Aircraft landing gear state comprehensive simulation device

Abstract

The utility model discloses an aircraft landing gear state comprehensive simulation device, which belongs to the field of simulation devices, and comprises a device main body, a first adapter cable and a second adapter cable, the first adapter cable and the second adapter cable are connected with the device main body, a display is embedded in the middle of one side surface of the device main body, a switch and socket assembly is arranged around the display, and the first adapter cable and the second adapter cable are connected with the device main body. The switch and socket assembly specifically comprises a first quick-release cable socket embedded in the edge position of one side above the display, a second quick-release cable socket is embedded in one side of the first quick-release cable socket, and a power switch is embedded in the side, away from the first quick-release cable socket, of the second quick-release cable socket. A power socket is embedded in the side, away from the second quick-release cable socket, of the power switch, and a self-checking key switch is embedded in one side of the displayer. According to the utility model, automatic protection and visual display of the airplane state when the airplane state logic is disordered are realized, and normal airplane performance is ensured.

Description

Technical Field

[0001] This utility model relates to the field of simulation devices, specifically a comprehensive simulation device for the state of an aircraft landing gear. Background Technology

[0002] During aircraft maintenance, when powering on and testing systems (such as flight control systems), it is necessary to check the system's performance under different conditions (such as ground parking, two-wheel taxiing, takeoff-landing, and in-flight).

[0003] The status of a certain type of aircraft is determined through a comprehensive logical judgment based on the connection and disconnection of the onboard nose landing gear load, main landing gear load, and landing gear retraction / extension endpoint switches (when the endpoint switches are on, a +28V signal is transmitted to the onboard computer; when the endpoint switches are off, there is no voltage signal input to the corresponding port of the onboard computer). Because ground maintenance involves raising and lowering the aircraft and retracting and lowering the landing gear, which alters the landing gear load and retraction / extension endpoint switch statuses, the workload is substantial and the safety risks are high. Therefore, during actual inspections, the corresponding endpoint switch connectors on the aircraft are disconnected, and an external ground simulation device is connected to simulate the landing gear status switching.

[0004] In existing technologies, ground simulation devices are mainly single-structure mechanical switches, which connect and disconnect the terminal switch on the simulator by turning the switch on and off. However, this type of simulation device is prone to logical disorder when switching multiple switches (such as simulating the retraction of the landing gear when the aircraft is under ground load), which may cause the aircraft system to malfunction and interrupt the operation. At the same time, it cannot intuitively display the aircraft status (it requires the operator to judge based on the combination of multiple switch states on the simulation device).

[0005] Therefore, those skilled in the art have provided an integrated simulation device for aircraft landing gear status to solve the problems mentioned in the background art. Utility Model Content

[0006] The purpose of this invention is to provide an integrated simulation device for aircraft landing gear status, which can realize automatic protection when the aircraft status logic is disordered and intuitive display of the aircraft status, ensuring normal aircraft performance and smooth inspection work, so as to solve the problems mentioned in the background art.

[0007] To achieve the above objectives, this utility model provides the following technical solution:

[0008] An integrated simulation device for aircraft landing gear status includes:

[0009] The main body of the device, and the first adapter cable and the second adapter cable connected to the main body of the device.

[0010] The device has a display embedded in the middle of one side of its main body, and a switch and socket assembly is arranged around the display.

[0011] As a further embodiment of this utility model: the switch and socket assembly specifically includes: a first quick-release cable socket embedded on one side edge of the upper part of the display, a second quick-release cable socket embedded on one side of the first quick-release cable socket, and a power switch embedded on the side of the second quick-release cable socket away from the first quick-release cable socket, a power socket embedded on the side of the power switch away from the second quick-release cable socket, a self-test button switch embedded on one side of the display, and a first rotary switch, a second rotary switch, and a third rotary switch horizontally arranged below the display.

