Aircraft ELT control panel test equipment

Abstract

The utility model relates to the technical field of equipment testing, in particular to airplane ELT control panel testing equipment which comprises a to-be-tested panel interface end and a testing interface end. The test interface end comprises a voltage test end 1, a signal test end 1, a voltage test end 2, a signal test end 2, a signal test end 3, a signal test end 4, a voltage test end 3, a voltage test end 4, a signal generator and an oscilloscope. According to the airplane ELT control panel test equipment, the to-be-tested panel interface end is connected with each test port of the test interface end, so that voltage input and various output signals on the airplane ELT control panel can be tested, the airplane ELT control panel can be ensured to be input and output, stable operation can be ensured, the test process is simplified, and the test efficiency is improved. A set of complete and convenient test equipment is provided for testing the ELT control panel, and the test equipment is convenient to use.

Description

Technical Field

[0001] The utility model relates to the technical field of equipment testing, in particular to an aircraft ELT control panel testing device. Background Art

[0002] Emergency Locator Transmitters (ELTs), also known as emergency radios, come in two types: portable and fixed. When an aircraft experiences a severe impact or water strikes, the ELT transmits an emergency signal, typically lasting at least 24 hours. The signal can be received by the International Satellite Search and Rescue (COSPAS) satellite system.

[0003] Currently, ELT control panels installed on Boeing B737, B767, G7116-01, and G7116-02 aircraft require ground testing of various output signals before factory installation to ensure proper operation in an emergency. Existing testing methods involve using the appropriate equipment for each signal. For example, to verify the panel's 28V voltage input is normal, a multimeter is used to test the voltage amplitude and current. To verify the normality of output signals, such as the MASTER CAUTION PULSE signal, an oscilloscope is used. This increases the complexity of testing and is inconvenient. In light of this, we propose an aircraft ELT control panel testing device. Utility Model Content

[0004] The purpose of the present invention is to provide an aircraft ELT control panel testing device to solve the problems raised in the above background technology.

[0005] To achieve the above objectives, the present invention provides the following technical solutions:

[0006] An aircraft ELT control panel test device comprises: a panel interface terminal to be tested and a test interface terminal;

[0007] The test interface includes:

[0008] The voltage test terminal 1 is connected to ports 3 and 4 of the interface terminal of the panel to be tested;

[0009] The signal test terminal 1 is connected to port 1 of the interface terminal of the panel to be tested, and ports 2 and 5 of the interface terminal of the panel to be tested are respectively connected to indicator light 1 and indicator light 2 through single-pole double-throw switches S1 and S2, and then connected in series to one end of a resistor R1, and the other end of the resistor R1 is connected to the signal test terminal 1;

[0010] The voltage test terminal 2 is connected to port 6 of the interface end of the panel to be tested, and the other switch interface of the single-pole double-throw switches S1 and S2 is connected to port 6 of the interface end of the panel to be tested; port 7 of the interface end of the panel to be tested is connected to the indicator light 3 through the switch S3 and then connected to the voltage test terminal 2; port 10 of the interface end of the panel to be tested is connected to the voltage test terminal 2 through the resistor R2; port 11 of the interface end of the panel to be tested is connected to the voltage test terminal 2 through the resistor R3;

[0011] The signal test terminal 2 is connected to port 9 of the interface terminal of the panel to be tested, and ports 8 and 12 of the interface terminal of the panel to be tested are connected to the signal test terminal 1 through switches S4 and S6 respectively;

[0012] The signal test terminal 3 is connected to the port 10 of the interface terminal of the panel to be tested;

[0013] The signal test terminal 4 is connected to the port 11 of the interface terminal of the panel to be tested;

[0014] The voltage test terminal 3 is connected to the port 13 of the interface terminal of the panel to be tested;

[0015] The voltage test terminal 4 is connected to the port 14 of the interface terminal of the panel to be tested;

[0016] The signal generator is connected to port 15 of the interface end of the panel to be tested through the resistor R4, transistor Q1, and single-pole double-throw switch S5;

[0017] The oscilloscope is connected to port 15 of the interface end of the panel to be tested via a single-pole double-throw switch S5, and the other switch of the single-pole double-throw switch S5 is connected to port 8 of the interface end of the panel to be tested.

[0018] Preferably, the voltage test terminal 1 is provided with a current test terminal 1 for connecting an ammeter;

[0019] The voltage test terminal 2 is provided with a current test terminal 2 for connecting to an ammeter;

[0020] The voltage test terminal 3 is provided with a current test terminal 3 for connecting an ammeter.

[0021] Preferably, the resistance of the resistor R1 is 100KΩ; the resistance of the resistors R2, R3, and R4 is 10KΩ.

[0022] Preferably, the signal test terminal 2 is further provided with a plurality of external test ports.

[0023] Preferably, the transistor Q1 is an NPN transistor, and the base of the transistor Q1 is connected to the signal transmitting end of the signal generator, the collector is connected to one end of the single-pole double-throw switch S5, and the emitter is grounded.

