt 51 of the direct current input ammeter, the positive rated contactor 9, or the positive anti-short circuit contactor 14, and is connected to the first direct current positive output port 12 through the first direct current contactor 11, the second direct current positive output port 16 through the second direct current contactor 15, the third direct current positive output port 20 through the third direct current contactor 19, and the positive end of the fourth direct current positive and negative output port 22 through the fourth direct current contactor 21, to form a positive direct current power circuit. The negative end of the direct current input port 7 is connected to the direct current negative bus bar 26 through the negative rated contactor 23 or the negative anti-short circuit contactor 24, and is connected to the negative end of the fourth direct current positive and negative output port 22, to form a negative direct current power circuit.

[0007] Optionally, in the detection system for the power supply of the aircraft direct current power supply system as described above, the detection system further comprises: a reverse polarity control circuit, which comprises: a direct current control power circuit breaker 38, an emergency power-off switch 39, and a reverse polarity control relay 18 connected in series in turn at the rear end of the rated fuse 8, and four direct current contactor control switches for one-to-one control of the on-off states of the four direct current contactors. Among the four paths at the rear end of the 2-way normally closed contact of the reverse polarity control relay 18, the first path controls the on-off state of the first direct current contactor 11 through the first direct current contactor control switch 34, the second path controls the on-off state of the second direct current contactor 15 through the second direct current contactor control switch 35, the third path controls the on-off state of the third direct current contactor 19 through the third direct current contactor control switch 36, and the fourth path controls the on-off state of the fourth direct current contactor 21 through the fourth direct current contactor control switch 37. The reverse polarity control circuit in series with the reverse polarity control relay 18, for when the reverse polarity power supply is carried out, the reverse polarity control relay 18 is turned on, and the 2-way normally closed contact is opened, to cut off the power supply of the positive end of the DC control power supply in front of the four-way DC contactor control switch, so as to ensure that the four-way DC contactor will not work all the time, that is, to block the positive polarity DC power supply to the positive end of the four DC power output ports.

[0008] Optionally, as described above, in the detection system for the power supply of the aircraft DC power supply system, in the DC power supply circuit, the front end of the DC positive bus bar 10 and the DC negative bus bar 26 is provided with a current conversion circuit, the conversion of the current conversion circuit is controlled by the DC control power supply circuit breaker 38, the emergency power-off switch 39, the 1-way normally closed contact of the reverse polarity control relay 18 and the current conversion switch 29, the current conversion circuit includes four parallel current paths, which are: The first current path connects the positive end of the DC input port 7 to the DC positive bus bar 10 through the rated fuse 8, the shunt of the DC input current meter 51 and the positive rated contactor 9, the second current path connects the negative end of the DC input port 7 to the DC negative bus bar 26 through the negative rated contactor 23, and the first current path and the second current path form a positive polarity rated power supply circuit; The third current path connects the positive end of the DC input port 7 to the DC positive bus bar 10 through the rated fuse 8, the shunt of the DC input current meter 51, the short-circuit protection circuit breaker 13 and the positive short-circuit protection contactor 14, and the fourth current path connects the negative end of the DC input port 7 to the DC negative bus bar 26 through the negative short-circuit protection contactor 24, and the third current path and the fourth current path form a positive polarity short-circuit protection power supply circuit; The current conversion circuit is used to limit the total current of the first DC positive output port 12, the second DC positive output port 16, the third DC positive output port 20 and the fourth DC positive and negative output port 22 to 10A when the positive polarity power supply is first carried out on the aircraft, first using the positive polarity short-circuit protection power supply circuit to supply small current 10A, and then using the positive polarity rated power supply circuit to supply large current 100A when the circuit on the aircraft is working normally without short-circuit fault; The 1-way normally closed contact of the reverse polarity control relay 18 in series in the current conversion circuit is opened when the reverse polarity power supply is carried out, so as to cut off the power supply of the positive end of the DC control power supply in front of the middle point of the current conversion switch 29, so as to ensure that the positive rated contactor 9, the negative rated contactor 23, the positive short-circuit protection contactor 14 and the negative short-circuit protection contactor 24 will not work, that is, to block the positive polarity DC power supply to the DC positive bus bar 10 and the DC negative bus bar 26.

[0009] Optionally, in the detection system for the power supply of the aircraft DC power supply system as described above, in the DC power supply circuit, the DC input port 7 is connected to the first DC positive output port 12, the second DC positive output port 16, and the fourth DC positive and negative output port 22 through the reverse polarity power supply circuit respectively; the reverse polarity power supply circuit comprises: a reverse polarity fuse 17 and a reverse polarity control relay 18 connected in series, and a reverse polarity power supply relay 25; The positive end of the DC input port 7 is connected to the DC negative bus bar 26 through the rated fuse 8, the reverse polarity fuse 17 and the 1-way normally open contact of the reverse polarity control relay 18 in series, and is connected to the negative end of the fourth DC positive and negative output port 22; the first DC positive output port 12, the second DC positive output port 16, and the positive end of the fourth DC positive and negative output port 22 are connected to the negative end of the DC input port 7 through the 1-way normally open contact of the reverse polarity power supply relay 25. In the DC power supply circuit, the reverse polarity power supply circuit is provided to supply reverse polarity power to the three on-board DC power supplies to detect whether the reverse polarity monitoring circuit function of the three on-board DC power supplies of the on-board equipment is normal; when the reverse polarity power is supplied, the reverse polarity monitoring circuit of the corresponding three on-board equipment should cut off the power supply to the aircraft; the three on-board power supplies are: the left storage battery 3, the right storage battery 4, and the ground DC power supply socket 6.

[0010] Optionally, in the detection system for the power supply of the aircraft DC power supply system as described above, in the circuit of the detection test bench 2, the positive end of the DC input port 7 is divided into two paths after the DC control power supply positive end after the rated fuse 8, one path is the positive polarity control power supply positive end, and the other path is the reverse polarity control power supply positive end; The reverse polarity control power supply positive end is connected to the reverse polarity control relay 18 through the 1-way normally closed contact of the positive polarity interlocking relay 40 and the reverse polarity switch 41, and the reverse polarity power supply relay 25 is connected to the negative end of the DC input port 7 through the positive polarity interlocking relay 40; so that the reverse polarity control relay 18 and the reverse polarity power supply relay 25 in the reverse polarity power supply circuit are controlled by the 1-way normally closed contact of the positive polarity interlocking relay 40 and the reverse polarity switch 41; When the positive polarity power is supplied, the positive polarity interlocking relay 40 is connected, the 1-way normally closed contact is disconnected, and the power supply of the positive end of the DC control power supply before the reverse polarity switch 41 is cut off; at this time, even if the reverse polarity switch 41 is connected, the reverse polarity control relay 18 and the reverse polarity power supply relay 25 will not work; the positive DC power supply of the reverse polarity will not supply power to the DC negative bus bar 26 and the negative end of the fourth DC positive and negative output port 22; the negative DC power supply of the reverse polarity will not supply power to the first DC positive output port 12, the second DC positive output port 16, and the positive end of the fourth DC positive and negative output port 22.

[0011] Optionally, in the detection system for the power supply of the aircraft DC power supply system as described above, The positive polarity control power supply positive end in the circuit of the detection test bench 2 is branched into 3 paths, respectively passing through 1 path of the normally closed contact of the reverse polarity control relay 18, the circuit after the first path of the normally closed contact is connected to the middle point of the current conversion switch 29, which is used to control the on-off of the positive short circuit prevention contactor 14, the negative short circuit prevention contactor 24, the positive rated contactor 9 and the negative rated contactor 23; the circuit after the second path of the normally closed contact is branched into 2 paths, which are respectively connected to the first DC contactor control switch 34 and the second DC contactor control switch 35, which are used to control the on-off of the first DC contactor 11 and the second DC contactor 15; the circuit after the third path of the normally closed contact is branched into 2 paths, which are respectively connected to the third DC contactor control switch 36 and the fourth DC contactor control switch 37, which are used to control the on-off of the third DC contactor 19 and the fourth DC contactor 21.

[0012] Optionally, in the detection system for the power supply of the aircraft DC power supply system as described above, The detection test bench 2 controls the on-off of the power supply circuit connected to the positive end of the DC control power supply in front of the first DC contactor control switch 34, the second DC contactor control switch 35, the third DC contactor control switch 36, the fourth DC contactor control switch 37, the current conversion switch 29 and the reverse polarity switch 41 through the emergency power-off switch 39; when an emergency dangerous situation occurs, the DC control power supply positive end in front of the above-mentioned switches is disconnected by opening the emergency power-off switch 39, so that the corresponding DC contactor or relay of the switch is disconnected, and all the positive polarity DC power supply or reverse polarity DC power supply to the aircraft DC power supply system from the on-board power supply feeder port can be quickly cut off.

