CN220391527U - Flight lock verifying attachment and equipment - Google Patents
Flight lock verifying attachment and equipment Download PDFInfo
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- CN220391527U CN220391527U CN202321804468.7U CN202321804468U CN220391527U CN 220391527 U CN220391527 U CN 220391527U CN 202321804468 U CN202321804468 U CN 202321804468U CN 220391527 U CN220391527 U CN 220391527U
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Abstract
The utility model discloses a flight lock inspection device, comprising: the system comprises a power supply module, a working condition mode selection switch, a ground working condition checking module and an on-board working condition checking module; the power module is connected with the working condition mode selection switch; the working condition mode selection switch is respectively connected with the ground working condition checking module and the on-board working condition checking module; when the working condition mode selection switch is communicated with the ground working condition checking module to form a closed loop, entering a flight lock checking ground mode; and when the working condition mode selection switch is communicated with the on-board working condition checking module to form a closed loop, entering an on-board mode of the flight lock checking machine. The technical scheme can be applied to two working conditions of a ground mode and an onboard mode, solves the problems that the current flight lock inspection mode is complex and is difficult to position after faults occur, confirms the state of the flight lock under the condition that the aircraft is not developed so as to position the faults, simulates the actuation state of the flight lock on the aircraft, and meets the simulation test of the aircraft under the condition that the aircraft is not electrified on the ground.
Description
Technical Field
The utility model relates to the field of civil aircraft assembly manufacturing and testing, in particular to a flight lock inspection device and equipment.
Background
In modern civil aircraft, the door system is an important part of the aircraft system, the doors being distributed throughout the fuselage, with the flight locks being mounted in the gates, service doors and emergency doors.
If the flight lock cannot work normally in the flight process of the aircraft, so that the cabin door is opened, the aircraft belongs to disaster-level equipment failure, and the flight lock is particularly important for aircraft safety. In order to avoid irreversible damage caused by opening a cabin door due to misoperation or intentional operation in the flight process of the aircraft, the flight lock is ensured to function normally on the aircraft, and the flight lock needs to be subjected to function inspection in the manufacturing and assembling processes.
Disclosure of Invention
The utility model provides a flight lock inspection device and equipment, which can be used for inspecting the flight lock function and ensuring the safety of airplane running.
According to an aspect of the present utility model, there is provided a flight lock inspection device including: the system comprises a power supply module, a working condition mode selection switch, a ground working condition checking module and an on-board working condition checking module;
the power module is connected with the working condition mode selection switch;
the working condition mode selection switch is respectively connected with the ground working condition checking module and the on-board working condition checking module;
when the working condition mode selection switch is communicated with the ground working condition checking module to form a closed loop, entering a flight lock checking ground mode;
and when the working condition mode selection switch is communicated with the on-board working condition checking module to form a closed loop, entering an on-board mode of the flight lock checking machine.
According to another aspect of the present utility model, there is provided a flight lock inspection apparatus comprising: the device comprises a device box body, at least two device handles, a flying lock placing area and the flying lock checking device provided by any embodiment of the utility model; the flight lock inspection device is a control panel on the equipment box body.
According to the flight lock checking device and the flight lock checking equipment, the working condition mode selection switch, the ground working condition checking module and the on-board working condition checking module are arranged, when the working condition mode selection switch is communicated with the ground working condition checking module to form a closed loop, the flight lock checking ground mode is entered, and the flight lock checking of the ground mode is realized; and when the working condition mode selection switch is communicated with the on-board working condition checking module to form a closed loop, entering an on-board mode of the flight lock checking machine to realize the flight lock checking of the on-board mode. The technical scheme can be applied to two working conditions of a ground mode and an onboard mode, solves the problems that the current flight lock inspection mode is complex and is difficult to position after faults occur, confirms the state of the flight lock under the condition that the aircraft is not developed so as to position the faults, simulates the actuation state of the flight lock on the aircraft, and meets the simulation test of the aircraft under the condition that the aircraft is not electrified on the ground.
