Helicopter fuel transfer electromagnetic conversion valve in-situ detection device

Abstract

The utility model relates to an electromagnetic change-over valve detection device. A helicopter fuel transfer electromagnetic change-over valve in-situ detection device comprises a power switch K0 and a detection loop, and the detection loop comprises a detection switch I and a first detection loop plug set. One plug in the first detection loop plug group is connected with a control coil of the test piece 1, and the other plug is connected with a feedback circuit of the test piece 1; the inside of the first detection loop plug group is connected with a power supply through a detection switch I and a power switch K0; in addition, a test piece 1 work normal indicating lamp A1 is connected in a feedback circuit of the first detection loop plug group connected with the test piece 1. According to the in-situ detection device for the helicopter fuel transfer electromagnetic change-over valve, on-board in-situ detection can be carried out on the working condition of the electromagnetic change-over valve under the condition that the electromagnetic change-over valve is not disassembled and assembled, and the outfield use requirement can be well met.

Description

TECHNICAL FIELD

[0001] The utility model relates to an electromagnetic conversion valve detection device, especially to a device capable of detecting the working condition of the electromagnetic conversion valve of the fuel transfer system of a helicopter in situ, which facilitates the field use of the helicopter. BACKGROUND

[0002] The fuel transfer system is an important component of the fuel system of a certain type of helicopter, and is mainly used to realize the on-demand distribution of fuel among various fuel tanks on the helicopter, balance the center of gravity of the helicopter, and maximize the utilization rate of fuel on the helicopter in emergency situations. The electromagnetic conversion valve is an important component of the fuel transfer system, and is used to open or close the oil circuit according to system control instructions. It is composed of an electromagnet, an upper spring, a valve, a valve seat, a rubber diaphragm, a connecting rod, a lower spring, a connecting piece, and a feedback circuit. In the initial state, the valve is pushed against the valve seat by the force of the upper spring, the oil circuit is closed, and the lower end of the connecting rod is pushed against the connecting piece, causing the feedback circuit to be disconnected. During normal operation, the system outputs control instructions, the upper electromagnet of the electromagnetic conversion valve is powered on, the connecting rod moves upward under the action of the electromagnetic force, overcoming the force of the upper spring, the valve gradually separates from the valve seat, the oil circuit gradually opens, and at the same time, the pressure of the lower end of the connecting rod against the connecting piece decreases, the connecting piece moves upward under the action of the lower spring force, the lower feedback circuit is connected, and the feedback electromagnetic conversion valve sends an opening signal. In actual use, there have been many cases of fuel transfer failure due to the failure of the feedback circuit to connect. In view of this situation, considering that there are no related detection instruments and equipment in the field, it is impossible to accurately grasp the working condition of the electromagnetic conversion valve in time, which may cause safety hazards for flight. From the perspective of improving the quality of helicopter field maintenance and support, according to the working principle of the electromagnetic conversion valve, the utility model designs an electromagnetic conversion valve in-situ detection device, which can conveniently and quickly detect the working condition of the electromagnetic conversion valve in situ on the helicopter. SUMMARY

[0003] The utility model provides a kind of helicopter fuel transfer electromagnetic conversion valve in-situ detection device, can be in-situ detected on the helicopter to the working condition of electromagnetic conversion valve without disassembling electromagnetic conversion valve, it is convenient to operate and use, and detection efficiency is high.

[0004] The utility model adopts the technical scheme of:

[0005] The in-situ detection device of the helicopter fuel transfer electromagnetic conversion valve comprises a power switch (K0) and a detection circuit, the detection circuit comprises a detection switch I (K1), a first detection circuit plug group (1), one plug in the first detection circuit plug group (1) is connected with a control coil of a test piece 1, and the other plug is connected with a feedback circuit of the test piece 1, the first detection circuit plug group is connected with a power supply through the detection switch I (K1) and the power switch (K0), and a test piece 1 normal working indicator lamp (A1) is connected in the feedback circuit of the test piece 1 connected with the first detection circuit plug group (1).

[0006] The in-situ detection device of the helicopter fuel transfer electromagnetic conversion valve, the detection circuit comprises a detection switch II (K2), a second detection circuit plug group (2), one plug in the second detection circuit plug group (2) is connected with a control coil of a test piece 2, and the other plug is connected with a feedback circuit of the test piece 2, the second detection circuit plug group is connected with a power supply through the detection switch II (K2) and the power switch (K0), and a test piece 2 normal working indicator lamp (A2) is connected in the feedback circuit of the test piece 2 connected with the second detection circuit plug group (2).

[0007] The in-situ detection device of the helicopter fuel transfer electromagnetic conversion valve, a test power supply can use a 28V DC power supply on an aircraft, is led out through a power cord (4) provided with a plug and is connected with the detection circuit through the power switch (K0), and the test power supply also uses a rechargeable lithium battery, a positive pole of the lithium battery is connected with the detection circuit through the power switch (K0), and a power supply indicator lamp (A0) is connected between one side of an output end of the power switch (K0) and a negative pole of the power supply.