[0013] Optionally, in the detection system for the power supply of the aircraft DC power supply system as described above, a control panel 28 and a display panel 27 are further arranged on the shell of the detection test bench 2; The control panel 28 is provided with an independent emergency power-off switch 39 in the independent area; the control panel 28 is provided with the current conversion switch 29 for controlling the positive short-circuit prevention contactor 14, the negative short-circuit prevention contactor 24, the positive rated contactor 9, the negative rated contactor 23, the control switch 34 and the first direct-current output signal lamp 52 of the first direct-current contactor, the control switch 35 and the second direct-current output signal lamp 61 of the second direct-current contactor, the control switch 36 and the third direct-current output signal lamp 56 of the third direct-current contactor, and the control switch 37 and the fourth direct-current output signal lamp 58 of the fourth direct-current contactor in the normal power supply area of the direct-current power supply system; the control panel 28 is provided with the reverse polarity control switch 41 for controlling the reverse polarity control relay 18 and the reverse polarity power supply relay 25, the first direct-current reverse polarity on-off switch 42 and the first direct-current reverse polarity output signal lamp 55, the second direct-current reverse polarity on-off switch 43 and the second direct-current reverse polarity output signal lamp 64, and the fourth direct-current reverse polarity on-off switch 44 and the fourth direct-current reverse polarity output signal lamp 59 in the reverse polarity power supply area of the direct-current power supply system. The display panel 27 is provided with a direct-current input signal lamp 48, a direct-current input voltmeter 49 and a direct-current input ammeter 50.

[0014] In the second aspect, the embodiment of the present application further provides a detection method for the power supply of an aircraft direct-current power supply system, which is a first power supply detection method for the aircraft direct-current power supply system by using the detection system for the power supply of the aircraft direct-current power supply system according to any one of the above embodiments, and the method comprises the following steps. Step 1: connecting the direct-current input port 7 of the detection test bench 2 with the ground direct-current power supply 1; Step 2: connecting the first direct-current positive output port 12 of the detection test bench 2 with the positive feeder of the left storage battery 3 on the aircraft, the second direct-current positive output port 16 with the positive feeder of the right storage battery 4 on the aircraft, the third direct-current positive output port 20 with the positive feeder of the auxiliary direct-current generator 5 on the aircraft, and the fourth direct-current positive and negative output port 22 with the ground direct-current power supply socket 6 on the aircraft; Step 3, when detecting, first, the DC control power breaker 38, the emergency power-off switch 39 is turned on, the current conversion switch 29 is turned on in the anti-short circuit position, and the positive and negative two anti-short circuit DC power supply circuits are turned on; by controlling the first DC contactor control switch 34, the second DC contactor control switch 35, the third DC contactor control switch 36, and the fourth DC contactor control switch 37 to be turned on, the first, second, third, and fourth DC circuits are turned on, the left storage battery 3, the right storage battery 4, the auxiliary DC generator 5, and the ground DC power socket 6 are simulated to work, and whether the left storage battery 3, the right storage battery 4, the auxiliary DC generator 5, and the ground DC power socket 6 are normally powered in the anti-short circuit state of the on-board circuit is detected; when the left storage battery 3, the right storage battery 4, the auxiliary DC generator 5, and the ground DC power socket 6 are normally powered in the anti-short circuit state and have no short circuit fault and normal working state, the current conversion switch 29 is set in the rated position, and the rated power supply and working state of the aircraft DC power supply system are detected; Step 4, after the positive polarity power supply and working state detection of the aircraft DC power supply system is completed, the current conversion switch 29 is placed in the neutral position, the reverse polarity switch 41 is then turned on, and then the first, second, and fourth reverse polarity switches are turned on, respectively, to simulate the reverse polarity working of the left storage battery 3, the right storage battery 4, and the ground DC power socket 6, and whether the reverse polarity monitoring function of the left storage battery 3, the right storage battery 4, and the ground DC power socket 6 is normal is detected.

[0015] The beneficial effects of the present application are as follows: the present application provides a detection system and a detection method for the power supply of an aircraft DC power supply system, by installing electrical elements and control circuits inside the detection test bench 2, one input of a ground DC power supply 1 is changed into four outputs, and the on-board power feeder port of the aircraft DC power supply system is powered, especially the first power supply anti-short circuit protection, the emergency power-off in emergency situations, the automatic conversion of the positive and negative polarities of the left storage battery 3, the right storage battery 4, and the ground DC power supply 5, the positive and negative polarity power supply interlocking, and the input and output display functions are realized. The technical scheme provided by the present application combines the actual needs of the first power supply of the aircraft DC power supply system to design the detection test bench: 1) by changing one input of the ground DC power supply into four outputs, the utilization rate of the equipment is improved; 2) by setting a 10A breaker on the DC power supply input circuit, the anti-short circuit protection of the on-board circuit and equipment during the first power supply of the aircraft is realized; 3) when an emergency situation occurs, the emergency power-off switch can quickly disconnect all DC power supplies that supply power to the port of the aircraft DC power supply system; 4) by the reverse polarity switch, the automatic conversion of the positive and negative polarities of the right storage battery, the left storage battery, and the ground DC power supply power supply circuit can be easily realized; 5) by the relay interlocking circuit, the short circuit between the positive and negative terminals of the DC power supply caused by the misoperation of the reverse polarity (or positive polarity) switch during the positive polarity (or reverse polarity) power supply can be prevented.

[0016] The testing bench in this invention is simple to operate, safe, and reliable, eliminating the risk of operational errors inherent in traditional testing methods and reducing the workload of operators. This invention features a novel design concept, is easy to implement, and has wide applicability. It can provide technical solutions for aircraft manufacturing, promote the development of power supply testing technology for DC power systems in aircraft final assembly, and possesses innovativeness, extremely high application value, and widespread applicability. Attached Figure Description

[0017] The accompanying drawings are provided to further understand the technical solutions of the present invention and constitute a part of the specification. They are used together with the embodiments of this application to explain the technical solutions of the present invention and do not constitute a limitation on the technical solutions of the present invention.

[0018] Figure 1 A schematic diagram of a detection system for power supply to an aircraft DC power system, provided as an embodiment of the present invention; Figure 2 for Figure 1 The circuit diagram of the test bench in the test system for powering an aircraft DC power supply system provided in the embodiment shown is shown. Figure 3 for Figure 2 A schematic diagram of the input display panel of the testing bench provided in the embodiment shown; Figure 4 for Figure 2 A schematic diagram of the control panel of the testing bench provided in the embodiment shown; Figure 5 for Figure 2 The DC-DC conversion circuit diagram of the testing bench provided in the embodiment shown; Figure 6 for Figure 2 The DC output circuit diagram of the testing bench provided in the embodiment shown; Figure 7 for Figure 2 The embodiment shown includes a diagram of the reverse polarity conversion and interlocking circuit of the testing bench. Figure 8 for Figure 2 The embodiment shown includes an emergency power-off circuit diagram for the testing bench. Figure 9 for Figure 2 The input indicator circuit diagram of the testing bench provided in the embodiment shown; Figure 10a A first output indicator circuit diagram of the testing bench provided in an embodiment of the present invention; Figure 10b A third output indicator circuit diagram of the testing bench provided in an embodiment of the present invention; Figure 10c The fourth output indicator circuit diagram of the testing bench provided in the embodiment of the present invention; Figure 11 For Figure 1 The overall circuit structure of the test bench in the detection system for the aircraft DC power supply system provided by the embodiment is shown schematically.

[0019] BRIEF DESCRIPTION OF DRAWINGS 1, ground DC power supply; 2, test bench; 3, left storage battery positive feeder; 4, right storage battery positive feeder; 5, auxiliary DC generator positive feeder; 6, ground DC power supply socket; 7, DC input port; 8, rated fuse; 9, positive rated contactor; 10, DC positive busbar; 11, first DC contactor; 12, first DC positive output port; 13, short-circuit prevention circuit breaker; 14, positive short-circuit prevention contactor; 15, second DC contactor; 16, second DC positive output port; 17, reverse polarity fuse; 18, reverse polarity control relay; 19, third DC contactor; 20, third DC positive output port; 21, fourth DC contactor; 22, fourth DC positive and negative output port; 23, negative rated contactor; 24, negative short-circuit prevention contactor; 25, reverse polarity power supply relay; 26, DC negative busbar; 27, display panel; 28, control panel; 29, current conversion switch; 30, first DC output diode; 31, second DC output diode; 32, third DC output diode; 33, fourth DC output diode; 34, first DC contactor control switch; 35, second DC contactor control switch; 36, third DC contactor control switch; 37, fourth DC contactor control switch; 38, DC control power circuit breaker; 39, emergency power-off switch; 40, positive polarity interlocking relay; 41, reverse polarity switch; 42, first reverse polarity switch; 43, second reverse polarity switch; 44, fourth reverse polarity switch; 45, first isolation diode; 46, second isolation diode; 47, fourth isolation diode; 48, DC input signal lamp; 49, DC input voltmeter; 50, DC input ammeter; 51, shunt of DC input ammeter; 52, first DC output signal lamp; 53, first DC output signal lamp diode; 54, first DC reverse polarity output signal lamp diode; 55, first DC reverse polarity output signal lamp; 56, third DC output signal lamp; 57, third DC output signal lamp diode; 58, fourth DC output signal lamp; 59, fourth DC reverse polarity output signal lamp; 60, fourth DC reverse polarity output signal lamp diode; 61, second DC output signal lamp; 62, second DC output signal lamp diode; 63, second DC reverse polarity output signal lamp diode; 64, second DC reverse polarity output signal lamp. DETAILED DESCRIPTION

[0020] In order to make the objects, technical solutions and advantages of the present application clearer, the embodiments of the present application will be described in detail below with reference to the drawings. It should be noted that the embodiments in the present application and the features in the embodiments can be combined with each other in any manner without conflict.

[0021] As described in the above background, the traditional detection method for the first power supply of the aircraft DC power supply system has the problems of low equipment utilization, high cost and poor economy, and the safety hazard that it is difficult to quickly disconnect all ground DC power supplies to the aircraft DC power supply system in dangerous situations.

