An aircraft overheat detection loop detection switching device and method

Abstract

An aircraft overheat detection loop detection switching device and method, comprising a first BMC loop selection switch, a second BMC loop selection switch and a BMC selection switch, a connection plug for connecting with an aircraft device port is arranged at the rear end of the device, the BMC selection switch is used for selecting the detected loop, and the first BMC loop selection switch and the second BMC loop selection switch are used for selecting the items of the selected loop. By providing an A series aircraft detection overheat detection loop resistance switching device for detecting the wing, the engine and the auxiliary power unit APU, only one installation of the device to the aircraft is needed when performing these detection works, and then the corresponding system and loop can be accurately connected to the detected loop by selecting the switch. During the detection process, the jumper is not needed to be pulled out and inserted, the risk of pulling out and inserting the jumper is avoided, the working time is reduced, and the purposes of improving the working efficiency and safe construction are achieved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of A320 aircraft detection equipment, in particular to an aircraft overheat detection loop detection switching device and method. BACKGROUND

[0002] The overheat detection loop of A320 series aircraft is used to monitor the hot air pipeline in the large wing, engine nacelle, auxiliary power unit (APU) cabin and large wing of the aircraft to prevent damage to the structure and accessories near the pipeline after air leakage or pipeline rupture. The system is composed of two air management computers (BMC) and multiple overheat detection loops. Each detection loop is composed of multiple detection elements in series, with 14 detection elements in the left wing A and B loops, 9 detection elements in the right wing A and B loops, 8 detection elements in the APU, and 1 detection element in each of the left and right engine pylons. The aircraft requires detection of the state of the loop to ensure its normal operation during each inspection. In addition, due to weather and environmental factors, detection element failure often occurs during flight and inspection, and the core resistance and insulation resistance of the detection element need to be detected to troubleshoot the fault.

[0003] The detection procedure of Airbus does not provide the required auxiliary equipment, and the current construction process requires manual insertion of two jumpers of the detection equipment into the plug of the air management computer (BMC) on the aircraft. After detecting each loop, the jumpers need to be removed and reinstalled in the plug of the other loop on the aircraft. This method not only takes time and effort, but also has the risk of inserting the jumpers into the wrong plug hole and increasing the risk of damaging the plug pins on the aircraft. SUMMARY

[0004] The technical problem to be solved by the present application is to provide an aircraft overheat detection loop detection switching device and method, and to provide an overheat detection loop resistance switching device for detecting the large wing, engine and auxiliary power unit (APU) of A320 series aircraft. When performing these detection tasks, only one installation of the device is required on the aircraft, and then the corresponding system and loop can be accurately connected to the loop to be detected by selecting the switch. During the detection process, the jumpers do not need to be removed and inserted, avoiding the risk of removing and inserting the jumpers and reducing the working time, thereby achieving the purpose of improving work efficiency and safe construction.

[0005] To solve the above technical problems, the technical solution adopted by the present application is:

[0006] The application discloses an aircraft overheat detection loop detection switching device, which is a cuboid device, and is provided with a front interaction panel at the front end of the device. The front interaction panel is provided with three selection switches, namely a first BMC loop selection switch, a second BMC loop selection switch and a BMC selection switch. The front interaction panel is provided with a detection end output port for connecting with an external detection device. The device is provided with a connecting plug at the rear end of the device for connecting with an aircraft device port. The BMC selection switch is used for selecting a detection loop. The first BMC loop selection switch and the second BMC loop selection switch are used for selecting items of the selected loop.

[0007] One end of the BMC selection switch is a selection knob. The other end of the BMC selection switch is connected with the first BMC loop selection switch and the second BMC loop selection switch.

[0008] The detection end output port is provided with three wiring ends, namely an output end 1, an output end 2 and an output ground. The output end 1 and the output end 2 are electrically connected with the selection knob end of the BMC selection switch in the aircraft overheat detection loop detection switching device. The output ground is connected with the shell of the aircraft overheat detection loop detection switching device. The shell of the aircraft overheat detection loop detection switching device can be connected with the ground wire of the aircraft device port.

