Testing device of aircraft instruction sensor

Abstract

The utility model relates to the technical field of airplane accessory maintenance, in particular to a testing device of an airplane instruction sensor, which comprises a shell, M detection instruments and a gear selector switch are arranged on the shell; the plurality of test switches are arranged in the shell, and each test switch is electrically connected with a switch to be tested in a sensor through a data line; wherein the plurality of test switches are divided into M groups, each group comprises N test switches, and each group of test switches are connected in parallel to one detection instrument. According to the test device provided by the invention, the states of all test points can be displayed on the test device in sequence only by connecting wires once in the test process and switching the gear change-over switch in the test without replacing and plugging test connecting wires back and forth, so that a large amount of test time is saved, and meanwhile, the device adopts an integrated design, so that the test efficiency is improved. Scattered power supplies, instruments, connecting lines and the like do not need to be externally connected, so that the testing process is more convenient.

Description

Technical Field

[0001] This utility model relates to the field of aircraft parts repair technology, and more specifically to a testing device for aircraft command sensors. Background Technology

[0002] The switching point of a sensor, often referred to as the threshold point or trigger point, is the point at which the sensor's output state changes significantly upon receiving a specific input signal. This point is a critical parameter of the sensor, determining when it begins or ceases to respond to external stimuli. When the sensor's input signal (such as temperature, pressure, light intensity, magnetic field, etc.) reaches or exceeds a preset threshold, the sensor's output state changes; this point of change is the switching point. The switching point is crucial for sensor applications, determining when the sensor triggers relevant control or alarm actions.

[0003] Therefore, testing the switching point of the command sensor is a critical testing process, which involves the accuracy and reliability of the point at which the sensor triggers the switching action under specific conditions.

[0004] Currently, some models of command sensors have a knob. When the knob is in different positions, there are different switching points. It is necessary to test the switching points at each angle during testing. The test connection needs to be changed at each angle. Furthermore, the process of repeatedly plugging and unplugging the test connection may cause the knob angle to be accidentally touched, which will affect the test accuracy. Utility Model Content

[0005] To address the technical problems existing in sensor testing in the prior art, this utility model proposes a testing device for aircraft command sensors, comprising:

[0006] The housing is equipped with M detection instruments and a gear shift switch.

[0007] Multiple test switches are disposed inside the housing, and each test switch is electrically connected to the switch under test inside the sensor via a data cable;

[0008] The test switches are divided into M groups, each group containing N test switches. Each group of test switches is connected in parallel to a detection instrument. The gear switching switch includes N+ gears. The N gears of the gear switching switch are used to control the closed state of one of the test switches in each group of N test switches. M and N are positive integers greater than zero.

[0009] Preferably, the gear shift switch includes N closed positions and one zero position. When the gear shift switch is in any closed position, the corresponding test switch in each group of test switches is closed and connected to the detection circuit of the corresponding detection instrument. When the gear shift switch is in the zero position, no test switch is connected to the detection circuit of the detection instrument.

[0010] Preferably, the housing is provided with N indicator lights, and when the gear switching switch is in any closed position, the corresponding indicator light is lit.

[0011] Preferably, the test switch includes a normally open switch, and the gear switching switch includes N relay structures. When the gear switching switch is rotated to any closed position, the corresponding relay structure will pull the corresponding test switch in each group of test switches from the normally open position to the closed position.

[0012] Preferably, N is greater than M.

[0013] Preferably, the plurality of test switches are divided into 4 groups, each group containing 5 test switches, and the gear switching switch includes 5 closed gears and one zero gear.

[0014] Preferably, the housing is further provided with a data cable plug and a power cable plug. Multiple test switches are integrated into the data cable plug. The data cable plug is used to connect a data cable, so that each test switch is electrically connected to the switch under test in the sensor. The power cable plug is used to connect to an external power supply device. The gear shift switch is electrically connected to the power cable plug.