[0022] In addition, when the aircraft DC power supply system is powered for the first time, the port of the aircraft DC power supply system is directly connected to the corresponding ground DC power supply without passing through a protection device, so that effective short circuit protection cannot be provided for the equipment and circuits on the aircraft. When the left storage battery, the right storage battery and the ground DC power supply reverse polarity detection is performed, the positive and negative wires of the left storage battery, the right storage battery and the ground DC power supply socket need to be disassembled and exchanged to adjust the polarity, and after the reverse polarity detection is completed, the original state is restored, which is repeated, time-consuming and laborious, and unsafe.

[0023] In view of the above problems, the present application provides a detection system and method for the first power supply of the aircraft DC power supply system, specifically a control, protection and detection system for the first power supply of the aircraft DC power supply system in the general assembly stage, which is used for simulating the detection system of the left storage battery, the right storage battery, the auxiliary DC generator and the ground DC power supply socket to the on-board power supply feeder port of the aircraft DC power supply system. The detection system can realize the functions of short circuit protection, emergency power-off, automatic conversion of positive and negative polarity of the left storage battery, the right storage battery and the ground DC power supply socket, interlocking of positive and negative polarity, input and output display, etc.

[0024] The following specific embodiments provided by the present application can be combined with each other, and the same or similar concepts or processes can not be described in some embodiments.

[0025] Figure 1 A system architecture schematic diagram of a detection system for the first power supply of the aircraft DC power supply system is provided for the embodiments of the present application, Figure 2 A Figure 1 A circuit schematic diagram of a detection system for the first power supply of the aircraft DC power supply system is provided for the embodiments shown in the drawings. Referring to Figure 1 and Figure 2As shown in the figure, the four onboard power supplies in the aircraft DC power supply system of the embodiment of the application are powered in the following manner: the left onboard storage battery 3 and the right onboard storage battery 4 provide emergency DC power supply, the onboard auxiliary DC generator 5 provides auxiliary DC power supply, and the ground DC power supply socket 6 provides ground maintenance power supply. The detection system for first power supply of the aircraft DC power supply system provided by the embodiment of the application comprises a ground DC power supply 1 and a detection test bench 2; the ground DC power supply 1 is electrically connected to the four onboard power supply feeder ports in the aircraft DC power supply system through the detection test bench 2, thereby providing detection power supply for the aircraft DC power supply system.

[0026] As shown in the figure, the detection test bench 2 in the embodiment of the application is connected to the ground DC power supply 1 through the DC input port 7 arranged on one side thereof, and is connected to the four onboard power supply feeder ports in the aircraft DC power supply system through the four DC power supply output ports arranged on the other side thereof. Figure 2

[0027] Among them, the positive terminal of the DC input port 7 is branched into four paths after passing through the DC positive bus bar 10, and the four paths are respectively connected to the positive terminals of the four DC power supply output ports through a DC contactor, thereby forming a positive DC power supply circuit; the negative terminal of the DC input port 7 is connected to the negative terminal of one of the DC power supply output ports through the DC negative bus bar 26, thereby forming a negative DC power supply circuit. The DC power supply circuit formed by the positive DC power supply circuit and the negative DC power supply circuit is used to supply positive polarity power supply to the four onboard power supplies in the aircraft DC power supply system.

[0028] In one implementation manner of the embodiment of the application, as shown in the figure, the four DC power supply output ports are respectively: a first DC positive output port 12, a second DC positive output port 16, a third DC positive output port 20, and a fourth DC positive-negative output port 22. Figure 2

[0029] In this implementation manner, the specific structure of the positive DC power supply circuit is as follows: the positive terminal of the DC input port 7 is connected to the DC positive bus bar 10 through the rated fuse 8, the shunt 51 of the DC input current meter, the positive rated contactor 9 or the positive anti-short-circuit contactor 14, and among the four paths branched from the DC positive bus bar 10, the first path is connected to the first DC positive output port 12 through the first DC contactor 11, the second path is connected to the second DC positive output port 16 through the second DC contactor 15, the third path is connected to the third DC positive output port 20 through the third DC contactor 19, and the fourth path is connected to the positive terminal of the fourth DC positive-negative output port 22 through the fourth DC contactor 21, thereby forming the positive DC power supply circuit.

[0030] ​​In the implementation, the specific structure of the negative DC power supply circuit is that the negative end of the DC input port 7 is connected to the DC negative bus bar 26 through the negative rated contactor 23 or the negative anti-short circuit contactor 24, thereby being connected to the negative end of the fourth DC positive and negative output port 22, and thereby forming the negative DC power supply circuit.

[0031] The detection system for the aircraft DC power supply system provided by the embodiment of the application further comprises a control circuit for realizing reverse polarity power supply, i.e., a reverse polarity control circuit, which comprises a DC control power supply circuit breaker 38, an emergency power-off switch 39 and a reverse polarity control relay 18 connected in series in turn at the rear end of the rated fuse 8, and four DC contactor control switches for one-to-one corresponding control of the on-off states of the four DC contactors. Figure 5 and Figure 6 as shown.

[0032] In the reverse polarity control circuit provided by the implementation, among the four paths branched at the rear end of the 2-path normally closed contact of the reverse polarity control relay 18, the first path controls the on-off state of the first DC contactor 11 through the first DC contactor control switch 34, the second path controls the on-off state of the second DC contactor 15 through the second DC contactor control switch 35, the third path controls the on-off state of the third DC contactor 19 through the third DC contactor control switch 36, and the fourth path controls the on-off state of the fourth DC contactor 21 through the fourth DC contactor control switch 37. The four DC contactors are controlled by the DC control power supply circuit breaker 38, the emergency power-off switch 39, the 2-path normally closed contact of the reverse polarity control relay 18, and the first DC contactor control switch 34, the second DC contactor control switch 35, the third DC contactor control switch 36 and the fourth DC contactor control switch 37.

[0033] The implementation principle of the reverse polarity power supply in the implementation is that the 2-path normally closed contact of the reverse polarity control relay 18 connected in series in the reverse polarity control circuit is disconnected when the reverse polarity control relay 18 is turned on during reverse polarity power supply, thereby cutting off the power supply from the positive end of the DC control power supply in front of the four DC contactor control switches. At this time, even if the four DC contactor control switches are turned on, the four DC contactors will not work, and the positive polarity DC power supply will not supply power to the positive end of the four DC power supply output ports, thereby preventing the short circuit between the positive end and the negative end of the DC power supply caused by the misoperation of turning on the positive polarity DC contactor control switch during reverse polarity power supply.

[0034] In one implementation form of the embodiment of the application, in the direct current power supply circuit, the front ends of the direct current positive bus bar 10 and the direct current negative bus bar 26 are provided with a current conversion circuit, the conversion of the current conversion circuit is controlled by the direct current control power supply circuit breaker 38, the emergency power-off switch 39, the normally closed contact of the reverse polarity control relay 18 and the current conversion switch 29, the current conversion circuit comprises four parallel current paths; see Figure 2 and Figure 5 As shown in the drawings, the four parallel current paths of the current conversion circuit are respectively: In the first current path, the positive end of the direct current input port 7 is connected to the direct current positive bus bar 10 through the rated fuse 8, the shunt 51 of the direct current input ammeter and the positive rated contactor 9; in the second current path, the negative end of the direct current input port 7 is connected to the direct current negative bus bar 26 through the negative rated contactor 23; the first current path and the second current path form a positive polarity rated power supply circuit. In the third current path, the positive end of the direct current input port 7 is connected to the direct current positive bus bar 10 through the rated fuse 8, the shunt 51 of the direct current input ammeter, the short-circuit prevention circuit breaker 13 and the positive short-circuit prevention contactor 14; in the fourth current path, the negative end of the direct current input port 7 is connected to the direct current negative bus bar 26 through the negative short-circuit prevention contactor 24; the third current path and the fourth current path form a positive polarity short-circuit prevention power supply circuit.

[0035] Based on the structure of the current conversion circuit, when the positive polarity power supply is first performed on the aircraft, the total current of the positive polarity power supply to the first direct current positive output port 12, the second direct current positive output port 16, the third direct current positive output port 20 and the positive end of the fourth direct current positive and negative output port 22 is limited to 10A for protection, first, the positive polarity short-circuit prevention power supply circuit is used to supply small current 10A, and after the on-board circuit is normal without short-circuit fault, the positive polarity rated power supply circuit is used to supply large current 100A; thus, the burning of wires, components, airborne equipment and the like caused by short-circuit fault on the aircraft can be effectively prevented.

[0036] It should be noted that the normally closed contact of the reverse polarity control relay 18 in series in the current conversion circuit is connected, and when the reverse polarity power supply is performed, the normally closed contact is disconnected, so that the power supply of the front end of the middle point of the current conversion switch 29 is cut off. At this time, even if the current conversion switch 29 is connected to the rated or short-circuit prevention position, the positive rated contactor 9 and the negative rated contactor 23 in the positive polarity rated power supply circuit and the positive short-circuit prevention contactor 14 and the negative short-circuit prevention contactor 24 in the positive polarity short-circuit prevention power supply circuit will not work; that is, the positive direct current power supply to the direct current positive bus bar 10 and the direct current negative bus bar 26 is blocked, thereby preventing the reverse polarity power supply, the misoperation of connecting the current conversion switch 29, and the short circuit between the positive end and the negative end of the direct current power supply.