[0009] The first BMC loop selection switch is a rotary knob selection switch and is provided with four groups of selection loops in two groups. The four groups of loops are an APU detection loop, a right wing A detection loop, a left wing A detection loop and a left engine suspension detection loop in sequence.

[0010] The second BMC loop selection switch is a rotary knob selection switch and is provided with four groups of selection loops in two groups. The four groups of loops are an NC open loop, a left wing B detection loop, a right wing B detection loop and a right engine suspension detection loop in sequence. The NC open loop terminal is suspended.

[0011] The last three groups of loops of the first BMC loop selection switch and the second BMC loop selection switch are electrically connected with the connecting plug in sequence after being short-circuited one by one. The APU detection loop of the first BMC loop selection switch is electrically connected with the connecting plug.

[0012] The aircraft device port is a No. 1 BMC bleed air management machine or a No. 2 BMC bleed air management machine.

[0013] The No. 1 BMC bleed air management machine is provided with four groups of detection loop ports in two groups. The four groups of detection loop ports are an APU detection loop, a right wing A detection loop, a left wing A detection loop and a left engine suspension detection loop.

[0014] The No. 2 BMC bleed air management machine has two sets of three sets of detection loop ports, which are respectively left large wing B detection loop, right large wing B detection loop and right engine suspension detection loop, and the positions of the three sets of ports correspond to the positions of the right large wing A detection loop, left large wing A detection loop and left engine suspension detection loop of the No. 1 BMC bleed air management machine.

[0015] The lower end of the front interaction panel is provided with an L-shaped lock.

[0016] The detection method of the switching device by using the aircraft overheat detection loop comprises the following steps:

[0017] Step one, remove the No. 1 or No. 2 BMC bleed air management machine from the aircraft equipment rack;

[0018] Step two, connect the removed No. 1 or No. 2 BMC bleed air management machine with the connection plug of the aircraft overheat detection loop detection switching device;

[0019] Step three, connect the locking device at the aircraft end with the L-shaped lock (6) of the aircraft overheat detection loop detection switching device, and tighten to make the two firmly installed;

[0020] Step four, select the corresponding gear on the BMC selection switch according to whether the No. 1 BMC bleed air management machine or the No. 2 BMC bleed air management machine is currently connected, so that the first BMC loop selection switch corresponds to the No. 1 BMC bleed air management machine, or the second BMC loop selection switch corresponds to the No. 2 BMC bleed air management machine;

[0021] Step five, connect the ground end of the No. 1 or No. 2 BMC bleed air management machine with the ground end of the aircraft overheat detection loop detection switching device, so as to realize the connection between the output ground end of the detection end output port and the shell of the aircraft overheat detection loop detection switching device;

[0022] Step six, connect the three output ports of the detection end output port by using the resistance and impedance external detection device, and detect the corresponding detection loop by selecting the position of the knob on the first BMC loop selection switch or the second BMC loop selection switch.

[0023] The aircraft overheat detection loop detection switching device and method provided by the application can realize accurate connection to the detected loop by selecting the corresponding system and loop through the selection switch after installing the device to the aircraft only once when performing the detection work, and the risk of plugging and unplugging the jumper is avoided, the working time is reduced, and the purpose of improving the working efficiency and safe construction is achieved. BRIEF DESCRIPTION OF DRAWINGS

[0024] The application will be further described in connection with the accompanying drawings and embodiments:

[0025] Figure 1 Front view of the aircraft overheat detection loop detection switching device of the application;

[0026] Figure 2 Left view of the aircraft overheat detection loop detection switching device;

[0027] Figure 3 Rear view of the aircraft overheat detection loop detection switching device;

[0028] Figure 4 Top view of the aircraft overheat detection loop detection switching device;

[0029] Figure 5 Perspective view of the aircraft overheat detection loop detection switching device Figure 1 ;

[0030] Figure 6 Perspective view of the aircraft overheat detection loop detection switching device Figure 2 ;

[0031] Figure 7 Internal electrical connection schematic diagram of the aircraft overheat detection loop detection switching device.

