Auxiliary measuring device and method for resistance of overheat detection element of wing fuselage

Abstract

The invention relates to the technical field of resistance auxiliary measuring devices, in particular to a wing and fuselage overheating detection element resistance auxiliary measuring device and method.The wing and fuselage overheating detection element resistance auxiliary measuring device comprises a box body, and the rear end of the box body is fixedly connected with an aviation switching electric connector used for being connected with an electric plug behind a thermal detection control assembly M237; the front end is fixedly connected with a first measuring line connecting end, a second measuring line connecting end and a change-over switch; the aviation switching electric connector comprises a grounding terminal and a plurality of detection element channel connecting terminals; the grounding terminal is connected with a second measuring line connecting end through a wire, the detecting element channel connecting terminal is connected with a change-over switch through a wire, and the change-over switch is connected with a first measuring line connecting end through a wire. The change-over switch is used for connecting the first measuring line connecting end to different detection element channel connecting terminals; according to the invention, the connection points of the measuring line do not need to be replaced frequently, the measuring efficiency is higher, and the pin of the electric plug behind the M237 is not damaged.

Description

Technical Field

[0001] The invention relates to the technical field of resistance-assisted measurement devices, and in particular to a resistance-assisted measurement device and method for a wing fuselage overheat detection element. Background Art

[0002] 22 wing fuselage overheat detection elements are distributed in 6 detection element channels. The detection element channels include channel lines and overheat detection elements connected to the channel lines. The two ends of the channel line are the upstream end and the downstream end. When performing the resistance measurement of the wing fuselage overheat detection elements of the Boeing 737NG aircraft, it is necessary to remove the overheat detection control component M237 after power is turned off, and then use the LCR meter to measure the resistance of the detection elements to ground by connecting the corresponding pins of the wing fuselage overheat detection elements of the electrical plug behind the overheat detection control component M237, so as to predict and determine in advance whether these detection elements are faulty. Since the electrical plug behind M237 is difficult to approach and the number of detection elements to be measured is large, especially when troubleshooting is required, the measurement takes longer time. It requires two people to cooperate to complete the line analysis, measurement, recording and lighting. The overall test efficiency is relatively low, and long-term work can easily cause fatigue to maintenance personnel. Working in narrow and poorly lit areas can easily cause pin damage when the LCR meter is connected to the electrical plug behind M237, posing a safety hazard. Summary of the invention

[0003] The main purpose of the present invention is to provide a wing fuselage overheat detection element resistance auxiliary measurement device and method to solve the problem of low measurement efficiency when measuring the resistance of the wing fuselage overheat detection element in the above-mentioned prior art, which easily causes damage to the pins of the electrical plug at the rear of M237.

[0004] In order to achieve the above-mentioned purpose, the present invention provides an auxiliary measurement device for the resistance of an overheat detection element of a wing and fuselage, comprising a box body, the rear end of the box body is fixedly connected with an aviation adapter electrical connector for connecting to an electrical plug at the rear of a heat detection control component M237, and the front end is fixedly connected with a measuring line connection terminal 1, a measuring line connection terminal 2 and a conversion switch; the aviation adapter electrical connector comprises a ground terminal and a plurality of detection element channel connection terminals; the ground terminal is connected to the measuring line connection terminal 2 through a wire, the detection element channel connection terminal is connected to the conversion switch through a wire, and the conversion switch is connected to the measuring line connection terminal 1 through a wire; the conversion switch is used to connect the measuring line connection terminal 1 to different detection element channel connection terminals.

[0005] Furthermore, the number of conversion switches is two; the detection element channel includes a channel line and an overheat detection element connected to the channel line; the two ends of the channel line are an upstream end and a downstream end; the detection element channel connection terminal includes a plurality of channel line upstream end connection terminals and a plurality of channel line downstream end connection terminals; the two conversion switches are respectively connected to the channel line upstream end connection terminal and the channel line downstream end connection terminal.

