A testing device for aircraft independent power supply components

Abstract

This utility model discloses a testing device for an aircraft independent power supply component, including connection terminals, a test circuit, and test terminals. The connection terminals are electrically connected to the independent power supply component to be tested, and the test terminals are electrically connected to the connection terminals through the test circuit. The test circuit includes a whole-machine test circuit and a charger test circuit. The whole-machine test circuit includes a whole-machine power input circuit, a power monitoring circuit, a load monitoring circuit, and a load access test circuit. The load access test circuit includes several load test branches. The charger test circuit includes a charger power input circuit, a simulated battery load circuit, and several test lines. Testers can quickly connect the connection terminals to the rear connector of the independent power supply component under test using a unified interface and perform various tests through the connection terminals. In addition, the charger test circuit can also simulate an uncharged battery to test the charger of the independent power supply component.

Description

Technical Field

[0001] This utility model relates to aircraft component testing devices, and more particularly to an aircraft independent power supply component testing device. Background Technology

[0002] The purpose of an aircraft independent power unit is to provide power to designated avionics equipment during normal aircraft operation and to charge its own internal nickel-cadmium batteries. In the event of a power failure, it can provide power to designated avionics equipment for at least 10 minutes using its own internal nickel-cadmium batteries.

[0003] Because the testing and troubleshooting of aircraft independent power supply components requires power input and monitoring of voltage and current feedback at various points under different conditions to ensure they meet the numerical requirements in the manufacturer's maintenance manual, and to quickly locate the faulty circuit when requirements are not met, current testing equipment for aircraft independent power supply components has overly complex wiring. Testers must manually lead test cables from the pins of the rear connector to perform short-circuiting, power supply, and measurement operations simulating test bench functions. This requires highly skilled operators, results in low testing efficiency, lacks error prevention mechanisms, and leads to serious consequences from incorrect wiring. Therefore, a test box needs to be developed that satisfies both safety and efficiency requirements, avoids human error caused by repeated wiring, and allows testing and troubleshooting of aircraft independent power supply components entirely according to the manufacturer's maintenance manual requirements. Utility Model Content

[0004] In view of the above-mentioned shortcomings of the current testing methods for aircraft independent power components, this utility model provides a testing device for aircraft independent power components, which can reduce the difficulty of testing aircraft independent power components and improve the testing efficiency.

[0005] To achieve the above objectives, the embodiments of this utility model adopt the following technical solutions:

[0006] An aircraft independent power supply component testing device includes connection terminals, a test circuit, and test terminals. The connection terminals are electrically connected to the independent power supply component to be tested, and the test terminals are electrically connected to the connection terminals via the test circuit. The test circuit includes an overall aircraft test circuit and a charger test circuit. The overall aircraft test circuit includes an overall aircraft power input circuit, a power monitoring circuit, a load monitoring circuit, and a load access test circuit. The load access test circuit includes several load test branches. Light-emitting diodes are connected in series on the load test branches. A power switch is connected in series on the overall aircraft power input circuit. A load switch is connected in series on the load monitoring circuit. The charger test circuit includes a charger power input circuit, a simulated battery load circuit, and several test lines. Several load resistors are connected in series on the simulated battery load circuit.

[0007] According to one aspect of the present invention, the power monitoring circuit includes a power monitoring main line and a power monitoring feeder; the load monitoring circuit includes a load monitoring main line and a load monitoring feeder; and the load access test circuit includes a load access test feeder.

[0008] According to one aspect of the present invention, the power input circuit of the charger includes a positive branch, a negative branch, and a temperature simulation branch; the simulated battery load circuit is connected in parallel between the positive branch and the negative branch.

[0009] According to one aspect of this utility model, a diode is connected in series in the power input circuit of the charger.

[0010] According to one aspect of the present invention, the detection circuit includes a heater monitoring circuit and a simulated battery status monitoring circuit.

[0011] According to one aspect of this utility model, a control switch is connected in series on the load access test feeder.

[0012] According to one aspect of the present invention, a current-limiting resistor and a diode are connected in series on the load test branch.

[0013] According to one aspect of the present invention, the connection terminal includes a first connection terminal and a second connection terminal; the first connection terminal is connected to the whole machine test circuit; and the second connection terminal is connected to the charger test circuit.

[0014] According to one aspect of this utility model, it also includes a housing and a test panel; the connection terminals, test terminals, power switch, load switch, light-emitting diode and control switch are disposed on the panel.