[0032] Wherein: the first BMC loop selection switch 1, the second BMC loop selection switch 2, the BMC selection switch 3, the detection end output port 4, the handle 5, the L-shaped lock 6, the upper panel 7, the lower panel 8, the left panel 9, the right panel 10, the front interactive panel 11, the connection plug 12, the anti-misplug safety pin 13, the fastener 14, the air vent 15, the front panel identification 16, the internal circuit connection module 17. DETAILED DESCRIPTION

[0033] The technical scheme of the application will be described in detail below in combination with the drawings and embodiments.

[0034] As shown in the drawings and embodiments: Figures 1-7 An aircraft overheat detection loop detection switching device, the aircraft overheat detection loop detection switching device is a cuboid device, a front interactive panel 11 is arranged at the front end of the device, three selection switches are arranged on the front interactive panel 11, which are a first BMC loop selection switch 1, a second BMC loop selection switch 2 and a BMC selection switch 3, a detection end output port 4 for connecting with an external detection device is arranged on the front interactive panel 11, a connection plug 12 for connecting with a port of an aircraft device is arranged at the rear end of the device, the BMC selection switch 3 is used for selecting a detection loop, and the first BMC loop selection switch 1 and the second BMC loop selection switch 2 are used for selecting items of the selected loop.

[0035] The one end of the BMC selection switch 3 is a selection knob, and the other end of the BMC selection switch 3 is connected with the first BMC loop selection switch 1 and the second BMC loop selection switch 2 respectively.

[0036] The detection end output port 4 is provided with three connection terminals of an output terminal 1, an output terminal 2 and an output ground, the output terminal 1 and the output terminal 2 are electrically connected with the selection knob end of the BMC selection switch 3 in the aircraft overheat detection loop detection switching device, and the output ground is connected with the shell of the aircraft overheat detection loop detection switching device, which can be connected with the ground wire of the aircraft device port.

[0037] The first BMC loop selection switch 1 is a rotary knob selection switch, and is provided with four groups of selection loops in two groups, and the four groups of loops are in turn the APU detection loop, the right wing A detection loop, the left wing A detection loop and the left engine pylon detection loop respectively.

[0038] The second BMC loop selection switch 2 is a rotary knob selection switch, and is provided with four groups of selection loops in two groups, and the four groups of loops are in turn the NC open loop, the left wing B detection loop, the right wing B detection loop and the right engine pylon detection loop respectively, and the NC open loop terminal is suspended.

[0039] The last three groups of loops of the first BMC loop selection switch 1 and the second BMC loop selection switch 2 are electrically connected with the connection plug 12 in turn through one-to-one short connection, and the APU detection loop of the first BMC loop selection switch 1 is electrically connected with the connection plug 12.

[0040] The aircraft device port is a No. 1 BMC bleed air management machine or a No. 2 BMC bleed air management machine.

[0041] The No. 1 BMC bleed air management machine is provided with four groups of detection loop ports in two groups, and the four groups of detection loop ports are the APU detection loop, the right wing A detection loop, the left wing A detection loop and the left engine pylon detection loop respectively.

[0042] The No. 2 BMC bleed air management machine is provided with three groups of detection loop ports in two groups, and the three groups of detection loop ports are the left wing B detection loop, the right wing B detection loop and the right engine pylon detection loop respectively, and the positions of the three groups of ports correspond to the positions of the right wing A detection loop, the left wing A detection loop and the left engine pylon detection loop of the No. 1 BMC bleed air management machine respectively.

