Aircraft power supply system simulation detection device

Abstract

An aircraft power supply system simulation detection device comprises two pins, a housing, a boost template, a power supply, a signal sending unit and a power switch. The boosting template, the power supply and the signal transmitting unit are respectively arranged in the shell; one end of the contact pin is fixed in the shell and is connected with the signal transmitting unit and the power switch through a cable; the other end of the contact pin is used for being connected with external 400Hz ground power supply equipment; the signal transmitting unit is respectively connected with the boosting template and the power supply and is used for outputting a 28V direct current signal; and the boosting template is connected with the power supply and is used for boosting an input signal and then outputting the input signal. According to the utility model, 28VDC is output by simulating an aircraft power supply system, and is transmitted to a 400Hz ground power supply through a pin and a power plug N / F interface, so that whether the 400Hz ground power supply equipment feeds back the 28VDC normally can be detected.

Description

Technical Field

[0001] The utility model relates to the technical field of power equipment detection, in particular to an aircraft power system simulation detection device. Background Art

[0002] The 400Hz ground power supply is a power equipment used for ground power transmission, which can convert alternating current into direct current and stably output, and is widely used in the fields such as aviation to ensure the normal operation of aircraft.

[0003] At present, to detect whether the 400Hz ground power supply is normal, the 28VDC output by the power system of the aircraft is connected to the 400Hz ground power supply, and the feedback fault simulation is required to complete the detection of the 400Hz ground power supply, which causes waste of aircraft resources and also affects the operation of the aircraft to a certain extent. Content of the Utility Model

[0004] In order to solve the deficiencies of the existing technology, the purpose of the utility model is to provide an aircraft power system simulation detection device, which can simulate the aircraft power system, and when connected to the 400Hz ground power supply, can restore the 28VDC feedback fault simulation in a 1:1 ratio, and can complete the detection of the 400Hz ground power supply without connecting to the aircraft.

[0005] To achieve the above purpose, the aircraft power system simulation detection device provided by the present application includes: two pins, a housing, a boost template, a power supply, a signal sending unit, and a power switch;

[0006] The boost template, the battery and the signal sending unit are respectively arranged inside the housing;

[0007] One end of the two pins is fixed inside the housing and is connected to the signal sending unit and the power switch through a cable; the other end of the two pins is used to connect to an external 400Hz ground power supply device;

[0008] The signal sending unit is respectively connected to the boost template and the power supply, and is used to output a 28V direct current signal;

[0009] The boost template is connected to the power supply and outputs after boosting the input signal.

[0010] Further, a partition is also arranged between the power supply and the boost module.

[0011] Further, the power switch is arranged on the housing and is respectively connected to one of the pins and the signal sending unit through a cable.

[0012] Furthermore, it further includes: a DC power supply, a first capacitor, a second capacitor, a third capacitor, a first resistor, a second resistor, a third resistor, a first diode, a second diode, a third diode, a first triode, a second triode, a third triode, and a transformer;

[0013] The positive pole of the DC power supply is respectively connected to one end of the first capacitor, the first resistor, the second capacitor, the third capacitor, the collector of the second triode, and the negative pole of the third diode;

[0014] The other end of the first capacitor is connected to the negative pole of the DC power supply. The other end of the first resistor is respectively connected to the positive pole of the first diode and the base of the first triode. The negative pole of the first diode is connected to the collector of the third triode. The other end of the second capacitor is respectively connected to the collector of the first triode and one end of the second resistor. The emitter of the first triode is connected to the negative pole of the DC power supply;

[0015] The other end of the second resistor is connected to one end of the primary coil of the transformer. The other end of the primary coil of the transformer is connected to the base of the second triode. One end of the secondary coil of the transformer is connected to the negative pole of the DC power supply. The other end of the secondary coil of the transformer is connected to the emitter of the second triode and the negative pole of the second diode. The positive pole of the second diode is connected to the emitter of the third triode. The base of the third triode is connected to the positive pole of the third diode and one end of the third resistor. The other ends of the third resistor and the third capacitor are both connected to the negative pole of the DC power supply. The two ends of the third capacitor serve as the positive and negative poles of the pin.