[0015] Advantages of this utility model:

[0016] The necessary circuit connections for testing are integrated, and test terminals are led out and placed on the test panel. Testers can quickly connect the testing device to the rear connector of the power supply component under test through a standard interface, avoiding wiring errors. Power can be supplied and instruments can be measured through the wiring ports on the test panel. The status of the power supply component can be judged by the indicator lights. Quick operation can be performed through the switches on the panel. The internal circuit simulates the load of a rechargeable battery to test the charger. The overall test circuit and the charger test circuit are independent of each other and do not interfere with each other, resulting in higher testing efficiency and safety. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments of this utility model, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0018] Figure 1 This is a schematic diagram of the structure of the test panel described in this utility model;

[0019] Figure 2 This is a schematic diagram of the overall testing circuit of this utility model;

[0020] Figure 3 This is a schematic diagram of the charger test circuit described in this utility model. Detailed Implementation

[0021] 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.

[0022] like Figure 1 , Figure 2 and Figure 3 As shown, an aircraft independent power supply component testing device includes a connection terminal, a test circuit, and a test terminal. The connection terminal is electrically connected to the independent power supply component to be tested, and the test terminal is electrically connected to the connection terminal through the test circuit. The test circuit includes an overall test circuit and a charger test circuit.

[0023] The connection terminals include a first connection terminal (corresponding to W1P1 on the test panel) and a second connection terminal (corresponding to W2P2 on the test panel); the first connection terminal is connected to the overall test circuit; the second connection terminal is connected to the charger test circuit; in practical applications, the first and second connection terminals can use 25-pin D-SUB connectors, and can also be converted to other universal connectors using adapters, facilitating quick connection to the rear connector of the independent power supply component via cable, effectively improving testing efficiency. At the same time, the pre-defined wiring sequence can also avoid the problem of errors that are easy to occur when manually wiring, making the testing process safer.

[0024] The overall testing circuit includes an overall power input circuit (corresponding to test panel ports J5 and J6), a power monitoring circuit, a load monitoring circuit, and a load connection test circuit (corresponding to test panel ports J7 and J8); the load connection test circuit includes several load test branches; LEDs (corresponding to DS1, DS2, and DS3 on the test panel) are connected in series on the load test branches; a power switch S1 is connected in series on the overall power input circuit; and a load switch S2 is connected in series on the load monitoring circuit.

[0025] The power monitoring circuit includes a power monitoring main line (corresponding to test panel port J1) and a power monitoring feeder line (corresponding to test panel port J2); the load monitoring circuit includes a load monitoring main line (corresponding to test panel port J3) and a load monitoring feeder line (corresponding to test panel port J4); the load access test circuit includes a load access test feeder line (corresponding to test panel port J8); a control switch S4 is connected in series on the load access test feeder line to control the access of the corresponding branch signal;

[0026] Taking actual operation as an example, J1 and J2 are used to connect a multimeter to detect the input voltage; J3 and J4 are connected to a multimeter to detect the current load voltage; J5 and J6 are input terminals used to connect a 28V adjustable DC power supply, and S1 can be used to control the power supply's on / off state; J7 and J8 are load terminals used to connect electronic loads, and S2 can be used to control the electronic load's on / off state; DS1, DS2, and DS3 are indicator lights used to indicate the working status of the independent power supply component. DS1 indicates that the independent power supply is working normally, DS2 indicates that the independent power supply has been activated, and DS3 indicates that the independent power supply needs maintenance; the device also brings out several test points D2, D3, and D4 to detect the conduction status of the relays inside the independent power supply.

[0027] The charger test circuit includes a charger power input circuit, a simulated battery load circuit, and several detection lines; several load resistors are connected in series on the simulated battery load circuit.

[0028] The charger power input circuit includes a positive branch (corresponding to test panel port TP1), a negative branch (corresponding to test panel port TP2), and a temperature simulation branch (corresponding to test panel port TP3); the simulated battery load circuit is connected in parallel between the positive and negative branches to simulate the load characteristics of an uncharged battery to test the charger's functionality; a cooling fan is also connected in parallel to the simulated battery load circuit to dissipate heat from the load resistor; the detection circuit includes a heater monitoring circuit (corresponding to test panel ports TP4 and TP5) and a simulated battery status monitoring circuit (corresponding to test panel port TP6);

[0029] Taking actual operation as an example, TP1 and TP2 are connected to an external power source to simulate the battery voltage during emergency battery power supply; for example... Figure 3 As shown, in this embodiment, pins 12 and 25 of the second connection terminal correspond to the positive power supply of the charger, and pins 1 and 14 correspond to the negative power supply of the charger; pins 17 and 18 correspond to the temperature signal receiving port of the charger; pins 20 and 21 correspond to the positive power supply of the two sets of heating circuits inside the charger, and pins 5 and 6 correspond to the negative power supply of the two sets of heating circuits inside the charger.