[0043] The first BMC loop selection switch 1 or the second BMC loop selection switch 2 can be selected according to whether the No. 1 BMC bleed air management machine or the No. 2 BMC bleed air management machine is connected, so that the specific loop project can be detected, so that the aircraft overheat detection loop detection switching device can detect the A and B loops of the left and right wings, the APU detection loop and the left and right engine suspension, which is convenient, fast and practical.

[0044] The lower end of the front interaction panel 11 is provided with an L-shaped lock 6.

[0045] The detection method of the aircraft overheat detection loop detection switching device is as follows:

[0046] Step one, remove the No. 1 or No. 2 BMC bleed air management machine from the aircraft equipment rack;

[0047] Step two, connect the removed No. 1 or No. 2 BMC bleed air management machine with the connection plug 12 of the aircraft overheat detection loop detection switching device;

[0048] Step three, use the locking device at the aircraft end to connect with the L-shaped lock 6 of the aircraft overheat detection loop detection switching device, and tighten to make them firmly installed;

[0049] Step four, select the corresponding gear on the BMC selection switch 3 according to whether the No. 1 BMC bleed air management machine or the No. 2 BMC bleed air management machine is connected, so that the first BMC loop selection switch 1 corresponds to the No. 1 BMC bleed air management machine, or the second BMC loop selection switch 2 corresponds to the No. 2 BMC bleed air management machine;

[0050] Step five, connect the ground end of the No. 1 or No. 2 BMC bleed air management machine with the ground end of the aircraft overheat detection loop detection switching device, so as to realize the connection between the output ground end of the detection end output port 4 and the shell of the aircraft overheat detection loop detection switching device;

[0051] Step six, use the resistance and impedance external detection device to connect to the three output ports of the detection end output port 4, and detect the corresponding detection loop by selecting the position of the knob on the first BMC loop selection switch 1 or the second BMC loop selection switch 2.

[0052] The support cores are counterclockwise slotted support cores and clockwise slotted support cores, and the corresponding fuses are counterclockwise fuses and clockwise fuses.

[0053] Embodiment:

[0054] An A320 series aircraft detection overheat detection loop switching device for detecting the wing, engine and auxiliary power unit (APU), comprising:

[0055] 1. A cuboid device housing, the upper panel and lower panel of the housing are provided with ventilation holes. The size of the housing is consistent with the size of the installation base of the aircraft bleed air management computer, which can be smoothly installed on the aircraft equipment end and tightly connected with the aircraft. The lower panel of the completely installed device housing can tightly adhere to the metal structure on the aircraft equipment rack to realize the same grounding of the device housing and the aircraft structure.

[0056] 2. The front panel of the housing contains from top to bottom:

[0057] a. Two bleed air management computer (BMC) loop selection switches, which can freely select the overheat detection loop path connected by No. 1 and No. 2 bleed air management computers, including left wing A detection loop and B detection loop, right wing A detection loop and B detection loop, left and right engine pylon detection loop and auxiliary power unit (APU) detection loop.

[0058] b. A bleed air management computer selection switch, which can detect two bleed air management computers connected by the system, and the switch is placed in the position of the corresponding system to be executed.

[0059] c. Three detection output ports, two of which are center line core output ports, and the third is a ground output port.

[0060] d. A U-shaped handle for easy disassembly and installation of the switching device, as well as short-distance manual transportation.

[0061] e. Device locking L-shaped lock, after the switching device is installed on the aircraft equipment rack, the L-shaped lock is used in cooperation with the locking device on the aircraft equipment rack to fix the switching device on the aircraft equipment rack, realizing the tight connection of the plug and the socket, and realizing the connection of the switching device and the aircraft structure, so that the aircraft structure and the device are at the same potential.

[0062] 3. The rear panel of the housing contains a computer socket assembly matched with the aircraft end plug, which is provided with a plug inside the socket, which can realize complementary assembly with the plug of the aircraft end, so as to ensure correct connection of the line. The use of socket and plug matched with the plug of the aircraft end can avoid damage to the aircraft end device and plug. The installation of error-proof pins allows the device to be installed only at the bleed air management computer port of the aircraft end and cannot be inserted at other computer ports of the aircraft, avoiding installation position errors.

