A portable aircraft ground power vehicle voltage rapid detection device

Abstract

This application provides a portable aircraft ground power vehicle voltage rapid detection device, belonging to the field of voltage detection technology. The device includes: a DC voltmeter A, a DC voltmeter B, a first switch K1, a second switch K2, a first pin, a second pin, a third pin, a fourth pin, a fifth pin, and a sixth pin. The third and sixth pins are connected by a first wire, and the first switch K1 is connected in series with the first wire. The fourth and fifth pins are connected by a second wire, and the second switch K2 is connected in series with the second wire. The first terminal of DC voltmeter A is connected to the first pin, and the second terminal of DC voltmeter A is connected to the first switch K1 and the third pin. The first terminal of DC voltmeter B is connected to the first switch K1 and the third pin, and the second terminal of DC voltmeter B is connected to the second pin. Voltage values ​​can be quickly obtained from DC voltmeters A and B.

Description

Technical Field

[0001] This utility model belongs to the field of voltage detection technology, and in particular relates to a portable aircraft ground power vehicle voltage rapid detection device. Background Technology

[0002] Aircraft ground power vehicles are core equipment for aircraft ground support. They are primarily used to provide stable power to onboard avionics systems, flight control systems, and environmental control equipment when engines are shut down, ensuring the continued operation of all critical aircraft systems. This equipment plays a vital role in aircraft maintenance, repair, and flight operations, providing reliable power for rapid aircraft sorties, ground readiness, and routine maintenance, significantly improving the operational readiness efficiency and continuous support capabilities of aviation equipment.

[0003] Before using an aircraft ground power vehicle to supply power to an aircraft, it is usually necessary to check whether the voltage is within the specified range. When an aircraft is rapidly launching, there are high requirements for the measurement efficiency, accuracy, reliability, and portability of the ground power vehicle.

[0004] Traditional handheld multimeters have many limitations in practical applications. Their measurement process is easily affected by the operator's skill level, leading to reading errors and low measurement efficiency. Furthermore, unreliable connections and a high risk of electric shock make it difficult to complete measurement tasks stably, accurately, and quickly.

[0005] Therefore, this utility model provides a portable aircraft ground power vehicle voltage rapid measurement device. Utility Model Content

[0006] This invention provides a portable aircraft ground power vehicle voltage rapid detection device to at least solve the problems of slow measurement speed, unreliable connection, poor anti-interference ability, high risk of electric shock, and difficulty in stable, accurate and rapid measurement by traditional handheld multimeters in the prior art.

[0007] The portable aircraft ground power vehicle voltage rapid detection device includes: DC voltmeter A, DC voltmeter B, first switch K1, second switch K2, first pin, second pin, third pin, fourth pin, fifth pin, and sixth pin.

[0008] The first pin, the second pin, the third pin, the fourth pin, the fifth pin, and the sixth pin are all used to connect to the ground power vehicle of the aircraft under test;

[0009] The third pin and the sixth pin are connected by a first wire, and the first switch K1 is connected in series with the first wire;

[0010] The fourth pin and the fifth pin are connected by a second wire, and the second switch K2 is connected in series with the second wire;

[0011] The first terminal of the DC voltmeter A is connected to the first pin, and the second terminal of the DC voltmeter A is connected to the first switch K1 and the third pin;

[0012] The first terminal of the DC voltmeter B is connected to the first switch K1 and the third pin, and the second terminal of the DC voltmeter B is connected to the second pin.

[0013] Furthermore, the first pin, the second pin, and the third pin are all power supply pins.

[0014] Furthermore, the fourth pin, the fifth pin, and the sixth pin are all shorting pins.

[0015] Furthermore, the DC voltmeter A is a 28V DC voltmeter used to display a 28V DC voltage.

[0016] Furthermore, the DC voltmeter B is a 56V DC voltmeter used to display a 56V DC voltage.

[0017] Furthermore, the voltage rapid detection device also includes a housing;

[0018] The DC voltmeter A, DC voltmeter B, first switch K1, second switch K2, first pin, second pin, third pin, fourth pin, fifth pin, and sixth pin are all integrated on the housing.

[0019] Furthermore, the first pin, the second pin, the third pin, the fourth pin, the fifth pin, and the sixth pin are all made of copper.

[0020] Furthermore, the outer casing is made of insulating material.

[0021] As can be seen from the above technical solutions, this utility model has the following advantages:

[0022] The measurement process is greatly simplified. Simply insert the pin of the voltage rapid detection device into the socket of the aircraft ground power vehicle, turn on the first switch K1 and the second switch K2, and you can intuitively and quickly obtain the voltage value on DC voltmeter A and DC voltmeter B.

[0023] By connecting the pins to the sockets of the aircraft ground power vehicle, compared with the traditional method of short-circuiting wires and measuring with multimeter probes, the connection is more secure and reliable, eliminating voltage misjudgment caused by human error and reducing the risk of electric shock at the source, thus significantly improving work safety.