[0030] During testing, a 0 to 3 volt adjustable DC voltage is provided to the charger's temperature signal receiving port through the TP3 port to simulate the current battery temperature signal. This can be used to detect whether the charger can adjust the charging current according to the battery temperature. TP4 and TP5 are used to connect the positive and negative terminals of the upper and lower heating circuits inside the charger to the external constant current electronic load to detect whether the heating circuit is working properly. Figure 3 Resistors R4 and R5 are used to simulate the internal resistance of the battery; TP6 can detect the current voltage of the simulated battery.

[0031] Furthermore, a current-limiting resistor (corresponding to) is connected in series on the load test branch. Figure 2 R1, R2 and R3) and diodes (corresponding) Figure 2 The components in the circuit include D5, D6, and D7. The current-limiting resistor limits the current, while the diode protects other components in the circuit by utilizing its reverse cutoff characteristic. A diode D8 is connected in series on the power input circuit of the charger to protect the circuit and prevent the tested circuit from being burned out by reverse connection of the power supply.

[0032] For ease of use, the testing device also includes a housing and a test panel; the test circuit is located inside the housing, while the connection terminals, test terminals, power switch, load switch, LEDs and control switches are located on the panel.

[0033] Testers can quickly connect the connection terminals to the rear connector of the independent power supply component under test using a unified interface, and quickly connect the power supply, test instruments, and external loads to perform various tests through the connection terminals. In addition, the charger test circuit can also simulate an uncharged battery to test the charger of the independent power supply component, which is convenient, fast, and safer.

[0034] Advantages of this utility model:

[0035] The necessary circuit connections for testing are integrated, and test terminals are led out and placed on the test panel. Testers can quickly connect the testing device to the rear connector of the power supply component under test through a standard interface, avoiding wiring errors. Power can be supplied and instruments can be measured through the wiring ports on the test panel. The status of the power supply component can be judged by the indicator lights. Quick operation can be performed through the switches on the panel. The internal circuit simulates the load of a rechargeable battery to test the charger. The overall test circuit and the charger test circuit are independent of each other and do not interfere with each other, resulting in higher testing efficiency and safety.

[0036] The above description is merely a specific embodiment of this utility model, but the protection scope of this utility model is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this utility model should be included within the protection scope of this utility model. Therefore, the protection scope of this utility model should be determined by the protection scope of the claims.

Claims

1. An aircraft independent power supply unit detection device comprising a connection terminal, a test circuit, and a test terminal, the connection terminal being electrically connected to an independent power supply unit to be detected, the test terminal being electrically connected to the connection terminal through the test circuit, characterized in that, The test circuit includes a complete machine test circuit and a charger test circuit; the complete machine test circuit includes a complete machine power input circuit, a power monitoring circuit, a load monitoring circuit, and a load connection test circuit; the load connection test circuit includes several load test branches; light-emitting diodes are connected in series on the load test branches; a power switch is connected in series on the complete machine power input circuit; a load switch is connected in series on the load monitoring circuit; the charger test circuit includes a charger power input circuit, a simulated battery load circuit, and several detection lines; several load resistors are connected in series on the simulated battery load circuit.

2. The aircraft independent power supply component testing device according to claim 1, characterized in that, The power monitoring circuit includes a power monitoring main line and a power monitoring feeder; the load monitoring circuit includes a load monitoring main line and a load monitoring feeder; the load access test circuit includes a load access test feeder.

3. The aircraft independent power supply component testing device according to claim 1, characterized in that, The charger power input circuit includes a positive branch, a negative branch, and a temperature simulation branch; the simulated battery load circuit is connected in parallel between the positive branch and the negative branch.

4. The aircraft independent power supply component testing device according to claim 1, characterized in that, A diode is connected in series in the power input circuit of the charger.

5. The aircraft independent power supply component testing device according to claim 1, characterized in that, The detection circuitry includes a heater monitoring circuit and a simulated battery status monitoring circuit.

6. The aircraft independent power supply component testing device according to claim 1, characterized in that, A control switch is connected in series on the load access test feeder.

7. The aircraft independent power supply component testing device according to claim 6, characterized in that, A current-limiting resistor and a diode are connected in series on the load test branch.

8. The aircraft independent power supply component testing device according to claim 7, characterized in that, The connection terminals include a first connection terminal and a second connection terminal; the first connection terminal is connected to the whole machine test circuit; and the second connection terminal is connected to the charger test circuit.

9. The aircraft independent power supply component testing device according to claim 8, characterized in that, It also includes a housing and a test panel; the connection terminals, test terminals, power switch, load switch, light-emitting diode and control switch are arranged on the panel.

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