[0024] Compared with the prior art, the beneficial effects of the present invention are: the aircraft ELT control panel test equipment, the panel interface end to be tested is connected to the various test ports of the test interface end, which can realize the test of voltage input and various output signals on the aircraft ELT control panel, ensuring that the input and output of the aircraft ELT control panel can operate stably, simplifying the testing process, and providing a complete and convenient set of test equipment for the testing of the ELT control panel, which is easy to use. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 It is a schematic diagram of the overall structure of the utility model.

[0026] In the figure: J202, voltage test terminal 1; J201, signal test terminal 1; J203, voltage test terminal 2; J204, signal test terminal 2; J212, signal test terminal 3; J205, signal test terminal 4; J206, voltage test terminal 3; J207, voltage test terminal 4; J210, signal generator; J208, oscilloscope; J301-2, current test terminal 1; J303-4, current test terminal 2; J305-6, current test terminal 3. DETAILED DESCRIPTION

[0027] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0028] In the description of this patent, it should be noted that, unless otherwise expressly specified or limited, the terms "installed," "connected," "connected," and "set" should be understood in a broad sense. For example, they can refer to fixed connection or set, detachable connection or set, or integral connection or set. Those skilled in the art will understand the specific meanings of the above terms in this patent based on the specific circumstances.

[0029] An aircraft ELT control panel test equipment, such as Figure 1 As shown, it includes: a panel interface end to be tested and a test interface end;

[0030] The panel interface terminal to be tested includes:

[0031] Ports 3 and 4 are 28V DC input ports;

[0032] Port 1 is AURAL CHIME signal output port;

[0033] Ports 2 and 5 are RST 2 and RST 1 signal output terminals respectively;

[0034] Port 6 is a 17V DC input port;

[0035] Port 7 is the EXTERNAL ON signal output port;

[0036] Port 8 is the ELT ON signal output port;

[0037] Port 15 is the signal receiving end;

[0038] Port 9 is the DC grounding terminal;

[0039] Port 12 is the MASTER LIGTHING TEST signal output port;

[0040] Port 10 is the MASTER CAUTION PULSE signal output port;

[0041] Port 11 is the MASTER CAUTION STEADYSTATE signal output port;

[0042] Port 13 is the 5V AC input port;

[0043] Port 14 is the AC grounding terminal.

[0044] The test interface end of the utility model includes:

[0045] The voltage test terminal 1J202 is connected to ports 3 and 4 of the interface terminal of the panel to be tested;

[0046] The signal test terminal 1J201 is connected to port 1 of the interface terminal of the panel to be tested, and ports 2 and 5 of the interface terminal of the panel to be tested are respectively connected to indicator light 1 and indicator light 2 through single-pole double-throw switches S1 and S2, and then connected in series to one end of the resistor R1, and the other end of the resistor R1 is connected to the signal test terminal 1J201;

[0047] The voltage test terminal 2J203 is connected to port 6 of the panel interface to be tested, and the other switch interface of the single-pole double-throw switches S1 and S2 is connected to port 6 of the panel interface to be tested; port 7 of the panel interface to be tested is connected to indicator light 3 through switch S3 and then to the voltage test terminal 2J203; port 10 of the panel interface to be tested is connected to the voltage test terminal 2J203 through resistor R2; port 11 of the panel interface to be tested is connected to the voltage test terminal 2J203 through resistor R3;

[0048] The signal test terminal 2J204 is connected to port 9 of the panel interface to be tested, and ports 8 and 12 of the panel interface to be tested are connected to the signal test terminal 1J201 through switches S4 and S6 respectively;

[0049] The signal test terminal 3J212 is connected to port 10 of the interface terminal of the panel to be tested;

[0050] The signal test terminal 4J205 is connected to port 11 of the interface terminal of the panel to be tested;

[0051] The voltage test terminal 3J206 is connected to port 13 of the interface terminal of the panel to be tested;

[0052] The voltage test terminal 4J207 is connected to port 14 of the interface terminal of the panel to be tested;

[0053] The signal generator J210 is connected to port 15 of the interface end of the panel to be tested through the resistor R4, transistor Q1, and single-pole double-throw fast switch S5;

[0054] The oscilloscope J208 is connected to port 15 of the interface end of the panel to be tested via a single-pole double-throw fast switch S5, and another switch of the single-pole double-throw fast switch S5 is connected to port 8 of the interface end of the panel to be tested.

[0055] Specifically, the voltage test terminal 1J202 is provided with a current test terminal 1J301-2 for connecting to an ammeter; the voltage test terminal 2J203 is provided with a current test terminal 2J303-4 for connecting to an ammeter; and the voltage test terminal 3J206 is provided with a current test terminal 3J305-6 for connecting to an ammeter. These are used to test the current of 28V DC input, 17V DC input, and 5V AC input.