[0015] Compared with the prior art, the advantages of this utility model are:

[0016] The testing device proposed in this application only requires one connection during the testing process. During the test, the status of all test points can be displayed sequentially on the testing device by simply switching the gear selector switch. This eliminates the need to repeatedly plug and unplug test cables, saving a significant amount of testing time. In addition, the device adopts an integrated design, eliminating the need for external power supplies, instruments, connecting lines, etc., making the testing process more convenient. Attached Figure Description

[0017] The accompanying drawings are not intended to be drawn to scale. In the drawings, each identical or nearly identical component shown in the various figures may be denoted by the same reference numeral. For clarity, not every component is labeled in each figure. Embodiments of various aspects of the present invention will now be described by way of example and with reference to the accompanying drawings, wherein:

[0018] Figure 1This is a schematic diagram showing the connection between the test device for the aircraft command sensor and the aircraft command sensor as shown in this utility model.

[0019] Figure 2 This is a front view of the test device for the aircraft command sensor shown in this utility model;

[0020] Figure 3 This is a rear view of the test device for the aircraft command sensor shown in this utility model;

[0021] Figure 4 This is a circuit diagram showing the connection between multiple test switches, gear shifting switches, and testing instruments as shown in this utility model. Detailed Implementation

[0022] To better understand the technical content of this utility model, specific embodiments are provided below in conjunction with the accompanying drawings.

[0023] Combination Figure 1 As shown, this utility model proposes a testing device for an aircraft command sensor, including a housing 10 and a plurality of test switches 20 disposed within the housing 10. The plurality of test switches 20 are disposed within the housing 10, and each test switch 20 is electrically connected to the switch 101 under test within the sensor 100 via a data cable 21.

[0024] In this way, multiple switches 101 under test in the sensor are directly transferred to the test switch 20 via the data line 21. The switching state of the switches 101 under test is controlled by the switching state of the test switch 20, and the on / off state of the switch point is evaluated accordingly.

[0025] Furthermore, the housing 10 is provided with M detection instruments 30 and a gear shift switch 40. The multiple test switches 20 are divided into M groups, each group containing N test switches 20. Each group of test switches 20 is connected in parallel to a detection instrument 30. The gear shift switch 40 includes N+1 gears. The N gears of the gear shift switch 40 are used to control the closed state of one of the test switches 20 in each group of N test switches 20. M and N are positive integers greater than zero.

[0026] Thus, when testing the switching point of sensor 100, first turn the knob of sensor 100 to the target angle, then turn the gear switching switch 40 one by one to switch different gears until N gears are switched. In each gear, observe and record the value of the detection instrument 30, and evaluate whether the test value meets the requirements after the test.

[0027] Optionally, the gear shift switch 40 includes N closed positions and one zero position. When the gear shift switch 40 is in any closed position, the corresponding test switch 20 in each group of test switches 20 is closed and connected to the detection circuit 31 of the corresponding detection instrument 30. When the gear shift switch 40 is in the zero position, no test switch 20 is connected to the detection circuit 31 of the detection instrument 30.

[0028] Thus, when the gear selector switch 40 is in the zero position, no test switch 20 is in the test state. When the gear selector switch 40 is switched to any closed position, all test switches 20 corresponding to that position are in the test state. That is, the test switch 20 in each group corresponding to the gear is connected to the corresponding detection instrument 30 and power supply, and the status of the test point is detected by the detection instrument 30.

[0029] Optionally, the detection instrument 30 is an ohmmeter, and the resistance value of the ohmmeter is used to determine whether the current switching point is normal.

[0030] Preferably, the housing 10 is provided with N indicator lights 41. When the gear shift switch 40 is in any closed position, the corresponding indicator light 41 lights up.

[0031] In this way, users can clearly know which gear they are currently in.

[0032] Preferably, the test switch 20 includes a normally open switch, and the gear shift switch 40 includes N relay structures, for example... Figure 4 As shown, the gear shift switch 40 includes a first relay 401, a second relay 402, a third relay 403, a fourth relay 404, and a fifth relay 405. When the gear shift switch 40 is rotated to any closed position, the corresponding relay structure will pull one of the corresponding test switches 20 in each group of test switches 20 from the normally open position to the closed position.

[0033] Thus, when the gear shift switch 40 is switched to a certain relay structure, such as the first relay 401, the test switches Ae, HF, Dg, and Pb are closed.

[0034] Furthermore, the indicator light 41 is connected in series with the relay in the gear selector switch 40. Thus, when the switch is activated to a specific relay, the corresponding indicator light 41 illuminates.

[0035] Furthermore, in order to reduce the number of detection instruments, where N is greater than M.

[0036] Combination Figures 2 to 4As shown, the multiple test switches 20 are divided into 4 groups, each group containing 5 test switches 20, and the gear switching switch 40 includes 5 closed gears and one zero gear.