[0063] 4. The device is internally provided with electronic components, including wires, line terminal switching modules, sockets and connecting plugs.

[0064] The working principle of the device is as follows:

[0065] 1. Remove the No. 1 and / or No. 2 Bleed Air Management Computer (BMC) from the aircraft equipment rack.

[0066] 2. Install the adapter device in place of the BMC.

[0067] 3. Connect the aircraft end lock to the L-shaped lock catch on the device and tighten to secure the device in place.

[0068] 4. If the adapter device is installed in place of the No. 1 BMC, set the BMC selector switch to the BMC-1 position to connect output 1 and output 2 to the probe loop of the No. 1 BMC. Set the loop selector switch-1 to the APU position to connect the lines through the device to the APU probe loops 7B and 8B, through the A and B ports of the adapter module to the 1 and 5 ports of the loop selector switch-1, through the 9 and 10 ports of the loop selector switch-1 to the 1 and 3 ports of the BMC selector switch, and through the 5 and 6 ports of the BMC selector switch to the output ports 1 and 2. The operation of the loop selector switch in other positions or the adapter device installed in place of the No. 2 BMC is similar to the above.

[0069] 5. Connect the pin in the 2A hole of the AA jack on the adapter device to the pin in the 2A hole of the aircraft end plug, and through the wire to the structure ground on the aircraft. Also, to achieve a good ground, the output ground is connected to the device housing, and through the device housing to the equipment rack on the aircraft.

[0070] 6. Use the dedicated resistance and impedance measuring device to connect to the three output ports on the adapter device, and through the selection of the corresponding switch to achieve the detection purpose.

[0071] The specific use steps of the device are as follows:

[0072] 1. Remove the No. 1 and / or No. 2 Bleed Air Management Computer (BMC) from the aircraft equipment rack.

[0073] 2. Install the adapter device in place of the BMC.

[0074] 3. Use the aircraft end lock to connect to the L-shaped lock catch on the device and tighten to secure the device in place.

[0075] 4. If the adapter is installed in the position of the No. 1 bleed air management computer BMC for testing, the BMC selector switch is set to the BMC-1 position, the output 1 and output 2 are connected to the detection loop of the BMC-1 computer. The loop selector switch-1 is set to the APU gear, the line is connected to the APU detection loop 7B and 8B through the adapter, and then connected to the 1 end and 5 end of the loop selector switch-1 through the A end and B end of the adapter, and then connected to the 1 end and 3 end of the BMC selector switch through the 9 end and 10 end of the loop selector switch-1, and finally connected to the output port 1 and 2 through the 5 end and 6 end of the BMC selector switch. The working principle of the loop selector switch in other positions or the adapter installed in the position of the No. 2 bleed air management computer BMC is similar to the above.

[0076] 5. The A2 hole plug of the AA socket of the adapter is connected to the 2A hole plug of the aircraft end plug, and connected to the structure ground of the aircraft through the wire. At the same time, in order to realize good grounding, the output ground is connected to the shell of the device, and the shell is connected to the equipment rack of the aircraft to realize grounding.

[0077] 6. A dedicated resistance and impedance external detection device is connected to the three output ports of the adapter, and the corresponding loop is detected by selecting the corresponding switch.

