Flight management component FMC rear interface component test system
By designing a rear interface component test system for flight management component FMC, the test cable and test board can effectively detect filtering performance in the filter circuit and the fault of the varistor R, which solves the problem that the existing test system cannot detect intermittent failures, and achieves rapid and simple fault detection and maintenance costs.
Patent Information
- Application Number
- CN202421415238.6
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-06-19
- Publication Date
- 2025-06-27
- Estimated Expiration
- 2034-06-19
AI Technical Summary
During the aircraft's Flight Management Component (FMC) repair, it was found that the varistor R had intermittent failure, resulting in inconsistent input signals of the FMC, displaying FMC DISAGREE information, and the existing test system was unable to effectively detect such faults.
A flight management component FMC rear interface component test system is designed. Through the test cable and test board, the dial switch SW and the interface component JP are used to connect and sample the filter capacitor C and varistor R in the filter circuit to determine whether its performance is normal.
The test system can quickly and simply detect the filtering performance in the filter circuit and whether there is an abnormal grounding fault in the varistor R, which improves the efficiency of fault detection and reduces maintenance costs.
Smart Images
Figure CN223038100U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of circuit performance, and particularly relates to a test system for the rear interface component of a Flight Management Component (FMC). Background Art
[0002] The rear interface component of the Flight Management Component (FMC) of an aircraft consists of a filter circuit component and a back interface component JP, which are mainly used for the preprocessing of FMC input and output signals and the abnormal protection of the core circuit board. Among them, the filter circuit component includes a signal filter circuit, which can not only protect the functional circuit, but also filter out the noise mixed in the external signal, improving the stability of FMC signal input and output.
[0003] During the repair process of the FMC, it has been found many times that the repair is caused by the failure of the varistor R in the signal filter circuit. Some of the faulty parts have stable fault phenomena and can be detected in normal standard tests, and such faults are generally easier to handle. However, there are also some varistors R with intermittent failure problems. The specific manifestation on the aircraft is that the discrete input signals of the FMCs on the left and right sides are inconsistent, and generally the FMC DISAGREE message will be displayed. The essential reason for this fault phenomenon is the aging of the varistor R, which causes the input signal to be abnormally grounded, thereby leading to misjudgment of the input signal by the FMC. Summary of the Utility Model
[0004] In view of this, the problem to be solved by the utility model is to provide a test system for the rear interface component of a Flight Management Component (FMC).
[0005] To solve the above technical problems, the technical solution adopted by the utility model is as follows:
[0006] A test system for the rear interface component of a Flight Management Component (FMC), wherein the rear interface component includes a filter circuit connected to the back interface, and the filter circuit includes a filter capacitor C connected to the ground electrode and a varistor R connected to the ground electrode;
[0007] Characterized in that it includes a test cable and a test board. The test cable includes a connector and an aviation plug. The connector is connected to the rear interface component, and the aviation plug is connected to the aviation plug through a plurality of connecting wires;
[0008] The test board includes an interface component JP and a DIP switch SW. Several pins of the interface component JP are respectively connected to one end of the corresponding DIP switch SW, and the other end is connected to the corresponding connecting wire inside the aviation plug. The interface component JP is connected to the test points corresponding to the sampling detection pinch.
[0009] Further, the model of the connector is ARINC600.
[0010] Further, the connection wire uses a PTFE insulation layer of AWG20.
[0011] Further, the model of the aviation plug is the Y50X series.
[0012] Further, the connector is respectively connected to a plurality of aviation plugs.
[0013] The advantages and positive effects of the present utility model are as follows:
[0014] By arranging the test cable to lead out each back interface in the rear interface assembly respectively, and then electrically connecting one end of the DIP switch SW on the test board, the other end of the DIP switch SW is connected to the corresponding test point on the sampling device through the interface assembly JP. The sampling device determines the filtering performance of the filter capacitor C in the filter circuit and determines whether there is an abnormal grounding fault of the varistor R in the filter circuit according to the received data at the test point and the conduction condition of the DIP switch SW. Description of the Drawings
[0015] The drawings are used to provide a further understanding of the present utility model, and constitute a part of the specification. Together with the embodiments of the present utility model, they are used to explain the present utility model, and do not constitute a limitation to the present utility model. In the drawings:
[0016] Figure 1 is the filter circuit diagram in the rear interface assembly of a flight management component FMC of the present utility model;
[0017] Figure 2 is the system diagram of a test device for the rear interface assembly of a flight management component FMC of the present utility model;
[0018] Figure 3 is the circuit diagram of the test board in a test device for the rear interface assembly of a flight management component FMC of the present utility model. Detailed Embodiments
[0019] Next, the technical solutions in the embodiments of the present utility model will be clearly and completely described in conjunction with the drawings in the embodiments of the present utility model. Obviously, the described embodiments are only a part of the embodiments of the present utility model, rather than all of the embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present utility model.
[0020] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by those of ordinary skill in the technical field to which this utility model belongs. The terms used in the specification of this utility model herein are only for the purpose of describing specific embodiments and are not intended to limit this utility model. The term "and / or" used herein includes any and all combinations of one or more of the related listed items.
