Aircraft emergency power supply capacity test box and power supply capacity test method thereof

Abstract

The present invention discloses an aircraft emergency power supply capacity test box and a power supply capacity test method thereof, which belong to the scope of aircraft detection technology. The test box is composed of a discharge load, a voltmeter, a timer, a relay, an indicator light, and a wiring block. All components are installed in a machine box, and 220VAC is connected to the power supply switch of the test box through the wiring block T1; the present invention adopts a constant resistance discharge method, that is, a 1 ohm high-power resistor equipped with a cooling fan is used for discharge, and the voltage value and discharge time of the aircraft emergency power supply are monitored in real time; during the discharge process, when the emergency power supply voltage is lower than the set value, the discharge process is automatically cut off, thereby realizing the automatic test power supply capacity test of the emergency power supply; this power supply capacity test box is small in size and easy to move. At the same time, the control panel is simple, the adjustment accuracy is high, the operation is convenient, easy to adjust and monitor, and the work efficiency is high; the present invention can meet the test requirements of aircraft emergency power supplies and has a wide range of applications.

Description

Technical Field

[0001] The invention belongs to the scope of aircraft detection technology, and particularly relates to an aircraft emergency power capacity test box and a power capacity test method thereof. Background Art

[0002] The emergency power supply on the aircraft plays a very important role in the safe flight of the aircraft. When the aircraft power supply is normal, the aircraft charges the emergency power supply to ensure that the emergency power supply has sufficient capacity. In the event of an emergency during the flight, the aircraft emergency power supply provides lighting for the cabin to ensure that passengers can escape safely in the event of an emergency, and to ensure the personal and property safety of relevant personnel. In order to ensure the flight safety of the aircraft, the aircraft emergency power supply needs to be maintained and capacity tested at any time. The capacity is calculated by directly measuring the voltage and current of the emergency power supply, which has a large error, cannot guarantee the maintenance quality, and has low work efficiency. Summary of the invention

[0003] The purpose of the present invention is to propose an aircraft emergency power supply capacity test box and a power supply capacity test method thereof; the feature is, an aircraft emergency power supply capacity test box; the feature is that the aircraft emergency power supply capacity test box includes a power supply end circuit and a load control end circuit; wherein the power supply end circuit of the test box is 220VAC and one side of the power supply switch S1 of the test box is connected to the T1-3 terminal of the wiring bank T1, and is connected to the neutral line of the AC power supply; the other side of the power supply switch S1 divides the 220VAC into two strands, which are respectively connected to the T1-1 terminal and the T1-2 terminal of the wiring bank T1, wherein the T1-1 terminal of the wiring bank T1 is connected to the voltage controller M1 and the timer MT1 of the load control end; and power is supplied to the voltage controller M1 and the timer MT1; specifically, the T1-1 terminal is connected to the common contact of the T1-3 terminal, the K1 relay, and the K2 relay through the indicator light, one end of the indicator switch S2, and one end of the contact K2s of the K2 relay; and the indicator switch S2 The other end, the contact K2s of relay K2, is connected to timer MT1 to form a loop; the T1-2 terminal of terminal block T1 is connected to fuse F1;

[0004] At the load control end, the outputs of the parallel K1 relay and K2 relay are connected to the voltage controller M1; the output end of the voltage controller M1 is connected to both ends of the pre-position switch S3 and the first and second terminals of the plug J1 / P1; the load resistor R1 is connected to the test plug P3 through the first and second terminals of the plug J1 / P1 via both ends of the contact K1s of the relay K1 and both ends of the pre-position switch S3, thereby being connected to the device under test through the plug P3.

[0005] The left side of the panel of the aircraft emergency power supply capacity test box is equipped with a timer MT1 and a voltage controller M1; the right side is equipped with a power switch S1, an indicator switch S2, and a pre-position switch S3 from top to bottom; and the middle part is an audible and visual alarm.