It should be understood that the description in this section is not intended to identify key or critical features of the embodiments of the utility model or to delineate the scope of the utility model. Other features of the present utility model will become apparent from the description that follows.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present utility model, the drawings required for the description of the embodiments will be briefly described below, and it is apparent that the drawings in the following description are only some embodiments of the present utility model, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a block diagram of a first flight lock testing device according to an embodiment of the utility model;
FIG. 2 is a block diagram of a second type of flight lock verification device according to a first embodiment of the utility model;
FIG. 3 is a block diagram of a third exemplary flight lock verification device according to an embodiment of the present utility model;
FIG. 4 is a block diagram of a fourth flight lock verification device according to an embodiment of the utility model;
FIG. 5 is a block diagram of a fifth exemplary flying lock testing device according to the present utility model;
FIG. 6 is a block diagram of a sixth exemplary flying lock testing device according to the present utility model;
FIG. 7 is a schematic circuit diagram of a flight lock testing device according to a first embodiment of the present utility model;
FIG. 8 is a block diagram of a flight lock verification device according to a second embodiment of the utility model;
fig. 9 is a schematic structural diagram of a flight lock inspection device according to a second embodiment of the present utility model.
Detailed Description
In order that those skilled in the art will better understand the present utility model, a technical solution in the embodiments of the present utility model will be clearly and completely described below with reference to the accompanying drawings in which it is apparent that the described embodiments are only some embodiments of the present utility model, not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the present utility model without making any inventive effort, shall fall within the scope of the present utility model.
It should be noted that the terms "first," "second," and "object" in the description of the present utility model and the claims and the above figures are used for distinguishing between similar objects and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used may be interchanged where appropriate such that the embodiments of the utility model described herein may be implemented in sequences other than those illustrated or otherwise described herein. Furthermore, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover a non-exclusive inclusion, such that a process, apparatus, system, article, or device that comprises a list of steps or elements is not necessarily limited to those steps or elements expressly listed or inherent to such process, apparatus, article, or device.
Example 1
Fig. 1 is a block diagram of a device for checking a flight lock according to an embodiment of the present utility model, where the embodiment is applicable to a situation where the actuation state of the flight lock is checked under different working conditions.
The flight lock is a cabin door lock of an airplane, and has two working modes, namely a flight lock power-off mode, when the power is off, the flight lock is in an extending position, and the boarding door and the whole cabin door are unlocked; upon power failure, the flight lock returns to the extended/unlocked position under the influence of a mechanical spring. The other is a flight lock power-on mode, when the flight lock receives a signal sent by the central control unit, the transmission rod is retracted and kept at the retracted position, and a solenoid coil in the flight lock is powered on to generate larger electromagnetic force to overcome spring force, inertia force and the like, so that the movable armature moves to lock the door. And outputting current for less than 0.3s. After switching on, the flight lock control circuit switches to a hold state (low power state), the current drops and is in a steady state. Switching from the high current state to the low current steady state is accomplished by the flight lock internal control circuitry without the need for additional external switches.
As shown in fig. 1, the apparatus includes: the system comprises a power supply module 10, a working condition mode selection switch 20, a ground working condition checking module 30 and an on-board working condition checking module 40; the power module 10 is connected with the working condition mode selection switch 20; the working condition mode selection switch 20 is respectively connected with the ground working condition checking module 30 and the on-board working condition checking module 40.
In this embodiment, the power module 10 may be understood as a dc voltage-stabilized power supply for converting ac power into dc power and outputting the converted dc power, for example, converting 220v ac power into 28v dc power. The operating mode selection switch 20 may be understood as a switch for selecting an operating mode, wherein the operating mode includes a ground mode, which may be understood as a mode simulating an operating state of the flight lock while the aircraft is on the ground, and an onboard mode, which may be understood as a mode simulating an operating state of the flight lock while the aircraft is traveling. It will be appreciated that there is a significant difference between the ground mode and the on-board mode in simulating air conditions such as air pressure, flow rate, etc.