[0024] DC voltmeter A and DC voltmeter B display the measured voltage value intuitively in digital form, making it easy to understand, reducing reading errors, and improving measurement efficiency. Attached Figure Description

[0025] To more clearly illustrate the technical solution of this application, the accompanying drawings used in the description will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0026] Figure 1 This is a circuit diagram of a portable aircraft ground power vehicle voltage rapid detection device.

[0027] Figure 2 This is a structural diagram of a portable aircraft ground power vehicle voltage rapid detection device.

[0028] Figure 3 This is a diagram showing the operational status of the portable aircraft ground power vehicle voltage rapid detection device.

[0029] Figure 4 A side view of a portable aircraft ground power vehicle voltage rapid detection device.

[0030] Reference numerals: 1-First pin; 2-Second pin; 3-Third pin; 4-Fourth pin; 5-Fifth pin; 6-Sixth pin; 7-Housing casing. Detailed Implementation

[0031] To make the purpose, features, and advantages of this application more apparent and understandable, specific embodiments and accompanying drawings will be used to clearly and completely describe the technical solution protected by this application. Obviously, the embodiments described below are only some embodiments of this application, and not all embodiments. Based on the embodiments in this patent, all other embodiments obtained by those skilled in the art without inventive effort are within the scope of protection of this patent.

[0032] Various embodiments of this disclosure will be described more fully in the following detailed description of the portable aircraft ground power vehicle voltage rapid detection device. This disclosure may have various embodiments, and adjustments and changes may be made therein. However, it should be understood that there is no intention to limit the various embodiments of this disclosure to the specific embodiments disclosed herein, but rather this disclosure should be understood to cover all adjustments, equivalents, and / or alternatives falling within the spirit and scope of the various embodiments of this disclosure.

[0033] In the following, the terms “comprising” or “may include”, which may be used in various embodiments of this disclosure, indicate the presence of the disclosed functions, operations, or elements, and do not limit the addition of one or more functions, operations, or elements. Furthermore, as used in various embodiments of this disclosure, the terms “comprising,” “having,” and their cognates are intended only to indicate a particular feature, number, step, operation, element, component, or combination of the foregoing, and should not be construed as primarily excluding the presence of one or more other features, numbers, steps, operations, elements, components, or combinations of the foregoing, or the possibility of adding one or more combinations of the foregoing.

[0034] In various embodiments of this disclosure, the expression "or" or "at least one of A and / or B" includes any combination or all combinations of the words listed simultaneously. For example, the expression "A or B" or "at least one of A and / or B" may include A, may include B, or may include both A and B.

[0035] The terms used in the various embodiments of this disclosure (such as "first," "second," etc.) may modify various components in the various embodiments, but do not limit the corresponding components. For example, the above terms do not limit the order and / or importance of the components. The above terms are only used for the purpose of distinguishing one component from others. For example, a first user device and a second user device refer to different user devices, although both are user devices. For example, a first component may be referred to as a second component without departing from the scope of the various embodiments of this disclosure, and similarly, a second component may also be referred to as a first component.

[0036] It should be noted that if a description is made of "connecting" one component to another, then the first component can be directly connected to the second component, and a third component can be "connected" between the first and second components. Conversely, when a component is "directly connected" to another component, it can be understood that there is no third component between the first and second components.

[0037] The term "user" as used in various embodiments of this disclosure may refer to a person using an electronic device, and may be a monitoring person, a testing person, or an operator.

[0038] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0039] This application provides a portable aircraft ground power vehicle voltage rapid detection device, which focuses on improving measurement speed, ensuring measurement accuracy, and reducing operational risks. The design principles are formulated from multiple dimensions such as portability, reliability, safety, and efficiency. It solves the technical problems that currently urgently need to realize the slow measurement speed, unreliable connection, poor anti-interference ability, high risk of electric shock, and difficulty in stable, accurate and rapid measurement of traditional handheld multimeters.

[0040] The technical solutions proposed in the embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0041] Figure 1 A circuit diagram of a portable aircraft ground power vehicle voltage rapid detection device provided in this application embodiment; Figure 2 A structural diagram of a portable aircraft ground power vehicle voltage rapid detection device provided in this application embodiment; Figure 3 A diagram illustrating the operational status of a portable aircraft ground power vehicle voltage rapid detection device. Figure 4 This is a side view of a portable aircraft ground power vehicle voltage rapid detection device. Figures 1 to 4 As shown in the embodiment of this application, a portable aircraft ground power vehicle voltage rapid detection device specifically includes:

[0042] The voltage rapid detection device includes: DC voltmeter A, DC voltmeter B, first switch K1, second switch K2, first pin 1, second pin 2, third pin 3, fourth pin 4, fifth pin 5, and sixth pin 6.

[0043] The first pin 1, the second pin 2, the third pin 3, the fourth pin 4, the fifth pin 5, and the sixth pin 6 are all used to connect to the ground power vehicle of the aircraft under test;

[0044] The third pin 3 and the sixth pin 6 are connected by a first wire, and the first switch K1 is connected in series with the first wire; this is used to control the circuit short circuit.