[0037] In one implementation of the embodiment of the application, to achieve the reverse polarity power supply to the airborne DC power supply, it is also required to set a reverse polarity power supply circuit in the DC power supply circuit. In a specific implementation, as shown in the figure, in the DC power supply circuit, the DC input port 7 is connected to the first DC positive output port 12, the second DC positive output port 16, and the fourth DC positive and negative output port 22 through the reverse polarity power supply circuit respectively. The reverse polarity power supply circuit includes a reverse polarity fuse 17 and a reverse polarity control relay 18 connected in series, and a reverse polarity power supply relay 25. Figure 7

[0038] In this implementation, the positive end of the DC input port 7 is connected to the DC negative bus bar 26 through the rated fuse 8, the 1-way normally open contact of the reverse polarity fuse 17 and the reverse polarity control relay 18, and the negative end of the fourth DC positive and negative output port 22. The first DC positive output port 12, the second DC positive output port 16, and the positive end of the fourth DC positive and negative output port 22 are connected to the negative end of the DC input port 7 through the 1-way normally open contact of the reverse polarity power supply relay 25.

[0039] In the DC power supply circuit, the reverse polarity power supply circuit is set to supply reverse polarity power to the three airborne DC power supplies to detect whether the reverse polarity monitoring circuit function of the three DC power supplies of the airborne equipment is normal. When the reverse polarity power supply is performed, the reverse polarity monitoring circuit of the corresponding three power supplies should cut off the power supply to the aircraft. The three airborne power supplies are the left storage battery 3, the right storage battery 4, and the ground DC power supply socket 6.

[0040] In a specific embodiment of this implementation, in the circuit of the test bench 2, the positive end of the DC input port 7 is divided into two paths after the DC control power supply positive end through the rated fuse 8, the DC control power supply circuit breaker 38, and the emergency power-off switch 39. One path is the positive polarity control power supply positive end, and the other path is the reverse polarity control power supply positive end.

[0041] On the one hand, the reverse polarity control power supply positive end is connected to the reverse polarity control relay 18 through the 1-way normally closed contact of the positive polarity interlocking relay 40 and the reverse polarity switch 41, and the reverse polarity power supply relay 25 is connected to the negative end of the DC input port 7 through the positive polarity interlocking relay 40. This makes the reverse polarity control relay 18 and the reverse polarity power supply relay 25 in the reverse polarity power supply circuit controlled by the 1-way normally closed contact of the positive polarity interlocking relay 40 and the reverse polarity switch 41. The specific control mode is as follows: ​When the positive polarity power supply, the positive polarity chain relay 40 is connected, its 1 way normally closed contact is disconnected, cutting off the front end of the positive polarity switch 41 DC control power supply power supply; At this time, even if the positive polarity switch 41 is connected, the negative polarity control relay 18 and the negative polarity power supply relay 25 will not work; The positive polarity of the positive DC power supply will not supply power to the DC negative bus 26 and the fourth DC positive and negative output port 22 negative end; The negative polarity of the negative DC power supply will not supply power to the first DC positive output port 12, the second DC positive output port 16, the fourth DC positive and negative output port 22 positive end; So as to effectively prevent the positive polarity power supply, the misoperation of connecting the negative polarity power supply switch, resulting in the short circuit between the positive end and the negative end of the DC power supply.

[0042] On the other hand, the positive polarity control power supply positive end in the circuit of the test bench 2 is branched into 3 ways, which are connected to the 1 way normally closed contact of the negative polarity control relay 18 respectively, and the circuit after the first normally closed contact is connected to the middle point of the current conversion switch 29, which is used to control the on-off of the positive short circuit prevention contactor 14, the negative short circuit prevention contactor 24, the positive rated contactor 9 and the negative rated contactor 23; The circuit after the second normally closed contact is branched into 2 ways, which are connected to the first DC contactor control switch 34 and the second DC contactor control switch 35 respectively, which are used to control the on-off of the first DC contactor 11 and the second DC contactor 15; The circuit after the third normally closed contact is branched into 2 ways, which are connected to the third DC contactor control switch 36 and the fourth DC contactor control switch 37 respectively, which are used to control the on-off of the third DC contactor 19 and the fourth DC contactor 21.

[0043] In the above embodiment of the present application, as shown in Figure 8 The test bench 2 can control the on-off of the power supply circuit of the DC control power supply positive end connected to the first DC contactor control switch 34, the second DC contactor control switch 35, the third DC contactor control switch 36, the fourth DC contactor control switch 37, the current conversion switch 29 and the front end of the negative polarity switch 41. When an emergency danger occurs, the DC control power supply positive end in front of the above-mentioned switches is disconnected by opening the emergency power-off switch 39, so that the corresponding DC contactors or relays of the above-mentioned switches are disconnected, and all the positive polarity DC power supply or negative polarity DC power supply feeding the aircraft DC power supply system through the on-board power supply feeder port can be quickly cut off.

[0044] In one implementation manner of the embodiment of the present application, as shown in Figure 3 and Figure 4 As shown in

[0045] As shown in Figure 3As shown, the display panel 27 is equipped with a power indicator light 48 for DC input signal, a DC input voltmeter 49 and a DC input ammeter 50.

[0046] like Figure 4 As shown, the control panel 28 has an independent emergency power-off switch 39 in its independent area; the normal power supply area of ​​the DC power system of the control panel 28 has a current conversion switch 29 for controlling the positive short-circuit protection contactor 14, the negative short-circuit protection contactor 24, the positive rated contactor 9, and the negative rated contactor 23, a control switch 34 and a first DC output indicator light 52 for the first DC contactor, a control switch 35 and a second DC output indicator light 61 for the second DC contactor, a control switch 36 and a third DC output indicator light 56 ​​for the third DC contactor, and a control switch 37 and a fourth DC output indicator light 58 for the fourth DC contactor; the reverse polarity power supply area of ​​the DC power system of the control panel 28 has a reverse polarity control switch 41 for controlling the reverse polarity control relay 18 and the reverse polarity power supply relay 25, a first DC reverse polarity connection switch 42 and a first DC reverse polarity output indicator light 55, a second DC reverse polarity connection switch 43 and a second DC reverse polarity output indicator light 64, and a fourth DC reverse polarity connection switch 44 and a fourth DC reverse polarity output indicator light 59.

[0047] Based on the detection system for aircraft DC power supply provided in the embodiments of the present invention, the present invention also provides a detection method for aircraft DC power supply. The method for detecting the initial power supply of an aircraft DC power supply system using the detection system for aircraft DC power supply provided in the above embodiments of the present invention includes the following steps: Step 1: Connect the DC input port 7 of the test bench 2 to a ground DC power supply 1; Step 2: Connect the first DC positive output port 12 of the test bench 2 to the positive feed line of the left battery 3 on the aircraft, the second DC positive output port 16 to the positive feed line of the right battery 4 on the aircraft, the third DC positive output port 20 to the positive feed line of the auxiliary DC generator 5 on the aircraft, and the fourth DC positive and negative output port 22 to the ground DC power socket 6 on the aircraft. Step 3, when detecting, first, through the control panel 28, the direct current control power circuit breaker 38, the emergency power-off switch 39 is turned on, the current conversion switch 29 is turned on in the anti-short circuit position, and the positive and negative two anti-short circuit direct current power supply circuits are turned on; through the control panel 28, the first direct current contactor control switch 34, the second direct current contactor control switch 35, the third direct current contactor control switch 36 and the fourth direct current contactor control switch 37 are turned on, the first, second, third and fourth direct current circuits are turned on, the left storage battery 3, the right storage battery 4 and the auxiliary direct current generator 5 are simulated to work and the ground direct current power supply socket 6 is simulated to work, and whether the left storage battery 3, the right storage battery 4, the auxiliary direct current generator 5 and the ground direct current power supply socket 6 are normally supplied with power in the anti-short circuit state of the aircraft circuit is detected; when the left storage battery 3, the right storage battery 4, the auxiliary direct current generator 5 and the ground direct current power supply socket 6 are normally supplied with power in the anti-short circuit state and the working state is normal, the current conversion switch 29 is set in the rated position, and the rated power supply and working state of the aircraft direct current power supply system are detected; Step 4, after the positive polarity power supply and working state detection of the aircraft direct current power supply system is completed, the current conversion switch 29 is placed in the neutral position through the control panel 28, then the reverse polarity switch 41 is turned on, and then the first, second and fourth reverse polarity switches are turned on respectively, the left storage battery 3, the right storage battery 4 and the ground direct current power supply socket 6 are simulated to work in reverse polarity, and whether the reverse polarity monitoring function of the left storage battery 3, the right storage battery 4 and the ground direct current power supply socket 6 is normal is detected.