[0021] This utility model provides a test system for the rear interface component of a flight management component (FMC). As Figure 1 shown, the rear interface component includes a filter circuit for transmitting signals and a back interface for connecting to external devices. The filter circuit includes a filter capacitor C and a varistor R. The filter capacitor C is used to remove the clutter in the transmitted signal; when a high-voltage signal flows through the filter circuit, the varistor R conducts to avoid burning out the hardware devices in the circuit board.
[0022] As Figure 2 shown, the test equipment includes a test cable and a test board. One end of the test cable is connected to the rear interface component, and the other end is connected to the test board, which is used to transmit the output signals of each back interface in the rear interface component respectively.
[0023] The test cable includes a connector and an aviation plug. The connector is connected to the back interface to transmit the output signal of each back interface separately; the connector is connected to the aviation plug through several connecting wires, and the aviation plug is fixedly installed on the test board by screws, which can improve the connection stability and communication stability between the test cable and the test board.
[0024] An embodiment of this application is: the model of the connector is ARINC600, which can be specifically used to connect to the flight management component. The outer surface of the connecting wire uses a PTFE insulation layer of AWG20, so that the connecting wire can have the properties of being resistant to friction, high temperature, low temperature and corrosion. The model of the aviation plug is the Y50X series.
[0025] As Figure 3 shown, the test board includes an interface component JP. The interface component JP is connected to the corresponding connecting wires in the aviation plug through the corresponding DIP switches SW. Several output terminals of the interface component JP are connected to the corresponding test points on the sampling device, and the data signals output from the back interface can be transmitted to the sampling device respectively.
[0026] Judge whether the performance of the filter capacitor C in the filter circuit is normal according to the data signal at the test point. According to the data signal at the test point and the closing condition of the DIP switch SW, judge whether the performance of the varistor R in the filter circuit is normal or whether it is aging.
[0027] The test board includes an interface component JP. The interface component JP includes a number of input pins. The input pins are connected to one end of the corresponding DIP switch SW, and the other end of the DIP switch SW is connected to the corresponding connecting wire inside the aviation plug. The interface component JP includes a number of output interfaces, and the output interfaces are connected to the corresponding test points.
[0028] The connector of ARINC600 and the connection group of the connecting wire can be manually adjusted so that the connector can be respectively connected to a number of aviation plugs. The electrical parameters of the number of aviation plugs are not exactly the same, so as to be connected to the subsequent interface component for transmitting different types of signals.
[0029] The working principle and process of the present utility model are as follows:
[0030] Use a test cable to connect the test board to the subsequent interface component of the flight management component, and close all the DIP switches SW on the test board. Turn on the flight management component so that each back interface in the subsequent interface component outputs a known data signal. The data signal passes through the connector, connecting wire, aviation plug, DIP switch SW, interface component JP, and test point in sequence. Collect the data signal at the test point, compare the collected data signal with the known data signal, and judge the performance of the filter connected to the back interface.
[0031] This solution can make up for the defects of the original factory test bench and realize the test functions that the original factory test bench cannot achieve; this solution has a fast and simple test speed. Compared with traditional test equipment, it is easier to find potential faults; this solution has a low maintenance cost and does not require daily maintenance. The present invention reduces the potential maintenance cost in design, making the equipment operation more efficient.
[0032] Switch the DIP switch SW multiple times, use the same method to collect the data signal at the test point, compare the collected data signal with the known data signal, and judge the performance of the filter connected to the back interface.
[0033] The above has described the embodiments of the present utility model in detail, but the content described is only the preferred embodiments of the present utility model and cannot be considered as limiting the scope of implementation of the present utility model. All equal changes and improvements made according to the scope of the present utility model should still fall within the scope covered by this patent.
Claims
1. A flight management component FMC rear interface component test system, wherein the rear interface component includes a filter circuit connected to the back interface, and the filter circuit includes a filter capacitor C connected to the ground electrode and a varistor R connected to the ground electrode; It is characterized in that It includes a test cable and a test board, wherein the test cable includes a connector and an aviation plug, wherein the connector is connected to the rear interface component, and the aviation plug is connected to the aviation plug through a plurality of connecting wires; The test board includes an interface component JP and a dip switch SW. Several pins of the interface component JP are respectively connected to one end of the corresponding dip switch SW, and the other end is connected to the corresponding connecting wire in the aviation plug. The interface component JP is connected to the corresponding test point of the sampling detection pinch.
2. A flight management component FMC rear interface component test system according to claim 1, characterized in that: The model of the connector is ARINC600.
3. A flight management component FMC rear interface component test system according to claim 1, characterized in that: The wiring wire uses an AWG20 PTFE insulation layer.
4. A flight management component FMC rear interface component test system according to claim 1, characterized in that: The model of the aviation plug is Y50X series.
5. A flight management component FMC rear interface component test system according to claim 1, characterized in that: The connectors are respectively connected to a plurality of aviation plugs.