[0006] A power capacity test method for an aircraft emergency power capacity test box; characterized in that the power capacity test method adopts a constant resistance discharge method, that is, the load resistor R1 adopts a 1 ohm 100 watt high-power resistor for discharge, and is equipped with a cooling fan to ensure safety and reliability during the emergency power test; the voltage value and discharge time of the aircraft emergency power supply are monitored in real time; when the emergency power supply voltage is lower than the set value during the discharge process, the discharge process is automatically cut off, the timer stops timing, and an audible and visual alarm is issued, thereby realizing automatic testing of the emergency power supply; the specific operation process is as follows:

[0007] (1). Connect the 220Vac power supply and turn on the power switch on the back of the test box;

[0008] (2) Turn switch S1 to the "off" position and switch S2 to the "release" position;

[0009] 3. Connect the discharge cable connector to the emergency power supply, paying attention to the polarity, positive (+) and negative (-);

[0010] 4. Press the reset button on the timer to reset the timer;

[0011] 5. Turn the power switch S1 to the "discharge" position, and at the same time turn the pre-position switch S3 to the "pre-position" position to start the discharge procedure and begin measurement;

[0012] 6. When the voltage controller M1 detects that the voltage of the emergency power supply is lower than the preset value, the voltage controller M1 controls the K2 relay to energize its coil, the contact K2s is energized, and the K1 relay is controlled by the voltage controller M1. Its contact K1s is disconnected, so that the power supply circuit of the sound and light alarm is energized, and the sound and light alarm sends out an alarm signal; at the same time, the control circuit of the timer MT1 is energized, and the system automatically disconnects the discharge circuit, causing the timer to stop timing and complete the discharge procedure; the discharge time and the termination voltage are automatically displayed on the panel; in addition, the contact K1s of the K1 relay is disconnected, and an sound and light alarm is issued at the same time; the connected load resistor R1 is disconnected at the same time, and the emergency power supply is stopped;

[0013] 7. Turn switch S2 to the "release" position, turn off the alarm, remove the discharge cable, and turn off the power switch.

[0014] The beneficial effect of the present invention is that the aircraft emergency power supply capacity test is to realize the continuous and monitorable capacity test (i.e., discharge test) of the aircraft emergency power supply through circuit design. The present invention is easy to operate and can complete the test process quickly and automatically without the need for continuous operation by maintenance personnel; it can meet the test requirements of various types of aircraft emergency power supplies and has a wide range of applications. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 This is the circuit diagram of the emergency power supply test box.

[0016] Figure 2 This is a diagram of the test box panel. DETAILED DESCRIPTION

[0017] The present invention provides an aircraft emergency power supply capacity test box, which includes electrical devices such as a discharge load, a voltage controller, a timer, a relay, an indicator light, a terminal block, a switch, etc., and all the components are installed in a machine box. The present invention is further described below in conjunction with the accompanying drawings.

[0018] like Figure 1 Shown is the circuit diagram of the emergency power supply test box. Figure 2 The panel diagram of the test box is shown. The aircraft emergency power supply capacity test box includes a power supply circuit and a load control circuit; wherein the power supply circuit of the test box is 220VAC and one side of the power switch S1 is connected to the T1-3 terminal of the wiring bank T1, and is connected to the neutral line of the AC power supply; the other side of the power switch S1 divides the 220VAC into two strands, which are respectively connected to the T1-1 terminal and the T1-2 terminal of the wiring bank T1, wherein the T1-1 terminal of the wiring bank T1 is connected to the voltage controller M1 and the timer MT1 of the load control end; and power is supplied to the voltage controller M1 and the timer MT1; specifically, the T1-1 terminal is connected to the common contact of the T1-3 terminal, the K1 relay, and the K2 relay through the indicator light, one end of the indicator switch S2, and one end of the contact K2s of the K2 relay; and the other end of the indicator switch S2 and the other end of the contact K2s of the relay K2 are connected to the timer MT1 to form a loop; the T1-2 terminal of the wiring bank T1 is connected to the fuse F1.