[0048] The detection system and detection method for the aircraft direct current power supply system provided by the embodiment of the application, through the electrical elements and control circuits installed in the detection test bench 2, one input of a ground direct current power supply 1 is changed into four outputs, the on-board power feeder port of the aircraft direct current power supply system is supplied with power, and especially, the first power supply anti-short circuit protection, the emergency power-off in emergency dangerous situations, the automatic conversion of the positive and reverse polarities of the left storage battery 3, the right storage battery 4 and the ground direct current power supply 5, the positive and reverse polarity power supply interlocking, the input and output display and other functions are realized. The technical scheme provided by the application combines the actual needs of the first power supply of the aircraft direct current power supply system to design the detection test bench: 1) through changing one input of the ground direct current power supply into four outputs, the utilization rate of the equipment is improved; 2) through setting the 10A circuit breaker on the direct current power supply input circuit, the anti-short circuit protection of the on-board circuit and equipment during the first power supply of the aircraft is realized; 3) when an emergency dangerous situation occurs, the emergency power-off switch can quickly disconnect all the direct current power supplies supplying power to the port of the aircraft direct current power supply system; 4) through the reverse polarity switch, the automatic conversion of the positive and reverse polarities of the right storage battery, the left storage battery and the ground direct current power supply supply circuit can be conveniently realized; 5) through the relay interlocking circuit, the short circuit between the positive end and the negative end of the direct current power supply caused by the misoperation of the reverse polarity (or positive polarity) switch during the positive polarity (or reverse polarity) power supply can be prevented.

[0049] The detection test bench in the embodiment of the application is simple in operation, safe and reliable, eliminates the risk of operation errors existing in the traditional test method, and reduces the working strength of the operator. The design idea of the application is novel, convenient to implement, and widely applicable, and can provide a technical solution for aviation manufacturing, promote the development of the power supply detection technology of the direct current power supply system of the aircraft assembly, and has innovation, high application value and promotion.

[0050] The specific implementation of each component in the detection system for the power supply of the direct current power supply system of the aircraft provided by the embodiment of the application will be described below.

[0051] 1. The specific implementation of the direct current conversion circuit in the detection test bench 2 is shown in the figure. Figure 5

[0052] The direct current conversion circuit of the detection test bench 2 is provided with a short circuit protection breaker DBF-10 (13) on the positive short circuit protection path, and the short circuit protection circuit is connected to the total power supply current of the direct current power supply system of the aircraft after being turned on, so that the short circuit protection of the on-board wires, components and devices and airborne equipment of the aircraft during the first power supply is realized.

[0053] The positive end of the control power supply of the direct current conversion circuit of the detection test bench 2 is connected to the neutral position of the current conversion switch MLK-3 (29) through the positive end of the direct current input port PJ-500A (7), rated fuse GB-100 (8), direct current control power supply breaker DBF-10 (38), emergency power-off switch MJK-2 (39) and the normally closed contact of the reverse polarity control relay JKC-56B (18).

[0054] ​Between the DC input port PJ-500A (7) of the test bench 2 and the DC positive bus bar 10 and the DC negative bus bar 26 inside the test bench 2, four parallel power supply paths are arranged, two of which are short-circuit prevention paths with a rated current of 10 amperes, and the other two are rated paths with a rated current of 100 amperes. The selection of the current path is realized by setting the corresponding position of the current switching switch MLK-3 (29) through the test bench control panel 28 to make the positive and negative short-circuit prevention contactors MZJ-25A (14), MZJ-25A (24) work at the same time or make the positive and negative rated contactors MZJ-100A (9), MZJ-100A (23) work at the same time. The current switching switch MLK-3 (29) is a single-pole switching switch with a neutral off position, which can ensure the uniqueness of the selection of the current path. When the current switching switch MLK-3 (29) is set to the short-circuit prevention position, the positive and negative short-circuit prevention contactors MZJ-25A (14), MZJ-25A (24) work at the same time, and the positive DC current input from the DC input port PJ-500A (7) is transmitted to the DC positive bus bar 10 inside the test bench 2 through the rated fuse GB-100 (8), the shunt QFL-3 (51) of the DC input current meter, the short-circuit prevention circuit breaker DBF-10 (13), and the positive short-circuit prevention contactor MZJ-25A (14). At the same time, the negative DC current input from the DC input port PJ-500A (7) is transmitted to the DC negative bus bar 26 inside the test bench 2 through the negative short-circuit prevention contactor MZJ-25A (24). At this time, the test bench works in the short-circuit prevention state. When the current switching switch MLK-3 (29) is set to the rated position, the positive and negative rated contactors MZJ-100A (9), (23) work at the same time, and the positive DC current input from the DC input port PJ-500A (7) is transmitted to the DC positive bus bar 10 inside the test bench 2 through the rated fuse GB-100 (8), the shunt QFL-3 (51) of the DC input current meter, and the positive rated contactor MZJ-100A (9). At the same time, the negative DC current input from the DC input port PJ-500A (7) is transmitted to the DC negative bus bar 26 inside the test bench 2 through the negative rated contactor MZJ-100A (23). At this time, the test bench works in the rated state.

[0055] 2. The specific implementation of the DC output circuit in the test bench is shown in Figure 6

[0056] ​The positive polarity direct current of the direct current positive bus bar 10 and the direct current negative bus bar 26 inside the detection test bench 2 is supplied to the positive end of the first direct current positive output port 12, the second direct current positive output port 16, the third direct current positive output port 20 and the fourth direct current positive negative output port 22 by turning on the first direct current contactor control switch MJK-2 (34), the second direct current contactor control switch MJK-2 (35), the third direct current contactor control switch MJK-2 (36) and the fourth direct current contactor control switch MJK-2 (37).

[0057] The control power positive end of the direct current output circuit of the detection test bench 2 is connected to the first direct current contactor control switch MJK-2 (34) and the second direct current contactor control switch MJK-2 (35) through the 1-way normally closed contact of the reverse polarity control relay JKC-56B (18) after the positive end of the direct current input port PJ-500A (7), the rated fuse GB-100 (8), the direct current control power circuit breaker DBF-10 (38) and the emergency power-off switch MJK-2 (39), and is used to control the on-off of the first direct current contactor MZJ-50A (11) and the second direct current contactor MZJ-50A (15).

[0058] The first direct current contactor control switch MJK-2 (34) is turned on through the control panel 28 of the detection test bench 2, so that the first direct current contactor MZJ-50A (11) of the detection test bench 2 works, and the positive direct current on the direct current positive bus bar 10 inside the detection test bench 2 is transmitted to the first direct current positive output port 12 of the detection test bench 2 through the first direct current contactor MZJ-50A (11) and the first direct current output diode IN4045 (30).

[0059] The second direct current contactor control switch MJK-2 (35) is turned on through the control panel 28 of the detection test bench 2, so that the second direct current contactor MZJ-50A (15) inside the detection test bench 2 works, and the positive direct current on the direct current positive bus bar 10 inside the detection test bench 2 is transmitted to the second direct current positive output port 16 of the detection test bench 2 through the second direct current contactor MZJ-50A (15) and the second direct current output diode IN4045 (31).

[0060] The third DC contactor control switch MJK-2 (36) is turned on through the test bench 2 control panel 28, and the third DC contactor MZJ-50A (19) in the test bench 2 is put into operation. The positive DC power on the DC positive bus bar 10 in the test bench 2 is transmitted to the third DC positive output port 20 of the test bench 2 through the third DC contactor MZJ-50A (19) and the third DC output diode IN4045 (32).

[0061] The fourth DC contactor control switch MJK-2 (37) is turned on through the test bench 2 control panel 28, and the fourth DC contactor MZJ-100A (21) in the test bench 2 is put into operation. The positive DC power on the DC positive bus bar 10 in the test bench 2 is transmitted to the positive end of the fourth DC positive and negative output port 22 of the test bench 2 through the fourth DC contactor MZJ-100A (21) and the fourth DC output diode IN4045 (33).

[0062] The negative DC power on the DC negative bus bar 26 in the test bench 2 is directly transmitted to the negative end of the fourth DC positive and negative output port 22 of the test bench 2.

[0063] 3. The specific implementation of the DC positive and negative polarity conversion and interlocking circuit in the test bench is shown in Figure 7 .

[0064] According to the power supply inspection requirements of the aircraft DC power supply system: when the reverse polarity DC power supply is supplied to the left storage battery 3, the right storage battery 4 and the DC power supply socket 6 of the aircraft, the reverse polarity power supply should not be connected to the aircraft DC power supply system. In order to verify the correctness of the reverse polarity monitoring circuit function of the left storage battery 3, the right storage battery 4 and the ground DC power supply socket 6 on the aircraft, it is necessary to provide reverse polarity DC power supply to the left storage battery 3, the right storage battery 4 and the ground DC power supply socket 6 of the aircraft. The traditional method is to disassemble and exchange the positive and negative wires of the left storage battery 3, the right storage battery 4 and the ground DC power supply socket 6 by the staff to adjust the polarity, which is time-consuming and laborious, and unsafe. Therefore, an automatic conversion circuit is provided in the test bench 2. After the DC control power supply circuit breaker DBF-10 (38) and the emergency power-off switch MJK-2 (39) are turned on, the reverse polarity switch MJK-2 (41) is turned on through the test bench 2 control panel 28, and the reverse polarity control relay JKC-56B (18) in the test bench 2 is turned on and put into operation. The positive end of the DC input port PJ-500A (7) is transmitted to the negative end of the fourth DC positive and negative output port 22 of the test bench 2 through the rated fuse GB-100 (8), the reverse polarity fuse TB-5 (17), the 1-way normally open contact of the reverse polarity control relay JKC-56B (18), and the DC negative bus bar 26.