[0006] Furthermore, a lighting strip and a light strip brightness adjustment switch are fixedly connected to the front end of the box, an aviation lithium battery is arranged inside the box, and the lighting strip, the light strip brightness adjustment switch and the aviation lithium battery are connected by wires.

[0007] Furthermore, the side of the box body is connected to a side door via a hinge, and the side door is provided with a heat dissipation hole and a side handle.

[0008] Furthermore, a handle and an auxiliary locking mechanism for connecting to the E1 electronic rack of the aircraft are fixedly connected to the front side of the box.

[0009] Furthermore, the wires connected to the aviation adapter electrical connector, the measuring line connection terminal 1, the measuring line connection terminal 2, the conversion switch, the lighting strip, the light strip brightness adjustment switch and the aviation lithium battery are all arranged inside the box.

[0010] The present invention also provides a measurement method of the wing fuselage overheat detection element resistance auxiliary measurement device, comprising the following steps: S1. Remove the heat detection control assembly M237, install the wing fuselage overheat detection element resistance auxiliary measurement device on the original position of the heat detection control assembly M237, and directly connect the aviation adapter electrical connector to the electrical plug at the rear of the heat detection control assembly M237; S2. Connect the measuring line of the LCR meter to the measuring line connection terminal 1 and the measuring line connection terminal 2; S3, toggle the conversion switch to measure different detection element channels, measure the resistance of the wing fuselage overheat detection element of the entire channel as a whole, and determine the abnormal detection element channel with abnormal resistance; S4. When there are multiple wing fuselage overheat detection elements in the abnormal detection element channel, the channel line is disconnected and divided into two channel sections, and each channel section is measured as a whole to determine the abnormal channel section with abnormal resistance; S5. The parallel value of the resistance of one or several wing-fuselage overheat detection elements in the abnormal channel section is measured separately by disconnecting the isolation, and finally it is confirmed that the resistance of which wing-fuselage overheat detection element is abnormal.

[0011] During measurement, the present invention only requires that the measuring line of the LCR meter be connected to the first measuring line connection terminal and the second measuring line connection terminal, the aviation adapter electrical connector be connected to the electrical plug at the rear of the thermal detection control component M237, and then the conversion switch be toggled to measure different channels; there is no need to connect the measuring line of the LCR meter to the corresponding pin of the wing fuselage overheat detection element of the electrical plug at the rear of the overheat detection control component M237, there is no need to frequently replace the connection points of the measuring line, the measurement efficiency is higher, and the pin of the electrical plug at the rear of the M237 will not be damaged.

[0012] The measuring line connection terminal 1, the measuring line connection terminal 2 and the conversion switch of the present invention are all located on the front side of the wing fuselage overheat detection element resistance auxiliary measurement device, in a spacious space that is convenient for operation, and there is no need to operate in a narrow space; and there is a lighting strip for lighting, the lighting conditions are good, which further facilitates operation, improves work efficiency and reduces personnel fatigue.

[0013] The structure of the wing-fuselage overheat detection element is relatively fragile, and frequent disassembly and assembly can easily cause damage, and the detection element is relatively expensive; the present invention reduces the number of disconnection and isolation of the wing-fuselage overheat detection element as much as possible during the measurement process, thereby reducing component damage and reducing costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] The drawings in the specification, which constitute a part of this application, are used to provide a further understanding of the present invention. The illustrative embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute improper limitations on the present invention.

[0015] Figure 1 Schematic diagram of the structure of the wing fuselage overheat detection element resistance auxiliary measurement device in the embodiment; Figure 2 Schematic diagram of the structure of the aviation adapter electrical connector in the embodiment.

[0016] Figure 3 It is a structural schematic diagram of the wiring of the detection element channel conversion switch in the embodiment; Figure 4 It is a structural schematic diagram of the connection between the C channel and the wing fuselage overheat detection element resistance auxiliary measurement device in the embodiment.