[0019] At the load control end, the outputs of the parallel K1 relay and K2 relay are connected to the voltage controller M1; the output end of the voltage controller M1 is connected to both ends of the pre-position switch S3 and the first and second terminals of the plug J1 / P1; the load resistor R1 is connected to the test plug P3 through the first and second terminals of the plug J1 / P1 via both ends of the contact K1s of the relay K1 and both ends of the pre-position switch S3, thereby being connected to the device under test through the plug P3.

[0020] The left side of the panel of the aircraft emergency power supply capacity test box is equipped with a timer MT1 and a voltage controller M1; the right side is equipped with a power switch S1, an indicator switch S2, and a pre-position switch S3 from top to bottom; and the middle part is an audible and visual alarm.

[0021] The power capacity test method of the aircraft emergency power capacity test box; the method adopts a constant resistance discharge method, and the emergency power capacity can be known by the change of discharge current and voltage within a certain period of time, that is, the load resistor R1 adopts a 1 ohm 100 watt high-power resistor for discharge, and is equipped with a cooling fan to ensure safety and reliability during the emergency power test; the voltage value and discharge time of the aircraft emergency power supply are monitored in real time; when the emergency power supply voltage is lower than the set value during the discharge process, the discharge process is automatically cut off, the timer stops timing, and an audible and visual alarm is issued, thereby realizing automatic testing of the emergency power supply; the specific operation process is as follows:

[0022] (3) Connect the 220Vac power supply and turn on the power switch on the back of the test box;

[0023] (4) Turn switch S1 to the "off" position and turn switch S2 to the "release" position;

[0024] 3. Connect the discharge cable connector to the emergency power supply, paying attention to the polarity: positive (+) and negative (-);

[0025] 4. Press the reset button on the timer to reset the timer;

[0026] 5. Turn the power switch S1 to the "discharge" position, and at the same time turn the pre-position switch S3 to the "pre-position" position to start the discharge procedure and begin measurement;

[0027] 6. When the voltage controller M1 detects that the voltage of the emergency power supply is lower than the preset value, the voltage controller M1 controls the K2 relay to energize its coil, the contact K2s is energized, and the K1 relay is controlled by the voltage controller M1. Its contact K1s is disconnected, so that the power supply circuit of the sound and light alarm is energized, and the sound and light alarm sends out an alarm signal; at the same time, the control circuit of the timer MT1 is energized, and the system automatically disconnects the discharge circuit, causing the timer to stop timing and complete the discharge procedure; the discharge time and the termination voltage are automatically displayed on the panel; in addition, the contact K1s of the K1 relay is disconnected, and an sound and light alarm is issued at the same time; at the same time, the connected load resistor R1 is disconnected to stop the emergency power supply;

[0028] 7. Turn switch S2 to the "release" position, turn off the alarm, remove the discharge cable, and turn off the power switch.

[0029] After the discharge procedure is completed, the emergency power supply voltage will rise again because the load discharge circuit has been disconnected and the emergency power supply is in a no-load state. If you want to continue testing other emergency power supplies, you need to follow the operating steps again.

[0030] Equipment power supply: The aircraft emergency power supply test box is powered by 220VAC, which makes it easy to find the power supply equipment and has simple usage conditions.

[0031] Connection method: The aircraft emergency power supply test box adopts a special connection plug, and its positive and negative terminals can be tightly and firmly connected with the positive and negative terminals of the emergency power supply under test to ensure the safety of the test.

[0032] In summary, the present invention realizes a continuously monitorable capacity test (i.e., a discharge test) of an aircraft emergency power supply through circuit design. The present invention is easy to operate and can complete the test process quickly and automatically without the need for continuous operation by maintenance personnel. It can meet the test requirements of various types of aircraft emergency power supplies and has a wide range of applications.