[0016] The aircraft power supply system simulation detection device of the present application has the following beneficial effects compared with the prior art:

[0017] By simulating the aircraft power supply system to output 28VDC, and transmitting it to the 400Hz ground power supply through the pin and the power plug N / F interface, it can detect whether the feedback of the 400Hz ground power supply device to 28VDC is normal, and the detection of the 400Hz ground power supply device can be completed without docking the aircraft.

[0018] Other features and advantages of the present application will be described in the subsequent description, and part of them will become obvious from the description, or will be understood by implementing the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] The drawings are used to provide a further understanding of the present application, and constitute a part of the specification. Together with the embodiments of the present application, they are used to explain the present application, and do not constitute a limitation to the present application. In the drawings:

[0020] Figure 1Schematic structural diagram of an aircraft power supply system simulation device according to the present utility model;

[0021] Figure 2 Schematic circuit diagram of an aircraft power supply system simulation and detection device according to an embodiment of the present utility model. Detailed implementation manners

[0022] The following describes the preferred embodiments of the present application with reference to the accompanying drawings. It should be understood that the preferred embodiments described herein are only for the purpose of illustration and explanation of the present application, and are not used to limit the present application.

[0023] The embodiments of the present application will be described in more detail below with reference to the accompanying drawings. Although some embodiments of the present application are shown in the drawings, it should be understood that the present application can be implemented in various forms and should not be construed as limited to the embodiments set forth herein. On the contrary, these embodiments are provided to more thoroughly and completely understand the present application. It should be understood that the drawings and embodiments of the present application are only for exemplary purposes and are not used to limit the protection scope of the present application.

[0024] The term "including" and its variations used herein are open-ended, that is, "including but not limited to". The term "based on" means "at least partially based on". The term "one embodiment" means "at least one embodiment"; the term "another embodiment" means "at least one additional embodiment"; the term "some embodiments" means "at least some embodiments". The relevant definitions of other terms will be given in the following description.

[0025] In the drawings, some structural or method features are shown in a specific arrangement and / or order. However, it should be understood that such a specific arrangement and / or order may not be required. In some embodiments, these features may be arranged in a manner and / or order different from that shown in the illustrative drawings. Additionally, the inclusion of a structural or method feature in a particular figure does not imply that such a feature is required in all embodiments, and in some embodiments, such a feature may not be included or may be combined with other features.

[0026] It should be understood that although the terms "first", "second", etc. may be used herein to describe various units or data, these units or data should not be limited by these terms. These terms are only used to distinguish one feature from another. For example, without departing from the scope of the exemplary embodiments, the first feature may be referred to as the second feature, and similarly, the second feature may be referred to as the first feature.

[0027] It should be noted that the modifiers "one" and "multiple" mentioned in this application are illustrative rather than restrictive. Those skilled in the art should understand that unless clearly specified otherwise in the context, it should be understood as "one or more". "Multiple" should be understood as two or more.

[0028] To make the purpose, technical solutions, and advantages of this application clearer, the following will further describe the implementation manners of this application in detail with reference to the accompanying drawings.

[0029] In the description of this application, it should be understood that the orientation or positional relationships indicated by terms such as "upper", "lower", "one side", "top", "inner", "front", "both ends", etc. may be the orientation or positional relationships based on the orientation or positional relationships shown in the accompanying drawings. It is only for the convenience of describing this utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it should not be construed as a limitation to this utility model.

[0030] In this application, unless otherwise clearly specified and defined, terms such as "installed", "set", "connected", "fixed", etc. should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or integrated; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium. It can be the communication inside two elements or the interaction relationship between two elements. Unless otherwise clearly defined, for those of ordinary skill in the art, the specific meanings of the above terms in this utility model can be understood according to specific situations.