[0017] In the figure: 1. Box body; 101. Hinge; 102. Side door; 103. Heat dissipation hole; 104. Side handle; 2. Aviation adapter electrical connector; 3. Measuring line connection terminal 1; 4. Measuring line connection terminal 2; 5. Conversion switch; 6. Light strip brightness adjustment switch; 7. Aviation lithium battery; 8. Handle; 9. Auxiliary locking mechanism; 10. Light strip; 11. Wing and fuselage overheat detection element; 1101. Core wire; 1102. Metal sleeve; 1103. Resistance material; 12. Channel line; 13. Fuselage grounding. DETAILED DESCRIPTION

[0018] It should be noted that, in the absence of conflict, the embodiments and features in the embodiments of the present application can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0019] like Figure 1 to Figure 2 As shown, according to an embodiment of the present invention, there is provided an auxiliary measurement device for the resistance of an overheat detection element of a wing and fuselage, comprising a box body 1, the rear end of the box body 1 being fixedly connected with an aviation adapter electrical connector 2 for connecting to an electrical plug at the rear of a heat detection control component M237, and the front end being fixedly connected with a measuring line connection terminal 1 3, a measuring line connection terminal 2 4 and a conversion switch 5; the aviation adapter electrical connector 2 comprises a ground terminal and a plurality of detection element channel connection terminals; the ground terminal is connected with the measuring line connection terminal 2 4 via a wire, the detection element channel connection terminal is connected with the conversion switch 5 via a wire, and the conversion switch 5 is connected with the measuring line connection terminal 1 3 via a wire; the conversion switch 5 is used to connect the measuring line connection terminal 1 3 to different detection element channel connection terminals.

[0020] The front end of the box body 1 is fixedly connected with a lighting strip 10 and a light strip brightness adjustment switch 6. An aviation lithium battery 7 is arranged inside the box body 1. The lighting strip 10, the light strip brightness adjustment switch 6 and the aviation lithium battery 7 are connected by wires.

[0021] The side of the box body 1 is connected to a side door 102 via a hinge 101 , and the side door 102 is provided with a heat dissipation hole 103 and a side handle 104 .

[0022] The front side of the box 1 is fixedly connected with a handle 8 and an auxiliary locking mechanism 9 for connecting to the aircraft E1 electronic rack; the auxiliary locking mechanism 9 is made of aviation standard parts and matches the aircraft structure to ensure that the auxiliary measuring device is installed in place without damage.

[0023] The wires connected to the aviation adapter electrical connector 2, the measuring line connection terminal 1 3, the measuring line connection terminal 2 4, the conversion switch 5, the lighting light strip 10, the light strip brightness adjustment switch 6 and the aviation lithium battery 7 are all arranged inside the box 1.

[0024] There are two conversion switches 5; the detection element channels all include a channel line 12 and an overheat detection element 11 connected to the channel line 12; the two ends of the channel line 12 are an upstream end and a downstream end; the detection element channel connection terminals include a plurality of channel line upstream end connection terminals and a plurality of channel line downstream end connection terminals; the two conversion switches 5 are respectively connected to the channel line upstream end connection terminal and the channel line downstream end connection terminal.

[0025] When one conversion switch 5 controls the measurement line of the LCR meter to be connected to the channel line 12, the other conversion switch 5 is in the OFF position; the two conversion switches 5 should not control the measurement line of the LCR meter to be connected to the channel line 12 at the same time.

[0026] The wing fuselage overheat detection element resistance auxiliary measurement device of this embodiment is used for measuring the wing fuselage overheat detection element 11; Figure 3 and Figure 4 As shown, 22 wing fuselage overheat detection elements 11 are distributed in 6 detection element channels; the 6 detection element channels are channel A, channel B, channel C, channel D, channel E, and channel F; the wing fuselage overheat detection element 11 includes a core wire 1101, a metal sleeve 1102 sleeved outside the core wire 1101, and a resistor material 1103 arranged between the core wire 1101 and the metal sleeve 1102, and the metal sleeve 1102 is connected to the fuselage ground 13; both ends of the channel wire 12 in each channel It is connected to the electrical plug at the rear of the thermal detection control component M237, and the fuselage ground 13 is also connected to the electrical plug at the rear of the thermal detection control component M237; when the aviation adapter electrical connector 2 is connected to the electrical plug at the rear of the thermal detection control component M237, the detection element channel connection terminal is connected to the channel line 12, and the ground terminal is connected to the fuselage ground 13; after connecting the measuring line of the LCR meter to the measuring line connection terminal 1 3 and the measuring line connection terminal 2 4, the LCR meter can measure the wing fuselage overheat detection element 11.