Claims

1. An aircraft overheat detection loop detection switching device, characterized by: The aircraft overheat detection loop detection switching device is a cuboid device, a front interaction panel (11) is arranged at the front end of the device, three selection switches are arranged on the front interaction panel (11), which are a first BMC loop selection switch (1), a second BMC loop selection switch (2) and a BMC selection switch (3), a detection end output port (4) for connecting with an external detection device is arranged on the front interaction panel (11), a connecting plug (12) for connecting with an aircraft device port is arranged at the rear end of the device, the BMC selection switch (3) is used for selecting a detection loop, the first BMC loop selection switch (1) and the second BMC loop selection switch (2) are used for selecting items of the selected loop; One end of the BMC selection switch (3) is a selection knob, and the other end of the BMC selection switch (3) is connected with the first BMC loop selection switch (1) and the second BMC loop selection switch (2) respectively. The detection end output port (4) is provided with three wiring ends of an output end 1, an output end 2 and an output ground, the output end 1 and the output end 2 are electrically connected with the selection knob end of the BMC selection switch (3) in the aircraft overheat detection loop detection switching device, the output ground is connected with the shell of the aircraft overheat detection loop detection switching device, and the shell of the aircraft overheat detection loop detection switching device can be connected with a ground wire of the aircraft device port. The first BMC loop selection switch (1) is a rotary knob selection switch and is provided with four groups of selection loops in two groups, and the four groups of loops are an APU detection loop, a right wing A detection loop, a left wing A detection loop and a left engine suspension detection loop in sequence. The second BMC loop selection switch (2) is a rotary knob selection switch and is provided with four groups of selection loops in two groups, and the four groups of loops are an NC open loop, a left wing B detection loop, a right wing B detection loop and a right engine suspension detection loop in sequence, and the NC open loop terminal is suspended. The last three groups of loops of the first BMC loop selection switch (1) and the second BMC loop selection switch (2) are electrically connected with the connecting plug (12) after being correspondingly short-circuited in sequence, and the APU detection loop of the first BMC loop selection switch (1) is electrically connected with the connecting plug (12).

2. An aircraft overheat detection loop detection switching device according to claim 1, wherein, The aircraft device port is a No. 1 BMC bleed air management machine or a No. 2 BMC bleed air management machine.

3. An aircraft overheat detection loop detection switchgear according to claim 2, wherein, The No. 1 BMC bleed air management machine is provided with four groups of detection loop ports in two groups, and the four groups of detection loop ports are an APU detection loop, a right wing A detection loop, a left wing A detection loop and a left engine suspension detection loop.

4. An aircraft overheat detection loop detection switchgear according to claim 3, wherein, The No. 2 BMC bleed air management machine is provided with three groups of detection loop ports in two groups, and the three groups of detection loop ports are a left wing B detection loop, a right wing B detection loop and a right engine suspension detection loop, and the positions of the three groups of ports correspond to the positions of the right wing A detection loop, the left wing A detection loop and the left engine suspension detection loop of the No. 1 BMC bleed air management machine respectively.

5. An aircraft overheat detection loop detection switchgear according to claim 4, wherein, The lower end of the front interaction panel (11) is provided with an L-shaped lock (6).

6. A method of detecting a switching device in an aircraft overheat detection loop using the apparatus of claim 5, wherein, The specific steps of detection are: Step one, remove No. 1 or No. 2 BMC bleed air management machine from the aircraft equipment rack; Step two, connect the removed No. 1 or No. 2 BMC bleed air management machine with the connection plug (12) of the aircraft overheat detection loop detection adapter device; Step three, use the locking device at the aircraft end to connect with the L-shaped lock (6) of the aircraft overheat detection loop detection adapter device, and tighten to make the two firmly installed; Step four, select the corresponding gear on the BMC selection switch (3) according to whether the current connection is No. 1 BMC bleed air management machine or No. 2 BMC bleed air management machine, so that the first BMC loop selection switch (1) corresponds to No. 1 BMC bleed air management machine, or the second BMC loop selection switch (2) corresponds to No. 2 BMC bleed air management machine; Step five, connect the ground end of No. 1 or No. 2 BMC bleed air management machine with the ground end of the aircraft overheat detection loop detection adapter device, to realize the connection with the output ground end of the detection end output port (4) and the shell of the aircraft overheat detection loop detection adapter device; Step six, use resistance and impedance external detection equipment to connect to the three output ports of the detection end output port (4), and detect the corresponding detection loop by selecting the position of the knob on the first BMC loop selection switch (1) or the second BMC loop selection switch (2).

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