The ground condition checking module 30 may be understood as a working condition checking module when the flight lock is actuated on the ground, and when the ground mode is selected by the condition mode selection switch 20, the ground condition checking module 30 works to check the flight lock. The on-board condition check module 40 may be understood as a working condition check module that simulates the operation of the flight lock on-board, and when the condition mode selection switch 20 selects the on-board mode, the on-board condition check module 40 works to check the flight lock.
Specifically, the power module 10 converts the accessed ac power into dc power for output, when the ground mode is selected by the working mode selection switch 20, the switch is closed, and at this time, the power module 10, the working mode selection switch 20 and the ground working mode inspection module 30 are communicated into a closed loop, and enter the ground mode for inspecting the flight lock, and the flight lock actuation state inspection of the ground working condition is performed on one flight lock connected with the flight lock inspection device.
Specifically, the power module 10 converts the accessed ac power into dc power for output, when the on-board mode is selected by the operating mode selecting switch 20, the switch is closed, and at this time, the power module 10, the operating mode selecting switch 20 and the on-board operating mode checking module 40 are connected into a closed loop, and enter the on-board mode of the flight lock checking machine, and perform on-board operating mode simulated flight lock actuation state checking on one flight lock connected with the flight lock checking device.
It can be understood that the working condition mode selection switch 20 can simultaneously select a ground mode and an on-board mode, specifically, the power module 10 converts the accessed alternating current into direct current for output, the working condition mode selection switch 20 simultaneously selects the ground mode and the on-board mode, at this time, the power module 10, the working condition mode selection switch 20, the ground working condition inspection module 30 and the on-board working condition inspection module 40 are communicated into a closed loop, and simultaneously enter the ground mode and the on-board mode for flight lock inspection, and the two flight locks connected with the flight lock inspection device are respectively subjected to flight lock actuation state inspection of ground working condition and on-board working condition simulation.
As a first alternative embodiment of the present embodiment, fig. 2 is a block diagram of a second type of flight lock testing device according to a first embodiment of the present utility model. As shown in fig. 2, the operating mode selection switch 20 includes: a ground mode switch 21 and an on-board mode switch 22; the ground mode switch 21 is connected with the ground working condition checking module 30; the on-board mode switch 22 is connected to an on-board condition check module 40.
In this embodiment, the ground mode switch 21 may be understood as a switch for selecting a ground condition for checking the flight lock. The on-board mode switch 22 may be understood as a switch for selecting the mode of operation for the analog on-board check of the flight lock.
Specifically, the power module 10 converts the accessed ac power into dc power for output, and when the ground mode switch 21 in the operating mode selection switch 20 is closed, the power module 10, the ground mode switch 21 in the operating mode selection switch 20 and the ground operating mode checking module 30 are communicated into a closed loop, enter the ground mode for checking the flight lock, and check the flight lock operating state of the ground operating mode for one flight lock connected with the flight lock checking device.
Specifically, the power module 10 converts the accessed ac power into dc power for output, and when the on-board mode switch 22 in the operating mode selection switch 20 is closed, the power module 10, the on-board mode switch 22 in the operating mode selection switch 20 and the on-board operating mode inspection module 40 are communicated into a closed loop, enter an on-board mode of the flight lock inspection machine, and perform an on-board operating mode-simulating flight lock operation state inspection on one flight lock connected with the flight lock inspection device.
Specifically, the power module 10 converts the accessed ac power into dc power for output, and when the ground mode switch 21 and the on-board mode switch 22 in the operating mode selection switch 20 are both closed, the ground mode switch 21, the on-board mode switch 22, the ground operating mode inspection module 30 and the on-board operating mode inspection module 40 in the operating mode selection switch 20 are communicated into a closed loop, and simultaneously enter a ground mode and an on-board mode for flight lock inspection, and respectively perform flight lock operation state inspection of ground operating mode and on-board operating mode simulation for two flight locks connected with the flight lock inspection device.
As a second alternative embodiment of the present embodiment, fig. 3 is a block diagram of a third type of flight lock testing device according to a first embodiment of the present utility model. As shown in fig. 3, the ground condition checking module 30 includes: a ground switch group 31 and a terminal combination 32; the ground switch group 31 is connected with a terminal combination 32, and the terminal combination 32 is connected with a flight lock to be inspected.