[0027] A knob is provided on the conversion switch 5. Rotating the knob can connect the measuring line connection end 3 to different detection element channel connection terminals, and then connect different detection element channels; thereby, the resistance of the wing-fuselage overheat detection element 11 of the entire channel can be uniformly measured; when the resistance in a detection element channel is measured to be abnormal, the resistance of one or several wing-fuselage overheat detection elements 11 in the detection element channel is measured separately by disconnecting the isolation, and the range is continuously narrowed to detect which wing-fuselage overheat detection element 11 has an abnormal resistance, until the abnormal wing-fuselage overheat detection element 11 is found.

[0028] This embodiment also provides a measurement method of the above-mentioned wing fuselage overheat detection element resistance auxiliary measurement device, comprising the following steps: S1. Remove the heat detection control assembly M237, install the wing fuselage overheat detection element resistance auxiliary measurement device on the original position of the heat detection control assembly M237, and directly connect the aviation adapter electrical connector 2 to the electrical plug at the rear of the heat detection control assembly M237; S2. Connect the measuring line of the LCR meter to the measuring line connection terminal 1 3 and the measuring line connection terminal 2 4; S3, toggle the conversion switch 5 to measure different detection element channels, measure the resistance of the wing fuselage overheat detection element 11 of the entire channel as a whole, and determine the abnormal detection element channel with abnormal resistance; S4. When there are multiple wing-fuselage overheat detection elements 11 in the abnormal detection element channel, the channel line 12 is disconnected to divide it into two channel sections, and each channel section is measured as a whole to determine the abnormal channel section with abnormal resistance; for example, the abnormal detection element channel is determined to be channel C, and the 7 wing-fuselage overheat detection elements 11 arranged in sequence in channel C are numbered M1912, M1910, M356, M371, M269, M1763, and M1764 respectively; disconnect M356 and M371, and channel C is divided into two channel sections; channel section one contains M1912, M1910, and M356, and channel section two contains M371, M269, M1763, and M1764; after measurement, channel section one is determined to be the abnormal channel section; S5. By disconnecting and isolating, the parallel value of the resistance of one or several wing-fuselage overheat detection elements 11 in the abnormal channel section is measured separately, and finally it is confirmed that the resistance of which wing-fuselage overheat detection element 11 is abnormal; for example, disconnect M1910 and M356 in channel section 1, and measure the overall resistance of M1912 and M1910; if the overall resistance of M1912 and M1910 is normal, then M356 is abnormal; if the overall resistance of M1912 and M1910 is abnormal, disconnect M1912 and M1910, and measure the resistance of M1912; if M1912 is normal, then M1910 is abnormal, and if M1912 is abnormal, then M1910 is normal.

[0029] The measuring line connection terminal 1 3, the measuring line connection terminal 2 4 and the conversion switch 5 of this embodiment are all located on the front side of the wing fuselage overheat detection element resistance auxiliary measurement device, in a spacious space that is convenient for operation, and there is no need to operate in a narrow space; and there is a lighting strip 10 for lighting, the lighting conditions are good, which further facilitates operation, improves work efficiency, and reduces personnel fatigue.

[0030] In this embodiment, there is no need to connect the measuring line of the LCR meter to the corresponding pins of the 22 wing and fuselage overheat detection elements of the electrical plug at the rear of the overheat detection control component M237, and there is no need to frequently replace the connection points of the measuring line. The measurement efficiency is higher and the pins of the electrical plug at the rear of M237 will not be damaged.

[0031] The structure of the wing-fuselage overheat detection element 11 is relatively fragile, and frequent disassembly and assembly can easily cause damage, and the detection element is relatively expensive. In the measurement process, this embodiment reduces the number of disconnection and isolation of the wing-fuselage overheat detection element 11 as much as possible, thereby reducing component damage and reducing costs.