[0065] When the reverse polarity control relay JKC-56B (18) in the test bench 2 is turned on, the one normally open contact in the reverse polarity control relay JKC-56B (18) is connected to turn on the reverse polarity power supply relay JKC-56B (25), and the negative terminal of the DC input port PJ-500A (7) is divided into three paths, each of which passes through one normally open contact of the reverse polarity power supply relay JKC-56B (25), and then passes through the first reverse polarity switch MJK-2 (42) and the first isolation diode 2CZ117B (45), the second reverse polarity switch MJK-2 (43) and the second isolation diode 2CZ117B (46), and the fourth reverse polarity switch MJK-2 (44) and the fourth isolation diode 2CZ117B (47), and is input to the positive terminals of the first DC positive output port 12, the second DC positive output port 16, and the fourth DC positive and negative output port 22 of the test bench 2. At this time, the first DC positive output port 12, the second DC positive output port 16, and the fourth DC positive and negative output port 22 are connected in reverse polarity with the negative terminal of the fourth DC positive and negative output port 22. The reverse polarity DC power supply passes through the first DC positive output port 12, the second DC positive output port 16, the fourth DC positive and negative output port 22, and the process cable to supply power to the left storage battery 3 and the right storage battery 4 on the aircraft and the ground DC power supply socket 6. In the reverse polarity positive terminal path, a reverse polarity fuse TB-5 (17) is arranged to protect the circuit by limiting the current to 5A.

[0066] In order to prevent the short circuit between the positive terminal and the negative terminal of the direct current power supply caused by the positive and negative polarity circuit connection when the direct current power supply is supplied with positive or negative polarity, the positive polarity and the negative polarity should be set to interlock each other so that they cannot work at the same time, and the control logic relationship should be set to the priority of the first worker. When the positive polarity is supplied, the positive short circuit prevention contactor MZJ-25A (14), the negative short circuit prevention contactor MZJ-25A (24) or the positive rated contactor MZJ-100A (9), the negative rated contactor MZJ-100A (23) work, the negative polarity control relay JKC-56B (18) and the negative polarity power supply relay JKC-56B (25) should not work. When the negative polarity control relay JKC-56B (18) works, the positive rated contactor MZJ-100A (9), the negative rated contactor MZJ-100A (23) and the positive short circuit prevention contactor MZJ-25A (14), the negative short circuit prevention contactor MZJ-25A (24) should not work. For this purpose, the design idea of the circuit is that the 1st normally closed contact of the negative polarity control relay JKC-56B (18) is connected in series between the emergency power-off switch MJK-2 (39) and the current conversion switch MLK-3 (29), the control switch MJK-2 (34) of the first direct current contactor and the control switch MJK-2 (35) of the second direct current contactor, the control switch MJK-2 (36) of the third direct current contactor and the control switch MJK-2 (37) of the fourth direct current contactor, when the negative polarity switch MJK-2 (41) is turned on, the negative polarity control relay JKC-56B (18) works, and the 3rd normally closed contact of the negative polarity control relay JKC-56B (18) is disconnected, cutting off the circuit for supplying power to the current conversion switch MLK-3 (29), the control switch MJK-2 (34) of the first direct current contactor and the control switch MJK-2 (35) of the second direct current contactor, the control switch MJK-2 (36) of the third direct current contactor and the control switch MJK-2 (37) of the fourth direct current contactor; at the same time, the 1st normally closed contact of the positive polarity interlock relay JKC-52B (40) is connected in series between the emergency power-off switch MJK-2 (39) and the negative polarity switch MJK-2 (41), when the current conversion switch MLK-3 (29) is set at the short circuit prevention or rated position, the positive short circuit prevention contactor MZJ-25A (14), the negative short circuit prevention contactor MZJ-25A (24) or the positive rated contactor MZJ-100A (9), the negative rated contactor MZJ-100A (23) work, the direct current positive bus bar (10) inside the test bench (2) has direct current positive electricity, the positive polarity interlock relay JKC-52B (40) works, and the 1st normally closed contact of the positive polarity interlock relay JKC-52B (40) is disconnected, cutting off the circuit for supplying power to the negative polarity switch MJK-2 (41).

[0067] 4. The specific embodiment of the emergency power-off circuit in the test bench is shown in Figure 8 ​

[0068] When emergency danger occurs during the aircraft power supply process, in order to quickly and urgently cut off the power, the control switches of all DC contactors or relays in the test bench 2: the first DC contactor control switch MJK-234, the second DC contactor control switch MJK-2(35), the third DC contactor control switch MJK-2(36), the fourth DC contactor control switch MJK-2(37), the current conversion switch MLK-3(29) and the positive end of the DC control power supply in front of the reverse polarity switch MJK-2(41) are all connected to an emergency power-off switch MJK-2(39), and these switches are controlled by the switch. When emergency danger occurs, disconnecting the switch will disconnect the power supply of the above-mentioned switches, and the DC contactors or relays controlled by the above-mentioned switches will be disconnected, so that all positive polarity DC power supplies or reverse polarity DC power supplies in the test bench which supply power to the aircraft DC power supply system port are disconnected, realizing the function of quick power-off in emergency danger.

[0069] 6、The specific implementation of the input indication circuit in the test bench is shown in Figure 9 .

[0070] In order to observe the working state of the input power supply, DC input signal lamp ZSD-1(48), DC input voltage meter BVJ-2A(49), DC input current meter BAZ-3(50) and shunt QFL-3(51) of the DC input current meter are arranged at the entrance of the DC input port PJ-500A(7) in the test bench 2, indicating the working state of the DC input power supply and the voltage and current values of the DC input power supply.

[0071] 7、The specific implementation of the output indication circuit in the test bench is shown in Figure 10a , Figure 10b , Figure 10c . To indicate the power supply state of the first DC positive output port 12, the first DC output signal lamp ZSD-1 (52) and the first DC reverse polarity output signal lamp ZSD-1 (55) are arranged at the first DC positive output port 12. When the first DC positive output port 12 is supplied with positive polarity, the first DC contactor MZJ-50A (11) works, and the positive DC power source passes through the first DC output signal lamp ZSD-1 (52) and the first DC output signal lamp diode 2CZ57J (53), so that the first DC output signal lamp ZSD-1 (52) is lit. When the first DC positive output port 12 is supplied with reverse polarity, the positive DC power source passes through the first DC reverse polarity output signal lamp diode 2CZ57J (54) and the first DC reverse polarity output signal lamp ZSD-1 (55), and the first DC reverse polarity output signal lamp ZSD-1 (55) is lit when the first reverse polarity switch MJK-2 (42) is turned on. The first isolation diode 2CZ117B (45) is arranged to isolate the first DC positive output port (12) from the positive voltage signal from the DC negative bus bar (26), the first DC reverse polarity output signal lamp diode 2CZ57J (54) and the first DC reverse polarity output signal lamp ZSD-1 (55) when the first reverse polarity switch MJK-2 (42) is not turned on.

[0072] The indication circuits of the first DC positive output port 12 and the second DC positive output port 16 are the same, and the first DC positive output port 12 is taken as an example for description. Figure 10a The indication circuits of the first DC positive output port 12 and the second DC positive output port 16 are the same, and the first DC positive output port 12 is taken as an example for description.

[0073] To indicate the power supply state of the third DC positive output port 20, the third DC output signal lamp ZSD-1 (56) is arranged at the third DC positive output port 20. When the third DC positive output port 20 is supplied with power, the third DC contactor 19 works, and the positive DC power source passes through the third DC output signal lamp ZSD-1 (56) and the third DC output signal lamp diode 2CZ57J (57), so that the third DC output signal lamp ZSD-1 (56) is lit.

[0074] To indicate the fourth DC positive output port 22 power supply state, the fourth DC output signal lamp ZSD-1 (58) and the fourth DC reverse polarity output signal lamp ZSD-1 (59) are set at the fourth DC positive output port 22, when the fourth DC positive output port 22 is positive polarity power supply, the fourth DC contactor (21) MZJ-100A works, the positive DC power supply passes through the fourth DC contactor MZJ-100A (21) auxiliary contact, makes the fourth DC output signal lamp ZSD-1 (58) burn; when the fourth DC positive output port 22 is reverse polarity power supply, the positive DC power supply passes through the fourth DC reverse polarity output signal lamp diode 2CZ57J (60), the fourth DC reverse polarity output signal lamp ZSD-1 (59), when the fourth reverse polarity switch MJK-2 (45) is connected, the fourth DC reverse polarity output signal lamp ZSD-1 (59) burns. Among them, the fourth isolation diode 2CZ117B (47) is set to isolate the fourth DC positive and negative output port 22 positive end from the positive voltage signal from the DC negative bus bar 26, the fourth DC reverse polarity output signal lamp diode 2CZ57J (60), the fourth DC reverse polarity output signal lamp ZSD-1 (59) when the fourth reverse polarity switch MJK-2 (45) is not connected.

[0075] 8. The circuit structure of the detection test bench is shown in Figure 11

[0076] The working principle of the detection test bench: turn on the ground DC power supply, the DC input signal lamp 48 burns, the DC input voltmeter 49 has DC voltage indication, the aircraft power supply has DC current indication. Turn on the short circuit protection circuit breaker 13, turn on the DC control power supply circuit breaker 38 and the emergency power off switch 39, connect the current conversion switch 29 to the short circuit protection position, make the positive short circuit protection contactor 14 and the negative short circuit protection contactor 24 work, the short circuit protection input path is connected, the DC positive bus bar 10 in the detection test bench has the DC positive voltage of the short circuit protection working state, and the DC negative bus bar 26 has the DC negative voltage of the short circuit protection working state. At this time, the positive polarity DC power output to the first DC positive output port 12, the second DC positive output port 16, the third DC positive output port 20 and the fourth DC positive and negative output port 22 will work in the short circuit protection state; connect the current conversion switch 29 to the neutral position, and then to the rated position, make the positive rated contactor 9 and the negative rated contactor 23 work, the DC positive bus bar 10 in the detection test bench has the DC positive voltage of the rated working state, and the DC negative bus bar 26 has the DC negative voltage of the rated working state. At this time, the positive polarity DC power output to the first DC positive output port 12, the second DC positive output port 16, the third DC positive output port 20 and the fourth DC positive and negative output port 22 will work in the rated state.