In this embodiment, the ground switch set 31 may be understood as a switch set in ground mode, including at least two switches for testing the extended and retracted state of the flight lock. The terminal combination 32 is understood to be a combination of terminals for connecting a flight lock to a flight lock testing device, comprising at least four terminals.
Specifically, in the connection line of the flight lock inspection device, the ground switch group 31 and the terminal combination 32; the ground switch group 31 is connected with a terminal combination 32, and the terminal combination 32 is connected with a flight lock to be inspected. When all the switches in the ground switch group 31 are in a closed state and the circuits are communicated, the flight lock check of the ground mode is realized.
Further, the ground switch group 31 includes a first switch and a second switch; the terminal combination 32 includes a first terminal, a second terminal, a third terminal, and a fourth terminal;
the first binding post is connected with the ground mode switch 21 through a first switch; the second terminal is connected with the ground mode switch 22 through a second switch; the third terminal and the fourth terminal are connected to the power module 10.
In this embodiment, the first switch and the second switch may be understood as control switches corresponding to ground modes, for testing the extended/retracted state of the flight lock. The first, second, third and fourth binding post may be understood as binding posts for connecting the flight lock to the flight lock testing device. It can be understood that five connecting lines are respectively a first finished product line, a second finished product line, a third finished product line, a fourth finished product line and a fifth finished product line, and the fifth finished product line is a short-circuit finished product line.
The first finished wire is connected with the first binding post to simulate an enabling control signal of an on-board cabin door signal system; the second finished wire is connected with the second binding post so as to simulate the direct current signal ground of the airplane; the third finished product line is connected with the third binding post so as to simulate a power supply signal of the aircraft; the fourth finished wire is connected with a fourth binding post to match the ground of the power supply signal of the simulated aircraft, and the fifth finished wire is suspended and not connected to simulate the on-board wheel load state signal. The flying lock finished wire and the binding post can be correspondingly connected through preset colors, for example, the first finished wire and the first binding post are red, the first finished wire is a red finished wire, and the first binding post is a red binding post; the second finished product line and the second binding post are both in green; the third finished product line and the third binding post are both in white; the fourth product line and the fourth binding post are all in blue, and the product line and the binding post can show corresponding relation in corresponding color, and the set color is not limited in this embodiment.
Specifically, the first binding post is connected with the ground mode switch 21 through a first switch, and the first binding post is also connected with a first finished wire of the flight lock; the second binding post is connected with the ground mode switch 22 through a second switch, and the second binding post is also connected with a second finished wire of the flight lock; the third binding post and the fourth binding post are both connected with the power module 10, the third binding post is connected with a third finished product line of the flight lock, and the fourth binding post is connected with a fourth finished product line of the flight lock. When the flight lock is not opened for inspection, the ground mode switch 21 and the on-board mode switch 22 in the working condition mode selection switch 20 are both in an open state, the first switch and the second switch in the ground switch group 31 are both in an open state, and after the power supply module 10 is powered on, the ground mode switch 21 is selected to be closed, and the flight lock is inspected in a ground mode. An operator controls the ground switch group 31, sets the first switch and the second switch to be closed, places the switches in an ON position, and verifies that the flight lock is placed in a retraction position; the ground switch group 31 is controlled, the first switch is set to be closed, the first switch is set to be in an ON position, the second switch is set to be open, the second switch is set to be in an OFF position, and the flight lock is verified to be in an extended position; the ground switch set 31 is controlled to set the first switch to open, set the second switch to close, set the ON position, and verify that the flight lock is in the extended position.
As a third alternative embodiment of the present embodiment, fig. 4 is a block diagram of a fourth type of flight lock testing device according to a first embodiment of the present utility model. As shown in fig. 4, the on-board condition checking module 40 includes: an onboard switch set 41 and an aircraft connector 42.