[0032] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A resistance auxiliary measurement device for wing and fuselage overheat detection elements, characterized in that: The invention comprises a box body (1), wherein the rear end of the box body (1) is fixedly connected with an aviation adapter electrical connector (2) for connecting to an electrical plug at the rear of a heat detection control component M237, and the front end is fixedly connected with a measuring line connection terminal 1 (3), a measuring line connection terminal 2 (4) and a conversion switch (5); the aviation adapter electrical connector (2) comprises a ground terminal and a plurality of detection element channel connection terminals; the ground terminal is connected to the measuring line connection terminal 2 (4) via a wire, the detection element channel connection terminal is connected to the conversion switch (5) via a wire, and the conversion switch (5) is connected to the measuring line connection terminal 1 (3) via a wire; the conversion switch (5) is used to connect the measuring line connection terminal 1 (3) to different detection element channel connection terminals.

2. The wing fuselage overheat detection element resistance auxiliary measurement device according to claim 1, characterized in that: The number of the conversion switches (5) is two; the detection element channels each include a channel line (12) and an overheat detection element (11) connected to the channel line (12); the two ends of the channel line (12) are an upstream end and a downstream end; the detection element channel connection terminals include a plurality of channel line upstream end connection terminals and a plurality of channel line downstream end connection terminals; The two conversion switches (5) are respectively connected to the channel line upstream end connection terminal and the channel line downstream end connection terminal.

3. The wing fuselage overheat detection element resistance auxiliary measurement device according to claim 1, characterized in that: A lighting strip (10) and a light strip brightness adjustment switch (6) are fixedly connected to the front end of the box (1); an aviation lithium battery (7) is arranged inside the box (1); and the lighting strip (10), the light strip brightness adjustment switch (6) and the aviation lithium battery (7) are connected via a wire.

4. The wing fuselage overheat detection element resistance auxiliary measurement device according to claim 1, characterized in that: The side of the box body (1) is connected to a side door (102) via a hinge (101), and the side door (102) is provided with a heat dissipation hole (103) and a side handle (104).

5. The wing fuselage overheat detection element resistance auxiliary measurement device according to claim 1, characterized in that: A handle (8) and an auxiliary locking mechanism (9) for connecting to an aircraft E1 electronic rack are fixedly connected to the front side of the box body (1).

6. The wing fuselage overheat detection element resistance auxiliary measurement device according to claim 1, characterized in that: Lead wires connected to the aviation adapter electrical connector (2), the first measuring line connection terminal (3), the second measuring line connection terminal (4), the conversion switch (5), the lighting light strip (10), the light strip brightness adjustment switch (6) and the aviation lithium battery (7) are all arranged inside the box (1).

7. A method for measuring the resistance auxiliary measurement device of the wing fuselage overheat detection element as claimed in any one of claim 2, characterized in that: The following steps are involved: S1. Remove the heat detection control assembly M237, install the wing fuselage overheat detection element resistance auxiliary measurement device on the original position of the heat detection control assembly M237, and directly connect the aviation adapter electrical connector (2) to the electrical plug at the rear of the heat detection control assembly M237; S2. Connect the measuring line of the LCR meter to the measuring line connection terminal 1 (3) and the measuring line connection terminal 2 (4); S3, toggle the conversion switch (5) to measure different detection element channels, measure the resistance of the wing fuselage overheat detection element (11) of the entire channel as a whole, and determine the abnormal detection element channel with abnormal resistance; S4. When there are multiple wing fuselage overheat detection elements (11) in the abnormal detection element channel, the channel line (12) is disconnected to divide it into two channel sections, and each channel section is measured as a whole to determine the abnormal channel section with abnormal resistance; S5. By disconnecting the isolation, the parallel value of the resistance of one or several wing-fuselage overheat detection elements (11) in the abnormal channel section is measured separately, and finally it is confirmed which wing-fuselage overheat detection element (11) has the abnormal resistance.

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