[0008] The in-situ detection device of the helicopter fuel transfer electromagnetic conversion valve, the power switch (K0), the power supply indicator lamp (A0) and the detection switch I (K1), the detection switch II (K2), the first detection circuit plug group (1), the second detection circuit plug group (2), the test piece 1 normal working indicator lamp (A1) and the test piece 2 normal working indicator lamp (A2) are arranged on the device shell.

[0009] The in-situ detection device of the helicopter fuel transfer electromagnetic conversion valve has the beneficial effects that:

[0010] 1、The in-situ detection device of the helicopter fuel transfer electromagnetic conversion valve can detect the working condition of the electromagnetic conversion valve on the aircraft without disassembling the electromagnetic conversion valve, is convenient to operate and use, has high detection efficiency and can well meet the use requirements of the field in various site environmental conditions.

[0011] 2, The utility model discloses a helicopter fuel transfer electromagnetic conversion valve in situ detection device, simple structure, small, use machine 28V DC power supply, can realize electromagnetic conversion valve single detection or two simultaneous detection, and detection efficiency is high. BRIEF DESCRIPTION OF DRAWINGS

[0012] Figure 1 As shown is the utility model detection device external shape schematic view,

[0013] Figure 2 As shown is the utility model detection device circuit principle diagram. DETAILED DESCRIPTION

[0014] In order to make the technical concept and the advantages of the invention realize its invention purpose more clearly and clearly, the technical scheme of the utility model is further described in detail below in conjunction with the drawings. It should be understood that the following examples are only used to explain and illustrate the preferred embodiment of the utility model, and should not be regarded as and constitute the limitation of the patent protection scope required by the utility model. EMBODIMENT

[0015] Referring to Figure 1 、 Figure 2 The utility model discloses a helicopter fuel transfer electromagnetic conversion valve in situ detection device, including power switch K0 and detection circuit, the detection circuit includes detection switch I (K1), first detection circuit plug group 1;One plug in the first detection circuit plug group 1 is connected to the control coil of test piece 1, and the other is connected to the feedback circuit of test piece 1;The first detection circuit plug group is connected to the power supply through detection switch I (K1) and power switch K0;And, in the feedback circuit of test piece 1 that first detection circuit plug group 1 is connected, there is test piece 1 normal operation indicating lamp A1.

[0016] Test power uses machine 28V DC power supply, is led out through the power cord 4 with plug and is connected to detection circuit through power switch K0;There is power indicating lamp A0 between the output end side of power switch K0 and the negative pole of power supply.

[0017] The power switch K0, power indicating lamp A0 and detection switch I (K1), first detection circuit plug group 1 and test piece 1 normal operation indicating lamp A1 are arranged on device housing 3. EMBODIMENT

[0018] The helicopter fuel transfer electromagnetic conversion valve in situ detection device of the embodiment is different from the embodiment 1 in that test power uses rechargeable lithium battery, and the positive pole of lithium battery output is connected to detection circuit through power switch K0;There is power indicating lamp A0 between the output end side of power switch K0 and the negative pole of lithium battery. The device housing is provided with battery compartment. EMBODIMENT

[0019] The in-situ detection device for the helicopter fuel transfer electromagnetic conversion valve of the embodiment is different from that of the embodiment 1 in that: further, the detection circuit comprises a detection switch II (K2) and a second detection circuit plug group 2; one plug in the second detection circuit plug group 2 is connected to the control coil of the test piece 2, and the other is connected to the feedback circuit of the test piece 2; the second detection circuit plug group is connected to the power supply through the detection switch II (K2) and the power supply switch K0; and the working normal indicator lamp A2 of the test piece 2 is connected in the feedback circuit of the test piece 2 connected to the second detection circuit plug group 2.

[0020] The power supply switch K0, the power supply indicator lamp A0, the detection switch I (K1), the detection switch II (K2), the first detection circuit plug group 1, the second detection circuit plug group 2, the working normal indicator lamp A1 of the test piece 1 and the working normal indicator lamp A2 of the test piece 2 are all arranged on the device housing 3.

[0021] Similarly, the test power supply uses the 28V DC power supply on the machine, is led out through the power supply line 4 with a plug and is connected to the detection circuit through the power supply switch K0; the test power supply can also use a rechargeable lithium battery, and the positive output of the lithium battery is connected to the detection circuit through the power supply switch K0; and the battery compartment is arranged in the device housing.