[0037] Furthermore, the housing 10 is also provided with a data cable plug 11 and a power cable plug 12. Multiple test switches 20 are integrated into the data cable plug 11. The data cable plug 11 is used to connect the data cable 21, so that each test switch 20 is electrically connected to the switch under test 101 in the sensor 100. The power cable plug 12 is used to connect to an external power supply device. The gear shift switch 40 is electrically connected to the power cable plug 12.

[0038] Specifically, when using the testing device, the power cord plug 12 is inserted into an external power supply. One end of the data cable 21 is connected to the sensor, and the other end is connected to the data cable plug 11. At this time, the test switch 101 inside the sensor 100 is connected to the test switch 20 in the testing device. The knob angle of the sensor 100 is controlled to be at the first angle. Then, the gear switching switch 40 is rotated in sequence to be at the first to fifth gears. That is, the first relay 401, the second relay 402, the third relay 403, the fourth relay 404, and the fifth relay 405 are connected to the circuit in sequence. The 20 test switches 20 are tested five times, four at a time, and the test results are displayed by four testing instruments 30 respectively, completing the test of one angle. Then, the above operation is repeated to test the second angle, the third angle, and so on, until all angles are tested.

[0039] In conjunction with the above embodiments, the testing device proposed in this application only requires one connection during the testing process. During the test, only the gear switching switch needs to be changed to display the status of all test points sequentially on the testing device, eliminating the need to repeatedly plug and unplug test cables, thus saving a significant amount of testing time. At the same time, the device adopts an integrated design, eliminating the need for external power supplies, instruments, connecting lines, etc., making the testing process more convenient.

[0040] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Those skilled in the art to which this invention pertains can make various modifications and refinements without departing from the spirit and scope of the present invention. Therefore, the scope of protection of this invention shall be determined by the claims.

Claims

1. A testing device for an aircraft command sensor, characterized in that, include: The housing (10) is provided with M detection instruments (30) and a gear shift switch (40); Multiple test switches (20) are disposed inside the housing (10), and each test switch (20) is electrically connected to the switch under test (101) inside the sensor (100) via a data line (21); The test switches (20) are divided into M groups, each group containing N test switches (20). Each group of test switches (20) is connected in parallel to a detection instrument (30). The gear switching switch (40) includes N+1 gears. The N gears of the gear switching switch (40) are used to control the closed state of one of the test switches (20) in each group of N test switches (20). M and N are positive integers greater than zero.

2. The testing apparatus for the aircraft command sensor according to claim 1, characterized in that, The gear shift switch (40) includes N closed positions and one zero position. When the gear shift switch (40) is in any closed position, the corresponding test switch (20) in each group of test switches (20) is closed and connected to the detection circuit (31) of the corresponding detection instrument (30). When the gear shift switch (40) is in the zero position, no test switch (20) is connected to the detection circuit (31) of the detection instrument (30).

3. The testing apparatus for the aircraft command sensor according to claim 2, characterized in that, The outer casing (10) is provided with N indicator lights (41). When the gear switching switch (40) is in any closed position, the corresponding indicator light (41) lights up.

4. The testing apparatus for the aircraft command sensor according to claim 2, characterized in that, The test switch (20) includes a normally open switch, and the gear switching switch (40) includes N relay structures. When the gear switching switch (40) is rotated to any closed position, the corresponding relay structure will pull one of the corresponding test switches (20) in each group of test switches (20) from the normally open position to the closed position.

5. The testing apparatus for the aircraft command sensor according to claim 1, characterized in that, in, N is greater than M.

6. The testing apparatus for an aircraft command sensor according to claim 1, characterized in that, The test switches (20) are divided into 4 groups, each group containing 5 test switches (20), and the gear switching switch (40) includes 5 closed gears and one zero gear.

7. The testing apparatus for the aircraft command sensor according to claim 1, characterized in that, The housing (10) is also provided with a data cable plug (11) and a power cable plug (12). Multiple test switches (20) are integrated into the data cable plug (11). The data cable plug (11) is used to connect the data cable (21) so that each test switch (20) is electrically connected to the switch under test (101) in the sensor (100). The power cable plug (12) is used to connect to an external power supply device. The gear shift switch (40) is electrically connected to the power cable plug (12).

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