Specifically, in the connection line of the flight lock inspection device, the on-board switch group 41 is connected with the aviation connector 42, and the aviation connector 42 is connected with the flight lock to be inspected. When all the switches in the on-board switch group 41 are in a closed state and the circuits are connected, the on-board mode flight lock check is realized.
Further, the on-board switch group 41 includes a third switch and a fourth switch; the air connector 42 includes a first interface, a second interface, a third interface 433, and a fourth interface 434;
the first interface is connected with the on-board mode switch 22 through a third switch; the second interface is connected with the on-board mode switch 22 through a fourth switch; the third interface and the fourth interface are both connected to the power module 10.
In this embodiment, the third switch and the fourth switch may be understood as control switches corresponding to the on-board mode, and are used for testing the extended and retracted states of the flight lock. The first interface, the second interface, the third interface 433 and the fourth interface 434 can be understood as an aviation connector for connecting a flight lock and a flight lock checking device, and matching with field test requirements, and the purpose of prolonging test distance is achieved by being connected with a tooling patch cord, so that after the on-board flight lock is installed, the on-board flight lock is ensured to have the flight lock checking and testing capability under specific working conditions.
Specifically, the first interface is connected to the on-board mode switch 22 through a third switch; the second interface is connected with the on-board mode switch 22 through a fourth switch; the third interface and the fourth interface are both connected to the power module 10. The aircraft connector 42 is connected to the flight lock to be inspected.
When the flight lock is not opened for inspection, the ground mode switch 21 and the on-board mode switch 22 in the working condition mode selection switch 20 are both in an open state, and the third switch and the fourth switch in the on-board switch group 41 are both in an open state, and after the power module 10 is powered on, the on-board mode switch 22 is closed to enter the on-board mode of the flight lock inspection. The operator controls the ON-board switch group 41, sets the third switch and the fourth switch to be closed, places the switch in the ON position, and verifies that the flight lock is placed in the retraction position; the ON-board switch group 41 is controlled, the third switch is set to be closed, the ON position is set, the fourth switch is set to be opened, the OFF position is set, and the flight lock is verified to be set in the extension position; the ON-board switch set 41 is controlled to set the third switch to open, set the fourth switch to close, set the ON position, and verify that the flight lock is set in the extended position.
As a fourth alternative embodiment of the present embodiment, fig. 5 is a block diagram of a fifth flying lock testing device according to a first embodiment of the present utility model. As shown in fig. 5, the flight lock inspection device further includes: a digital display voltage module 50; the digital display voltage module 50 is connected with the power module 10.
In this embodiment, the digital display voltage module 50 may be understood as a digital display voltmeter, which is used to display the real-time output voltage of the circuit on the screen, and determine the connection state of the circuit, so as to further determine whether the flight lock inspection device can work normally.
Specifically, the power module 10 converts the accessed ac power into dc power for output, and the digital voltage module 50 is connected to the power module 10. When the power is connected, the digital display voltage module works normally, and in the running process of the flight lock inspection device, the real-time output voltage value is displayed on the screen of the digital display voltage module 50, and the circuit communication state is determined, so that whether the flight lock inspection device can work normally is further determined.
As a fifth alternative embodiment of the present embodiment, fig. 6 is a block diagram of a sixth type of flight lock testing device according to a first embodiment of the present utility model. As shown in fig. 6, the flight lock inspection device further includes: the power supply interface 60, the power supply interface 60 is connected with the power supply module 10, and when the power supply interface 60 is powered on, the power supply module 10 works.
In this embodiment, the power interface 60 may be understood as a power outlet for obtaining 220v ac power.
Specifically, when the power interface 60 is plugged in, high-power alternating current is obtained and transmitted to the power module 10, and the power module 10 converts the alternating current into direct current.