[0031] In an embodiment of this utility model, a simulation detection device for an aircraft power supply system is provided, including: a boost template, a signal sending unit, a connection cable, a pin, and a housing, which can simulate a 28V feedback signal of an aircraft. When maintenance personnel are maintaining 400Hz ground power supply equipment, they can directly connect this 28V feedback detector to the N / F interface of the 400Hz ground power supply plug to detect the normality of the 28V feedback signal of the 400Hz ground power supply equipment, shorten the maintenance time, and avoid directly connecting to the aircraft for detection and damaging the internal control elements of the aircraft, resulting in significant economic losses.

[0032] Figure 1 For the structural schematic diagram of the simulation detection device for an aircraft power supply system according to this utility model, as Figure 1 shown, the simulation detection device for an aircraft power supply system of this utility model includes: a pin 1, a housing 2, a boost template 3, a cable 4, a battery 5, a partition 6, a cable 7, a signal sending unit 8, and a power switch 9.

[0033] The boost template 3, cable 4, battery 5, partition 6, cable 7, and signal transmission unit 8 are all arranged inside the housing 2. One end of the pin 1 passes through the housing 2 and is connected to the signal transmission unit 8 and the power switch 9 (ON / OFF) through the cable 7. The other end (pin part) of the pin 1 is used to connect to the 400Hz ground power plug. The signal transmission unit 8 is respectively connected to the boost template 3 and the power supply 5 (in this embodiment, a 9VDC non-rechargeable power supply is used) and is used to output a 28V feedback signal. The boost template 3 is used to boost the 9VDC voltage to a 28VDC signal. The cable 4 refers to the signal transmission cable between internal structures, and no special description is made for this in the present utility model.

[0034] In this embodiment, a partition 6 is arranged inside the housing 2 to isolate and install the battery and the boost module (in this embodiment, the partition 6 is made of polyurethane sponge).

[0035] In this embodiment, in order to implement the aircraft power system simulation detection device, a dry battery is used to provide input power supply for the boost module. The boost module gets powered and works, and is converted into an output of 28VDC (direct current) through an internal amplification circuit. Then, two wires (the pin 1 in this embodiment) are used. One end of the wires is respectively connected to the positive and negative poles of the output 28VDC, and the other end of the wires is respectively connected to the plug ends N and F of the power supply device for connection testing, that is, to simulate the 28V direct current of the aircraft and test whether the N and F lines of the plug ends of the 400Hz ground power supply device are normal and there is no open circuit situation, so as to avoid the power supply device causing the aircraft to malfunction.

[0036] In this embodiment, the boost module 3 adopts an existing boost circuit and uses electronic components such as a bootstrap boost diode and a bootstrap boost capacitor to superimpose the capacitor discharge voltage and the power supply voltage, thereby increasing the voltage (for example, using a capacitor and a diode, where the capacitor stores charge and the diode prevents current backflow. When the frequency is relatively high, the voltage of the boost circuit is the sum of the input voltage of the circuit and the voltage on the capacitor, playing a role in boosting the voltage).

[0037] Figure 2 For the circuit structure schematic diagram of the aircraft power system simulation detection device according to the embodiment of the present utility model, as Figure 2As shown, the positive electrode of 9VDC (DC power supply) is respectively connected to capacitor C1, resistor R1, one end of capacitor C2 and capacitor C3, as well as the collector of transistor V2 and the negative electrode of diode D3; the other end of capacitor C1 is connected to the negative electrode of 9VDC; the other end of resistor R1 is respectively connected to the positive electrode of diode D1 and the base of transistor V1; the negative electrode of diode D1 is connected to the collector of transistor V3; the other end of capacitor C2 is respectively connected to the collector of transistor V1 and one end of resistor R2; the emitter of transistor V1 is connected to 9VDC. The negative pole of VDC, the other end of resistor R2 is connected to one end of transformer T1 (primary coil), the other end of transformer T1 is connected to the base of transistor V2, one end of transformer T2 (secondary coil) is connected to the negative pole of 9VDC, the other end of transformer T2 is connected to the emitter of transistor V2 and the negative pole of diode D2, the positive pole of diode D2 is connected to the emitter of transistor V3, the base of transistor V3 is connected to the positive pole of diode D3 and one end of resistor R3, and the other ends of resistor R3 and capacitor C3 are connected to the negative pole of 9VDC. Use the two ends of capacitor C3 as the positive and negative outputs of pin 1 to detect the target power supply device.