[0056] Specifically, the resistance of the resistor R1 is 100KΩ; the resistance of the resistors R2, R3, and R4 is 10KΩ. It is used to perform signal stability testing on the AURAL CHIME signal, RST 2, RST 1 signal, MASTER CAUTION PULSE signal, and MASTERCAUTION STEADYSTATE signal according to test requirements.

[0057] Specifically, the signal test terminal 2J204 is further provided with a plurality of external test ports, which are used as spare external test ports to connect external devices to test the generated voltage value for parameters such as frequency and voltage.

[0058] Specifically, transistor Q1 is an NPN transistor, with its base connected to the signal transmitter of signal generator J210, its collector connected to one end of single-pole double-throw switch S5, and its emitter grounded. It is used to simulate and send various test signals to the interface of the panel under test according to test requirements, to test whether the interface can normally output various signals.

[0059] When the aircraft ELT control panel test equipment of this embodiment is in use, various test signals are sent to the interface end of the panel to be tested through the signal generator J210, and the interface end of the panel to be tested is then connected to the test ports of the test interface end, so as to realize the testing of parameters such as 28V DC input, AURAL CHIME signal output, RST 2, RST 1 signal output, 17V DC input, EXTERNAL ON signal output, ELT ON signal output, MASTER LIGTHING TEST signal output, MASTERCAUTION PULSE signal output, MASTERCAUTION STEADYSTATE signal output, and 5V AC input on the aircraft ELT control panel, thereby ensuring that the input and output of the aircraft ELT control panel can operate stably, simplifying the testing process, and providing a complete and convenient set of test equipment for the testing of the ELT control panel, which is easy to use.

[0060] The above shows and describes the basic principles, main features, and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The above embodiments and descriptions are merely preferred examples of the present invention and are not intended to limit the present invention. Various changes and improvements may be made to the present invention without departing from the spirit and scope of the present invention, and such changes and improvements fall within the scope of the present invention. The scope of protection claimed in the present invention is defined by the appended claims and their equivalents.

Claims

1. An aircraft ELT control panel test device, characterized in that: include: Interface end of the panel to be tested and test interface end; The test interface includes: The voltage test terminal 1 (J202) is connected to ports 3 and 4 of the panel to be tested; Signal test terminal 1 (J201) is connected to port 1 of the panel interface to be tested, and ports 2 and 5 of the panel interface to be tested are connected to indicator light 1 and indicator light 2 respectively through single-pole double-throw switches S1 and S2, and then connected in series to one end of resistor R1, and the other end of resistor R1 is connected to signal test terminal 1 (J201); The voltage test terminal 2 (J203) is connected to port 6 of the interface end of the panel to be tested, and the other switch interface of the single-pole double-throw switches S1 and S2 is connected to port 6 of the interface end of the panel to be tested; port 7 of the interface end of the panel to be tested is connected to indicator light 3 through switch S3 and then to the voltage test terminal 2 (J203); port 10 of the interface end of the panel to be tested is connected to the voltage test terminal 2 (J203) through resistor R2; port 11 of the interface end of the panel to be tested is connected to the voltage test terminal 2 (J203) through resistor R3; The signal test terminal 2 (J204) is connected to port 9 of the panel interface to be tested, and ports 8 and 12 of the panel interface to be tested are connected to the signal test terminal 1 (J201) through switches S4 and S6 respectively. Signal test terminal 3 (J212) is connected to port 10 of the interface terminal of the panel to be tested; Signal test terminal 4 (J205) is connected to port 11 of the interface terminal of the panel to be tested; The voltage test terminal 3 (J206) is connected to port 13 of the interface end of the panel to be tested; The voltage test terminal 4 (J207) is connected to port 14 of the interface end of the panel to be tested; The signal generator (J210) is connected to port 15 of the interface end of the panel to be tested through the resistor R4, transistor Q1, and single-pole double-throw switch S5; The oscilloscope (J208) is connected to port 15 of the interface end of the panel to be tested via a single-pole double-throw switch S5, and the other switch of the single-pole double-throw switch S5 is connected to port 8 of the interface end of the panel to be tested.

2. The aircraft ELT control panel test equipment according to claim 1, characterized in that: The voltage test terminal 1 (J202) is provided with a current test terminal 1 (J301-2) for connecting an ammeter; The voltage test terminal 2 (J203) is provided with a current test terminal 2 (J303-4) for connecting an ammeter; The voltage test terminal 3 (J206) is provided with a current test terminal 3 (J305-6) for connecting an ammeter.

3. The aircraft ELT control panel test equipment according to claim 1, characterized in that: The resistance value of the resistor R1 is 100KΩ; the resistance values of the resistors R2, R3, and R4 are 10KΩ.

4. The aircraft ELT control panel test equipment according to claim 1, characterized in that: The signal test terminal 2 (J204) is also provided with a plurality of external test ports.

5. The aircraft ELT control panel testing device according to claim 1, characterized in that: The transistor Q1 is an NPN transistor, and the base of the transistor Q1 is connected to the signal transmitting end of the signal generator (J210), the collector is connected to one end of the single-pole double-throw switch S5, and the emitter is grounded.

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