[0077] ​When the short-circuit protection or rated passage operation is in progress, if the control switch 34 of the first DC contactor is turned on, the first DC contactor 11 is operated, the first DC output signal lamp 52 is lighted, and the first DC positive output port 12 has positive polarity DC voltage; if the control switch 35 of the second DC contactor is turned on, the second DC contactor 15 is operated, the second DC output signal lamp 61 is lighted, and the second DC positive output port 16 has positive polarity DC voltage; if the control switch 36 of the third DC contactor is turned on, the third DC contactor 19 is operated, the third DC output signal lamp 56 is lighted, and the third DC positive output port 20 has positive polarity DC voltage; if the control switch 37 of the fourth DC contactor is turned on, the fourth DC contactor 21 is operated, the fourth DC output signal lamp 58 is lighted, and the fourth DC positive output port 20 has positive polarity DC voltage.

[0078] When the short-circuit protection or rated passage operation is in progress, the DC positive busbar 10 in the test platform supplies power to the coil of the positive polarity interlocking relay 40, so that the positive polarity interlocking relay 40 is operated, its normally closed contact is opened, and the circuit from the emergency power-off switch 39 to the reverse polarity control switch 41 is cut off; at this time, if the reverse polarity control switch 41 is turned to the reverse polarity position again, the reverse polarity control relay 18 and the reverse polarity power supply relay 25 will not be operated, and the reverse polarity DC voltage will not be supplied to the first DC positive output port 12, the second DC positive output port 16, the positive terminal of the fourth DC positive and negative output port 22, and the negative terminal of the fourth DC positive and negative output port 22.

[0079] Before the reverse polarity power supply is carried out, the current switch 29 should be connected to the neutral position, and the reverse polarity control switch 41 is connected to make the reverse polarity control relay 18 and the reverse polarity power supply relay 25 work. At this time, the first reverse polarity switch 42 is connected, the first DC reverse polarity output signal lamp 55 is lighted, and the first DC positive output port 12 and the fourth DC positive and negative output port 22 negative end have reverse polarity DC; the second reverse polarity switch 43 is connected, the second DC reverse polarity output signal lamp 64 is lighted, and the second DC positive output port 16 and the fourth DC positive and negative output port 22 negative end have reverse polarity DC; the fourth reverse polarity switch 44 is connected, the fourth DC reverse polarity output signal lamp 59 is lighted, and the fourth DC positive and negative output port 22 positive end and negative end have reverse polarity DC. After the reverse polarity control relay 18 works, its normally closed contact is disconnected, and the circuit from the emergency power-off switch 39 to the current switch 29 neutral position is cut off. At this time, if the current switch 29 is connected to the short circuit prevention position or the rated position again, the positive polarity DC will not be output to the DC positive bus 10 and the DC negative bus 26, and the positive polarity DC will not be output to the DC positive bus 10 and the DC negative bus 26. At the same time, after the reverse polarity control relay 18 works, its other two normally closed contacts are disconnected, and the circuit for supplying power to the control switch 34 of the first DC contactor, the control switch 35 of the second DC contactor, the control switch 36 of the third DC contactor and the control switch 37 of the fourth DC contactor is cut off. At this time, if these switches are connected again, the first DC contactor 11, the second DC contactor 19, the third DC contactor 19 and the fourth DC contactor 21 will not work.

[0080] Although the embodiments of the present application are disclosed as above, the content is only the embodiment adopted for the purpose of understanding the present application, and is not used to limit the present application. Any person skilled in the art of the present application can make any modification and change in the implementation form and details without departing from the spirit and scope of the present application disclosed, but the patent protection scope of the present application should be subject to the scope defined by the appended claims.

Claims

1. A detection system for a DC power supply system of an aircraft, the DC power supply system of the aircraft having four on-board power sources, the power supply forms of which are: an emergency DC power supply provided by on-board left storage batteries (3) and right storage batteries (4), an auxiliary DC power supply provided by an on-board auxiliary DC generator (5), and a ground maintenance power supply provided by a ground DC power supply socket (6), characterized in that, The detection system for the first power supply of the aircraft DC power supply system comprises a ground DC power supply (1) and a detection test bench (2); the ground DC power supply (1) is electrically connected with four onboard power supply feeder ports in the aircraft DC power supply system through the detection test bench (2) to provide detection power supply for the aircraft DC power supply system; The detection test bench (2) is connected with the ground DC power supply (1) through a DC input port (7) arranged on one side of the detection test bench (2) and is connected with the four onboard power supply feeder ports in the aircraft DC power supply system through four DC power supply output ports arranged on the other side of the detection test bench (2); The positive terminal of the DC input port (7) is branched into four paths through a DC positive bus bar (10), and the four paths are connected to the positive terminals of the four DC power supply output ports through a DC contactor, respectively, to form a positive DC power supply circuit; The negative terminal of the DC input port (7) is connected with the negative terminal of one of the DC power supply output ports through a DC negative bus bar (26) to form a negative DC power supply circuit; The DC power supply circuit formed by the positive DC power supply circuit and the negative DC power supply circuit is used for positive polarity power supply to the four onboard power supplies in the aircraft DC power supply system.

2. The detection system for powering an aircraft DC power supply system of claim 1, wherein, The four DC power supply output ports are a first DC positive output port (12), a second DC positive output port (16), a third DC positive output port (20) and a fourth DC positive and negative output port (22); The positive terminal of the DC input port (7) is connected to the DC positive bus bar (10) through a rated fuse (8), a shunt of a DC input current meter, a positive rated contactor (9) or a positive anti-short circuit contactor (14), and is branched into four paths through the DC positive bus bar (10), wherein the first path is connected to the first DC positive output port (12) through a first DC contactor (11), the second path is connected to the second DC positive output port (16) through a second DC contactor (15), the third path is connected to the third DC positive output port (20) through a third DC contactor (19), and the fourth path is connected to the positive terminal of the fourth DC positive and negative output port (22) through a fourth DC contactor (21), so as to form a positive DC power supply circuit; The negative terminal of the DC input port (7) is connected to the DC negative bus bar (26) through a negative rated contactor (23) or a negative anti-short circuit contactor (24) and is connected to the negative terminal of the fourth DC positive and negative output port (22), so as to form a negative DC power supply circuit.

3. The detection system for power supply of an aircraft DC power system according to claim 2, characterized in that The detection system further comprises an inverse polarity control circuit, which comprises a DC control power supply circuit breaker (38), an emergency power-off switch (39) and an inverse polarity control relay (18) connected in series at the rear end of the rated fuse (8) and four DC contactor control switches for one-to-one corresponding control of the on-off states of the four DC contactors. Among them, the four paths of the back-end shunt of the 2-way normally closed contact of the reverse polarity control relay (18) are controlled by the first DC contactor control switch (34) to control the on-off state of the first DC contactor (11), the second DC contactor control switch (35) to control the on-off state of the second DC contactor (15), the third DC contactor control switch (36) to control the on-off state of the third DC contactor (19), and the fourth DC contactor control switch (37) to control the on-off state of the fourth DC contactor (21); The reverse polarity control circuit in series with the reverse polarity control relay (18) is used to turn on the reverse polarity control relay (18) when reverse polarity power supply is performed, and the 2-way normally closed contact is opened to cut off the power supply of the DC control power supply positive end in front of the four-way DC contactor control switch, thereby ensuring that the four-way DC contactor will not work all the time, that is, blocking the positive polarity DC power supply to the positive end of the four DC power output ports.

4. The detection system for power supply of an aircraft DC power system according to claim 3, characterized in that In the DC power supply circuit, the front end of the DC positive bus bar (10) and the DC negative bus bar (26) is provided with a current conversion circuit, and the conversion of the current conversion circuit is controlled by the DC control power supply circuit breaker (38), the emergency power-off switch (39), the 1-way normally closed contact of the reverse polarity control relay (18) and the current conversion switch (29). The current conversion circuit includes four parallel current paths, which are: In the first current path, the positive end of the DC input port (7) is connected to the DC positive bus bar (10) through the rated fuse (8), the shunt of the DC input current meter (51) and the positive rated contactor (9). In the second current path, the negative end of the DC input port (7) is connected to the DC negative bus bar (26) through the negative rated contactor (23). The first current path and the second current path form a positive polarity rated power supply circuit; In the third current path, the positive end of the DC input port (7) is connected to the DC positive bus bar (10) through the rated fuse (8), the shunt of the DC input current meter (51), the short-circuit protection circuit breaker (13) and the positive short-circuit protection contactor (14). In the fourth current path, the negative end of the DC input port (7) is connected to the DC negative bus bar (26) through the negative short-circuit protection contactor (24). The third current path and the fourth current path form a positive polarity short-circuit protection power supply circuit; The current conversion circuit is used to limit the total current of the first DC positive output port (12), the second DC positive output port (16), the third DC positive output port (20) and the fourth DC positive and negative output port (22) to 10A for protection when the first positive polarity power supply is performed on the aircraft. First, the positive polarity short-circuit protection power supply circuit is used to supply small current of 10A. After the on-board circuit is normal without short-circuit fault, the positive polarity rated power supply circuit is used to supply large current of 100A. The 1 normally closed contact of the reverse polarity control relay (18) in series in the current conversion circuit is connected, when the reverse polarity power supply is carried out, the normally closed contact of the reverse polarity control relay (18) is connected, and the normally closed contact is disconnected, so as to cut off the power supply of the positive end of the direct current control power supply in front of the middle point of the current conversion switch (29), so as to ensure that the positive rated contactor (9), the negative rated contactor (23), the positive anti short circuit contactor (14) and the negative anti short circuit contactor (24) will not work, that is, the power supply of the positive polarity direct current power supply to the direct current positive bus bar (10) and the direct current negative bus bar (26) is blocked.