Claims

1. An aircraft emergency power supply capacity test box, characterized in that: The aircraft emergency power supply capacity test box includes a power supply end circuit and a load control end circuit; wherein the power supply end circuit of the test box is 220VAC and one side of the power supply switch S1 of the test box is connected to the T1-3 terminal of the wiring bank T1, and is connected to the neutral line of the AC power supply; the other side of the power supply switch S1 divides the 220VAC into two strands, which are respectively connected to the T1-1 terminal and the T1-2 terminal of the wiring bank T1, wherein the T1-1 terminal of the wiring bank T1 is connected to the voltage controller M1 and the timer MT1 of the load control end; and power is supplied to the voltage controller M1 and the timer MT1; specifically, the T1-1 terminal is connected to the common contact of the T1-3 terminal, the K1 relay, and the K2 relay through the indicator light, one end of the indicator switch S2, and one end of the contact K2s of the K2 relay; and the other end of the indicator switch S2 and the other end of the contact K2s of the relay K2 are connected to the timer MT1 to form a loop; the T1-2 terminal of the wiring bank T1 is connected to the fuse F1; At the load control end, the outputs of the parallel K1 relay and K2 relay are connected to the voltage controller M1; the output end of the voltage controller M1 is connected to both ends of the pre-position switch S3 and the first and second terminals of the plug J1 / P1; The load resistor R1 is connected to the test plug P3 via the first and second terminals of the plug J1 / P1 through the two ends of the contact K1s of the relay K1 and the two ends of the pre-position switch S3, thereby being connected to the device under test through the plug P3.

2. The aircraft emergency power supply capacity test box according to claim 1, characterized in that: The left side of the panel of the aircraft emergency power supply capacity test box is equipped with a timer MT1 and a voltage controller M1; the right side is equipped with a power switch S1, an indicator switch S2, and a pre-position switch S3 from top to bottom; and the middle part is an audible and visual alarm.

3. A power capacity testing method for the aircraft emergency power capacity testing box according to claim 2, characterized in that: The power capacity test method adopts a constant resistance discharge method, that is, the load resistor R1 adopts a 1 ohm 100 watt high-power resistor for discharge, and is equipped with a cooling fan to ensure safety and reliability during the emergency power supply test; the voltage value and discharge time of the aircraft emergency power supply are monitored in real time; when the emergency power supply voltage is lower than the set value during the discharge process, the discharge process is automatically cut off, the timer stops timing, and an audible and visual alarm is issued, thereby realizing automatic testing of the emergency power supply; the specific operation process is as follows: (1). Connect the 220Vac power supply and turn on the power switch on the back of the test box; (2) Turn switch S1 to the "off" position and turn switch S2 to the "release" position; (3) Connect the discharge cable connector to the emergency power supply, paying attention to the positive and negative poles; (4) Press the reset button on the timer to reset the timer; (5) Turn the power switch S1 to the "discharge" position and the pre-position switch S3 to the "pre-position" position to start the discharge procedure and begin measurement; (6) When the voltage controller M1 detects that the voltage of the emergency power supply is lower than the preset value, the voltage controller M1 controls the K2 relay to energize its coil, the contact K2s is energized, and the K1 relay is controlled by the voltage controller M1 to disconnect its contact K1s, thereby energizing the power supply circuit of the sound and light alarm, and the sound and light alarm sends out an alarm signal; at the same time, the control circuit of the timer MT1 is energized, and the system automatically disconnects the discharge circuit, causing the timer to stop timing and complete the discharge procedure; the discharge time and the termination voltage are automatically displayed on the panel; in addition, the contact K1s of the K1 relay is disconnected, and an sound and light alarm is issued at the same time; the connected load resistor R1 is disconnected, and the emergency power supply is stopped; (7) Turn switch S2 to the "release" position, turn off the alarm, remove the discharge cable, and turn off the power switch.

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