[0038] The working principle of the aircraft power system simulation detection device of the utility model is as follows:

[0039] The 400Hz ground power plug is connected to the pin 1, the power switch 9 is turned on, the battery 5 outputs a 9VDC voltage, which is converted and output to a 28VDC voltage after the cable 7 and the amplification circuit and the boost circuit inside the boost template 3 work. The 28VDC voltage signal is output by the signal sending unit 8, and is transmitted to the 400Hz ground power supply through the pin 1 and the power plug N / F interface, so as to detect whether the 400Hz ground power supply equipment is normal in feedback of 28VDC. If the plug end N and F lines of the 400Hz ground power supply equipment are connected normally, the green LED indicator of the power plug lights up normally, indicating that this feedback function is normal, and the aircraft can switch to use the ground power supply equipment. On the contrary, the possible reasons why the LED green indicator light cannot light up normally are that the connection cable is broken, the LED green indicator light is damaged, or there is no 28V DC, which causes the aircraft to be unable to switch to use the power supply equipment. Through the aircraft power supply system simulation detection device of the utility model, the troubleshooting inspection process and troubleshooting time can be shortened, and the aircraft docking bridge can be avoided. Due to the high position, the power supply equipment cannot be checked in time.

[0040] The aircraft power supply system simulation detection device proposed by the utility model fills the gap in the industry and has broad application prospects in places such as civil aviation airports using 400Hz ground power supply.

[0041] Those of ordinary skill in the art will understand that the foregoing is only a preferred embodiment of the present application and is not intended to limit the present application. Although the present application has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or perform equivalent replacements for some of the technical features. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present application shall be included within the protection scope of the present application.

Claims

1. An aircraft power system simulation detection device, characterized in that: include: Two pins, housing, booster template, power supply, signal sending unit, and power switch; The boost template, the power supply and the signal sending unit are respectively arranged inside the housing; One end of the two pins is fixed in the housing and connected to the signal sending unit and the power switch through a cable; the other ends of the two pins are used to connect to an external 400Hz ground power supply device; The signal sending unit is connected to the boost template and the power supply respectively, and is used to output a 28V DC signal; The boost template is connected to the power supply and outputs the input signal after boosting it.

2. The aircraft power system simulation detection device according to claim 1, characterized in that: Also included is a partition disposed between the power source and the boost module.

3. The aircraft power system simulation detection device according to claim 1, characterized in that: The power switch is arranged on the housing and is respectively connected to one of the pins and the signal sending unit through a cable.

4. The aircraft power system simulation detection device according to claim 1, characterized in that: Also includes: A DC power supply, a first capacitor, a second capacitor, a third capacitor, a first resistor, a second resistor, a third resistor, a first diode, a second diode, a third diode, a first transistor, a second transistor, a third transistor, and a transformer; The positive electrode of the DC power supply is respectively connected to the first capacitor, the first resistor, one end of the second capacitor, the third capacitor, the collector of the second transistor, and the negative electrode of the third diode; The other end of the first capacitor is connected to the negative electrode of the DC power supply, the other end of the first resistor is respectively connected to the positive electrode of the first diode and the base of the first transistor, the negative electrode of the first diode is connected to the collector of the third transistor, the other end of the second capacitor is respectively connected to the collector of the first transistor and one end of the second resistor, and the emitter of the first transistor is connected to the negative electrode of the DC power supply; The other end of the second resistor is connected to one end of the primary coil of the transformer, the other end of the primary coil of the transformer is connected to the base of the second transistor, one end of the secondary coil of the transformer is connected to the negative electrode of the DC power supply, the other end of the secondary coil of the transformer is connected to the emitter of the second transistor and the negative electrode of the second diode, the positive electrode of the second diode is connected to the emitter of the third transistor, the base of the third transistor is connected to the positive electrode of the third diode and one end of the third resistor, the other ends of the third resistor and the third capacitor are both connected to the negative electrode of the DC power supply, and the two ends of the third capacitor serve as the positive and negative electrodes of the pin.

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