Fig. 7 is a schematic circuit diagram of a flight lock checking device according to a first embodiment of the present utility model. As shown in fig. 7, the connection line of the flight lock inspection device includes: the system comprises a power module 10, a working condition mode selection switch 20, a ground working condition checking module 30, an on-board working condition checking module 40, a ground switch group 31, a binding post combination 32, an on-board switch group 41, an aviation connector 42 and a digital display voltage module 50. The on-board wheel load state signal, the cabin door signal system enabling control signal (composed of a line enabling control signal and an airplane direct current signal) and the solid state power controller (composed of a direct current power supply and a loop ground) are simulated through the switch combination, so that the purpose of testing the flight lock under different working conditions is achieved, the testing efficiency is improved, and the field testing difficulty is reduced.
An embodiment of the present utility model provides a flight lock inspection device, including: the system comprises a power supply module, a working condition mode selection switch, a ground working condition checking module and an on-board working condition checking module; the power module is connected with the working condition mode selection switch; the working condition mode selection switch is respectively connected with the ground working condition checking module and the on-board working condition checking module; when the working condition mode selection switch is communicated with the ground working condition checking module to form a closed loop, entering a flight lock checking ground mode; and when the working condition mode selection switch is communicated with the on-board working condition checking module to form a closed loop, entering an on-board mode of the flight lock checking machine. The device can be applied to two working conditions, one scene is the test of the flight lock on the ground, the state of the flight lock can be confirmed in advance, and the problem that the fault parts are used in the function test to influence the test progress is avoided. Another scenario is the testing of the flight lock when installed on an aircraft, by simulating different power supplies, signal combinations, the status of the flight lock can be confirmed without development of the aircraft, so as to locate faults. The method solves the problems that the existing flight lock inspection mode is complex and difficult to locate after faults occur, simulates the on-board actuating state of the flight lock, and meets the simulation test of the aircraft under the condition of no power on the ground.
Example two
Fig. 8 is a block diagram of a flight lock checking device according to a second embodiment of the present utility model, where the present embodiment is applicable to a situation where the actuation state of the flight lock is checked under different working conditions.
As shown in fig. 8, the apparatus includes: an equipment cabinet 101, at least two equipment handles 102, a flight lock placement area 103, and at least one flight lock verification device 104 as provided in the above embodiments; the flight lock verification device 104 is a control panel on the equipment cabinet 101.
In the present embodiment, the apparatus case 101 can be understood as a case of a metal structure. The device handle 102 is a structure mounted on the device case 101 for securing portability of the flight lock inspection device. The flight lock placement area 103 can be understood as a placement storage area on the flight lock inspection device for placing the flight lock to be detected. The flight lock verification device 104 is a control panel on the equipment cabinet 101.
As a first alternative embodiment of the present embodiment, the flying lock placement area 103 includes: a ground pattern placement area 1031 and an on-board pattern placement area 1032; the floor mode placement area 1031 and the on-board mode placement area 1032 are recessed into the inside of the case on the apparatus case 101.
In the present embodiment, the ground mode placement area 1031 may be understood as an area where the flight lock is placed when checking the flight lock actuation state in the ground mode. The on-board mode placement section 1032 may be understood as the area where the flight lock is placed when checking the flight lock actuation state in the on-board mode. The floor mode placement area 1031 and the on-board mode placement area 1032 are recessed into the inside of the case on the apparatus case 101.
Fig. 9 is a schematic structural diagram of a flight lock inspection device according to a second embodiment of the present utility model. As shown in fig. 9, the flight lock inspection device is composed of a device box 101, two device handles 102, a ground mode placement area 1031, an onboard mode placement area 1032, and a flight lock inspection device, wherein the flight lock inspection device is an integrated control panel on the device box 101, and comprises a working condition mode selection switch 20, a ground switch group 31, a binding post combination 32, an onboard switch group 41, an aviation connector 42, a digital display voltage module 50, and a power interface 60.
The second embodiment of the utility model provides a flight lock inspection device, which comprises: the device comprises a device box body, at least two device handles, a flying lock placing area and at least one flying lock checking device provided by the embodiment; the flight lock inspection device is a control panel on the equipment box body. The device is not limited to ground scene test or engine driving scene test, can be used when an accident is eliminated on the aircraft, judges the functional condition of the crosslinking device by eliminating the fault of the flight lock, and more accords with the multi-working-condition test requirement of the civil aircraft.