[0022] The working principle of the in-situ detection device for the helicopter fuel transfer electromagnetic conversion valve of the utility model is as follows:

[0023] Before testing, the power supply line 4 with a plug is connected to the 28V DC power supply socket in the helicopter passenger and cargo compartment, the detection plug is connected to the two plugs on the electromagnetic conversion valve through a wire (when a single electromagnetic conversion valve is detected, the first detection circuit plug group or the second detection circuit plug group can be used; when two electromagnetic conversion valves are detected, the first detection circuit plug group and the second detection circuit plug group are used at the same time), the power supply switch K0 is turned on, the power supply indicator lamp A0 is bright, and it is indicated that the 28V DC power supply on the machine is normally powered. When detecting, the detection switch is turned on, the control coil (the electromagnetic coil) of the electromagnetic conversion valve is powered, the electromagnetic conversion valve is actuated, the feedback circuit thereof is connected, at this time, the working normal indicator lamp corresponding to the electromagnetic conversion valve is bright, indicating that the electromagnetic conversion valve is in normal working condition, if the working normal indicator lamp of the electromagnetic conversion valve is not bright, it indicates that the electromagnetic conversion valve has a fault, and needs to be disassembled for troubleshooting or replacement.

[0024] The in-situ detection device for the helicopter fuel transfer electromagnetic conversion valve of the utility model can detect the working condition of the electromagnetic conversion valve on the machine without disassembling the electromagnetic conversion valve, can well meet the field use requirements, uses the 28V DC power supply on the machine for power supply, is convenient to use, can realize single detection or simultaneous detection of two electromagnetic conversion valves, and has high detection efficiency.

Claims

1. A helicopter fuel transfer electromagnetic conversion valve in-situ detection device, comprising a power switch (K0) and a detection circuit, characterized in that: The detection circuit includes detection switch I (K1), first detection circuit plug group (1); one plug in the first detection circuit plug group (1) is connected with the control coil of test piece 1, and the other is connected with the feedback circuit of test piece 1; the first detection circuit plug group is connected with the power supply through detection switch I (K1) and power switch (K0) inside; and the working normal indicator light (A1) of test piece 1 is connected in the feedback circuit of test piece 1 connected with the first detection circuit plug group (1).

2. The helicopter fuel transfer electromagnetic conversion valve in situ detection device of claim 1, wherein: The detection circuit includes detection switch II (K2), second detection circuit plug group (2); one plug in the second detection circuit plug group (2) is connected with the control coil of test piece 2, and the other is connected with the feedback circuit of test piece 2; the second detection circuit plug group is connected with the power supply through detection switch II (K2) and power switch (K0) inside; the working normal indicator light (A2) of test piece 2 is connected in the feedback circuit of test piece 2 connected with the second detection circuit plug group (2).

3. The in situ detection device for a helicopter fuel transfer electromagnetic conversion valve according to claim 1 or 2, characterized in that: The test power supply uses 28V DC power supply on the machine, which is led out through the power line (4) with plug and connected with the detection circuit through the power switch (K0); the power indicator light (A0) is connected between the output side of the power switch (K0) and the negative pole of the power supply.

4. The in situ detection device for a helicopter fuel transfer electromagnetic conversion valve according to claim 3, characterized in that: The device shell is provided with the power switch (K0), the power indicator light (A0), the detection switch I (K1), the first detection circuit plug group (1) and the working normal indicator light (A1) of test piece 1.

5. The in situ detection device for a helicopter fuel transfer electromagnetic conversion valve according to claim 1 or 2, characterized in that: The test power supply uses rechargeable lithium battery, and the positive pole of the lithium battery output is connected with the detection circuit through the power switch (K0); the power indicator light (A0) is connected between the output side of the power switch (K0) and the negative pole of the lithium battery.

6. The in situ detection device for a helicopter fuel transfer electromagnetic conversion valve according to claim 5, characterized in that: The device shell is provided with the power switch (K0), the power indicator light (A0), the detection switch I (K1), the first detection circuit plug group (1) and the working normal indicator light (A1) of test piece 1; the device shell is provided with the battery compartment.

7. The in situ detection device for a helicopter fuel transfer electromagnetic conversion valve according to claim 2, characterized in that: The device shell is provided with the power switch (K0), the power indicator light (A0), the detection switch I (K1), the first detection circuit plug group (1) and the working normal indicator light (A1) of test piece 1; the device shell is provided with the battery compartment.

8. The in situ detection device for a helicopter fuel transfer electromagnetic conversion valve according to claim 2, characterized in that: The utility model relates to a test device for lithium battery, including shell (3), test power supply uses rechargeable lithium battery, and lithium battery output positive pole is connected detection circuit through power switch (K0), and the power switch (K0) is connected with the power indication lamp (A0) between lithium battery negative pole on the output end one side of power switch (K0), and the power switch (K0), power indication lamp (A0) and detection switch I (K1), detection switch II (K2), first detection circuit plug group (1), second detection circuit plug group (2), test piece 1 work normal indication lamp (A1), test piece 2 work normal indication lamp (A2) are all set up on the device shell.

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