[0045] The fourth pin 4 and the fifth pin 5 are connected by a second wire, and the second switch K2 is connected in series with the second wire; this is used to control the circuit short circuit.

[0046] The first terminal of the DC voltmeter A is connected to the first pin 1, and the second terminal of the DC voltmeter A is connected to the first switch K1 and the third pin 3;

[0047] The first terminal of the DC voltmeter B is connected to the first switch K1 and the third pin 3, and the second terminal of the DC voltmeter B is connected to the second pin 2.

[0048] The DC voltmeter A is a 28V DC voltmeter used to display a 28V DC voltage. The DC voltmeter B is a 56V DC voltmeter used to display a 56V DC voltage.

[0049] When the first switch K1 is closed, the third pin 3 and the sixth pin 6 are short-circuited. At this time, both DC voltmeter A and DC voltmeter B display a DC voltage of 28V. Then, when the second switch K2 is closed, the fourth pin 4 and the fifth pin 5 are short-circuited. At this time, DC voltmeter A displays a DC voltage of 28V, and DC voltmeter B displays a DC voltage of 56V.

[0050] It should be noted that the first switch K1 is turned on first and then off, while the second switch K2 is turned on last and then off.

[0051] In an exemplary embodiment, the first pin 1, the second pin 2, and the third pin 3 are all power supply pins.

[0052] According to another embodiment of the present invention, the fourth pin 4, the fifth pin 5 and the sixth pin 6 are all shorting pins.

[0053] Furthermore, as a refinement and extension of the specific implementation of the above embodiments, in order to fully illustrate the specific implementation process in this embodiment, another portable aircraft ground power vehicle voltage rapid detection device is provided, the voltage rapid detection device further includes a housing 7;

[0054] It should be noted that the DC voltmeter A, DC voltmeter B, first switch K1, second switch K2, first pin 1, second pin 2, third pin 3, fourth pin 4, fifth pin 5, and sixth pin 6 are all integrated on the housing 7.

[0055] It should be further noted that the first pin 1, the second pin 2, the third pin 3, the fourth pin 4, the fifth pin 5, and the sixth pin 6 are all made of copper.

[0056] As an example, the outer casing 7 is made of an insulating material.

[0057] The above description of the disclosed embodiments enables those skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

[0058] For those skilled in the art, designing different forms of control circuits based on the teachings of this invention does not require creative effort. Changes, modifications, substitutions, and variations made to the embodiments without departing from the principles and spirit of this invention still fall within the protection scope of this invention.

Claims

1. A portable airplane ground power unit voltage quick detection device, characterized in that, The voltage rapid detection device includes: DC voltmeter A, DC voltmeter B, first switch K1, second switch K2, first pin (1), second pin (2), third pin (3), fourth pin (4), fifth pin (5), and sixth pin (6); The first pin (1), the second pin (2), the third pin (3), the fourth pin (4), the fifth pin (5) and the sixth pin (6) are all used to connect to the ground power vehicle of the aircraft under test; The third pin (3) and the sixth pin (6) are connected by a first wire, and the first switch K1 is connected in series on the first wire; The fourth pin (4) and the fifth pin (5) are connected by a second wire, and the second switch K2 is connected in series on the second wire; The first end of the DC voltmeter A is connected to the first pin (1), and the second end of the DC voltmeter A is connected to the first switch K1 and the third pin (3). The first end of the DC voltmeter B is connected to the first switch K1 and the third pin (3), and the second end of the DC voltmeter B is connected to the second pin (2).

2. The portable aircraft ground power unit voltage quick detection device of claim 1, wherein, The first pin (1), the second pin (2) and the third pin (3) are all power supply pins.

3. The portable aircraft ground power unit voltage quick detection device of claim 2, wherein, The fourth pin (4), the fifth pin (5), and the sixth pin (6) are all shorting pins.

4. The portable aircraft ground power unit voltage quick detection device of claim 3, wherein, The DC voltmeter A is a 28V DC voltmeter used to display 28V DC voltage.

5. The portable aircraft ground power unit voltage quick detection device of claim 4, wherein, The DC voltmeter B is a 56V DC voltmeter used to display a 56V DC voltage.

6. The portable aircraft ground power vehicle voltage rapid detection device as described in claim 5, characterized in that, The voltage rapid detection device also includes a housing (7); The DC voltmeter A, DC voltmeter B, first switch K1, second switch K2, first pin (1), second pin (2), third pin (3), fourth pin (4), fifth pin (5), and sixth pin (6) are all integrated on the housing (7).

7. The portable aircraft ground power vehicle voltage rapid detection device as described in claim 6, characterized in that, The first pin (1), the second pin (2), the third pin (3), the fourth pin (4), the fifth pin (5) and the sixth pin (6) are all made of copper.

8. The portable aircraft ground power vehicle voltage rapid detection device as described in claim 7, characterized in that, The outer casing (7) is made of insulating material.

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