It should be appreciated that various forms of the flows shown above may be used to reorder, add, or delete steps. For example, the steps described in the present utility model may be performed in parallel, sequentially, or in a different order, so long as the desired results of the technical solution of the present utility model are achieved, and the present utility model is not limited herein.
The above embodiments do not limit the scope of the present utility model. It will be apparent to those skilled in the art that various modifications, combinations, sub-combinations and alternatives are possible, depending on design requirements and other factors. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present utility model should be included in the scope of the present utility model.
Claims (10)
1. A flight lock verification device, the flight lock verification device comprising: the system comprises a power supply module, a working condition mode selection switch, a ground working condition checking module and an on-board working condition checking module;
the power module is connected with the working condition mode selection switch;
the working condition mode selection switch is respectively connected with the ground working condition checking module and the on-board working condition checking module;
when the working condition mode selection switch is communicated with the ground working condition checking module to form a closed loop, entering a flight lock checking ground mode;
and when the working condition mode selection switch is communicated with the on-board working condition checking module to form a closed loop, entering an on-board mode of the flight lock checking machine.
2. The apparatus of claim 1, wherein the operating mode selection switch comprises: a ground mode switch and an on-board mode switch;
the ground mode switch is connected with the ground working condition checking module, and enters a flight lock to check a ground mode when the ground mode switch is closed and forms a communication loop with the ground working condition checking module;
the on-board mode switch is connected with the on-board working condition checking module, and enters a flight lock checking on-board mode when the on-board mode switch is closed and forms a communication loop with the on-board working condition checking module.
3. The apparatus of claim 2, wherein the ground condition verification module comprises: the ground switch group is combined with the binding post;
the ground switch group is connected with the binding post combination, and the binding post combination is connected with a flight lock to be inspected; when the ground switch group is closed and the loop is communicated, the flight lock inspection of the ground mode is realized.
4. A device according to claim 3, wherein the ground switch set comprises a first switch and a second switch; the binding post combination comprises a first binding post, a second binding post, a third binding post and a fourth binding post;
the first binding post is connected with the ground mode switch through the first switch;
the second binding post is connected with the ground mode switch through the second switch;
the third binding post and the fourth binding post are connected with the power supply module.
5. The apparatus of claim 2, wherein the on-board condition verification module comprises: an onboard switch set and an aviation connector;
the on-board switch group is connected with the aviation connector, and the aviation connector is connected with the flight lock to be inspected; and when the on-board switch group is closed and the loop is communicated, the on-board mode flight lock inspection is realized.
6. The apparatus of claim 5, wherein the set of on-board switches comprises a third switch and a fourth switch; the aviation connector comprises a first interface, a second interface, a third interface and a fourth interface;
the first interface is connected with the on-board mode switch through the third switch;
the second interface is connected with the on-board mode switch through the fourth switch;
the third interface and the fourth interface are both connected with the power supply module.
7. The apparatus of claim 1, wherein the flight lock verification device further comprises: a digital display voltage module; the digital display voltage module is connected with the power supply module, and displays the circuit communication condition of the flight lock inspection device when the power supply is connected.
8. The apparatus of claim 1, wherein the flight lock verification device further comprises: the power supply interface is connected with the power supply module, and the power supply module works when the power supply interface is powered on.
9. A flight lock verification device, the flight lock verification device comprising: a device case, at least two device handles, a flight lock placement area, and the flight lock inspection apparatus of any one of claims 1-8; the flight lock inspection device is a control panel on the equipment box body.
10. The apparatus of claim 9, wherein the flight lock placement zone comprises: a ground mode placement area and an on-board mode placement area; the ground mode placing area and the on-board mode placing area are recessed towards the inside of the box body on the equipment box body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321804468.7U CN220391527U (en) | 2023-07-11 | 2023-07-11 | Flight lock verifying attachment and equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321804468.7U CN220391527U (en) | 2023-07-11 | 2023-07-11 | Flight lock verifying attachment and equipment |
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