5. The detection system for power supply of an aircraft DC power system according to claim 4, characterized in that In the direct current power supply circuit, the direct current input port (7) is connected to the first direct current positive output port (12), the second direct current positive output port (16) and the fourth direct current positive and negative output port (22) through the reverse polarity power supply circuit respectively; the reverse polarity power supply circuit comprises: reverse polarity fuse (17) and reverse polarity control relay (18) in series, and reverse polarity power supply relay (25); The positive end of the direct current input port (7) is connected to the direct current negative bus bar (26) through the rated fuse (8), the normally open contact of the reverse polarity control relay (18) in series, and is connected to the negative end of the fourth direct current positive and negative output port (22); the first direct current positive output port (12), the second direct current positive output port (16) and the fourth direct current positive and negative output port (22) are connected to the negative end of the direct current input port (7) through the normally open contact of the reverse polarity power supply relay (25) after the reverse polarity power supply relay (25) is connected to the negative end of the direct current input port (7); In the direct current power supply circuit, the reverse polarity power supply circuit is arranged to supply reverse polarity power to the three direct current power supplies on board to detect whether the reverse polarity monitoring circuit function of the three direct current power supplies on board is normal; when the reverse polarity power supply is carried out, the reverse polarity monitoring circuit of the corresponding three power supply on board should cut off the power supply to the aircraft, and the three power supplies on board are: left storage battery (3), right storage battery (4) and ground direct current power supply socket (6).

6. The detection system for power supply of an aircraft DC power system according to claim 5, characterized in that In the circuit of the detection test bench (2), the positive end of the direct current input port (7) is divided into two ways after the direct current control power supply positive end after the rated fuse (8) is connected to the direct current control power supply circuit breaker (38) and the emergency power-off switch (39), one way is the positive polarity control power supply positive end, and the other way is the reverse polarity control power supply positive end; The reverse polarity control power supply positive end is connected to the reverse polarity control relay (18) through the normally closed contact of the positive polarity interlocking relay (40) and the reverse polarity switch (41), and the reverse polarity power supply relay (25) is connected to the negative end of the direct current input port (7) through the positive polarity interlocking relay (40); so that the reverse polarity control relay (18) and the reverse polarity power supply relay (25) in the reverse polarity power supply circuit are controlled by the normally closed contact of the positive polarity interlocking relay (40) and the reverse polarity switch (41). When the positive polarity power supply, the positive polarity chain relay (40) is connected, its 1 way normally closed contact is disconnected, cutting off the front end of the DC control power supply positive polarity switch (41) power supply; At this time, even if the positive polarity switch (41) is connected, the reverse polarity control relay (18) and the reverse polarity power supply relay (25) will not work; The positive polarity DC power supply will not supply power to the DC negative bus bar (26) and the fourth DC positive and negative output port (22) negative end; The negative polarity DC power supply will not supply power to the first DC positive output port (12), the second DC positive output port (16), the fourth DC positive and negative output port (22) positive end.

7. The detection system for the power supply of the aircraft DC power supply system according to claim 6, wherein, The positive polarity control power supply positive end in the circuit of the detection test bench (2) is branched into 3 ways, respectively passing through the 1 way normally closed contact of the reverse polarity control relay (18), the circuit after the first way normally closed contact is connected to the middle point of the current conversion switch (29), used for controlling the on-off of the positive short circuit prevention contactor (14), the negative short circuit prevention contactor (24), the positive rated contactor (9) and the negative rated contactor (23); The circuit after the 2nd way normally closed contact is branched into 2 ways, respectively connected to the first DC contactor control switch (34) and the second DC contactor control switch (35), used for controlling the on-off of the first DC contactor (11) and the second DC contactor (15); The circuit after the 3rd way normally closed contact is branched into 2 ways, respectively connected to the third DC contactor control switch (36) and the fourth DC contactor control switch (37), used for controlling the on-off of the third DC contactor (19) and the fourth DC contactor (21).

8. The detection system for the power supply of the aircraft DC power supply system according to claim 7, wherein, The detection test bench (2) controls the on-off of the power supply circuit of the DC control power supply positive end connected to the front end of the first DC contactor control switch (34), the second DC contactor control switch (35), the third DC contactor control switch (36), the fourth DC contactor control switch (37), the current conversion switch (29) and the reverse polarity switch (41) through the emergency power-off switch (39) arranged; When an emergency danger occurs, the DC control power supply positive end power supply at the front end of the above-mentioned switch is disconnected by disconnecting the emergency power-off switch (39), so that the corresponding DC contactor or relay of the switch is disconnected, and the positive polarity DC power supply or the reverse polarity DC power supply for supplying power to the aircraft DC power supply system from the on-board power supply feeder port can be quickly cut off.

9. A detection system for powering an aircraft DC power supply system as claimed in any one of claims 6 to 8, characterised in that, A control panel (28) and a display panel (27) are further arranged on the shell of the detection test bench (2); The control panel (28) is provided with an independent emergency power-off switch (39) in an independent area; the control panel (28) is provided with a current switch (29) for controlling the positive short-circuit prevention contactor (14), the negative short-circuit prevention contactor (24), the positive rated contactor (9), the negative rated contactor (23), the control switch (34) and the first direct-current output signal lamp (52) of the first direct-current contactor, the control switch (35) and the second direct-current output signal lamp (61) of the second direct-current contactor, the control switch (36) and the third direct-current output signal lamp (56) of the third direct-current contactor, and the control switch (37) and the fourth direct-current output signal lamp (58) of the fourth direct-current contactor in a normal power supply area of the direct-current power supply system; the control panel (28) is provided with a reverse polarity control switch (41) for controlling the reverse polarity control relay (18) and the reverse polarity power supply relay (25), the first direct-current reverse polarity on-off switch (42) and the first direct-current reverse polarity output signal lamp (55), the second direct-current reverse polarity on-off switch (43) and the second direct-current reverse polarity output signal lamp (64), and the fourth direct-current reverse polarity on-off switch (44) and the fourth direct-current reverse polarity output signal lamp (59) in a reverse polarity power supply area of the direct-current power supply system. The display panel (27) is provided with a direct-current input signal lamp (48), a direct-current input voltmeter (49) and a direct-current input ammeter (50).

10. A method of detecting power supply of an aircraft DC power system, characterized in that, The detection method for the first power supply of the aircraft direct-current power supply system by using the detection system for the power supply of the aircraft direct-current power supply system according to any one of claims 6-9 comprises the following steps: Step 1, connecting the direct-current input port (7) of the detection test bench (2) with the ground direct-current power supply (1); Step 2, connecting the first direct-current positive output port (12) of the detection test bench (2) with the left storage battery (3) on the aircraft, the second direct-current positive output port (16) with the right storage battery (4) on the aircraft, the third direct-current positive output port (20) with the auxiliary direct-current generator (5) on the aircraft, and the fourth direct-current positive and negative output port (22) with the ground direct-current power supply socket (6) on the aircraft; Step 3, connecting the direct-current input port (7) of the detection test bench (2) with the ground direct-current power supply (1); Step 3, when detecting, first, the DC control power circuit breaker (38) and the emergency power-off switch (39) are turned on, the current conversion switch (29) is turned on in the anti-short circuit position, and the positive and negative two anti-short circuit DC power supply circuits are connected; by controlling the first DC contactor control switch (34), the second DC contactor control switch (35), the third DC contactor control switch (36), and the fourth DC contactor control switch (37), the first, second, third, and fourth DC circuits are connected, the left storage battery (3), the right storage battery (4), and the auxiliary DC generator (5) are simulated to work, and the ground DC power supply socket (6) is simulated to work, and whether the left storage battery (3), the right storage battery (4), the auxiliary DC generator (5), and the ground DC power supply socket (6) are normally powered in the anti-short circuit state of the on-board circuit is detected; when the left storage battery (3), the right storage battery (4), the auxiliary DC generator (5), and the ground DC power supply socket (6) are normally powered in the anti-short circuit state, the current conversion switch (29) is set in the rated position, and the rated power supply and working state of the aircraft DC power supply system are detected; Step 4, after the positive polarity power supply and working state detection of the aircraft DC power supply system is completed, the current conversion switch (29) is placed in the neutral position, the reverse polarity switch (41) is turned on, and then the first, second, and fourth reverse polarity switches are turned on, respectively, the left storage battery (3), the right storage battery (4), and the ground DC power supply socket (6) are simulated to work in reverse polarity, and whether the reverse polarity monitoring function of the left storage battery (3), the right storage battery (4), and the ground DC power supply socket (6) is normal is detected.

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