[0012] As a further embodiment of this utility model: one end of the first adapter cable is connected to a first quick-release cable plug, and the other end of the first adapter cable is connected to a third quick-release cable socket, a fourth quick-release cable socket, a fifth quick-release cable socket, and a sixth quick-release cable socket. The first quick-release cable plug is connected to the first quick-release cable socket, the third quick-release cable socket and the fourth quick-release cable socket are connected to the external aircraft nose landing gear bearing end point switch docking plug, and the fifth quick-release cable socket and the sixth quick-release cable socket are connected to the external aircraft landing gear retraction end point switch docking plug.

[0013] As a further embodiment of this utility model: one end of the second adapter cable is connected to a second quick-release cable plug, and the other end of the second adapter cable is connected to a seventh quick-release cable socket and an eighth quick-release cable socket, wherein the second quick-release cable plug is connected to the second quick-release cable socket, and the seventh quick-release cable socket and the eighth quick-release cable socket are connected to the external aircraft main landing gear bearing end point power docking plug.

[0014] As a further improvement of this utility model, the first rotary switch, the second rotary switch and the third rotary switch are all changeover switches.

[0015] Compared with the prior art, the beneficial effects of this utility model are:

[0016] 1. This application enables automatic protection against aircraft status logic disorder and provides a clear display of aircraft status, ensuring normal aircraft performance and smooth inspection work. Specifically, by switching the landing gear load, main landing gear load, and landing gear retraction / extension switch positions on the device, it simulates the state conditions required for a given aircraft during commissioning, avoiding the enormous workload and safety risks associated with frequent aircraft jacking and landing gear retraction / extension. The overall device is convenient to use, simple to operate, and suitable for on-site operators.

[0017] 2. This application has the function of comprehensive judgment and fault protection of the position logic of landing gear bearing, main landing gear bearing and landing gear retraction switch, so as to avoid the on-board system malfunction caused by switch logic disorder and ensure the normal progress of aircraft commissioning work.

[0018] 3. This application has the functions of displaying landing gear load, main landing gear load, landing gear retraction and extension, and overall aircraft status, which makes it easy for operators to understand and improves the convenience of use and maintenance of the device.

[0019] 4. This application has a self-testing function, which can check the good condition of the device itself and ensure the reliability and safety of the device. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of a comprehensive simulation device for the state of an aircraft landing gear.

[0021] Figure 2 This is a block diagram illustrating the internal working principle of the main body of an aircraft landing gear state integrated simulation device.

[0022] Figure 3 This is a main workflow diagram of an integrated simulation device for aircraft landing gear status.

[0023] Figure 4 This is a self-test flowchart for an integrated simulation device for the condition of aircraft landing gear.

[0024] In the diagram: 1. Main body of the device; 2. First adapter cable; 3. Second adapter cable; 4. First quick-release cable socket; 5. Second quick-release cable socket; 6. Power switch; 7. Power socket; 8. Display; 9. Self-test button switch; 10. First rotary switch; 11. Second rotary switch; 12. Third rotary switch; 13. First quick-release cable plug; 14. Second quick-release cable plug; 15. Third quick-release cable socket; 16. Fourth quick-release cable socket; 17. Fifth quick-release cable socket; 18. Sixth quick-release cable socket; 19. Seventh quick-release cable socket; 20. Eighth quick-release cable socket. Detailed Implementation

[0025] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0026] As mentioned in the background section of this application, research has revealed that existing ground simulation devices are primarily single-structure mechanical switches, where the switching on and off of the switches corresponds to the connection and disconnection of the terminal switch on the simulator. However, this type of simulation device is prone to logical instability when multiple switches are switched (e.g., simulating the retraction of the landing gear while the aircraft is under ground load), which could lead to aircraft system malfunctions and interruptions in the operation. Furthermore, it cannot visually display the aircraft's status (requiring operators to judge based on the combination of multiple switch states on the simulation device), thus presenting certain drawbacks.

[0027] To address the aforementioned deficiencies, this application discloses an integrated simulation device for aircraft landing gear status, which enables automatic protection when the aircraft status logic is disordered and provides a visual display of the aircraft status, ensuring normal aircraft performance and smooth inspection work.

[0028] The following will describe in detail, with reference to the accompanying drawings, how the solution of this application solves the above-mentioned technical problems.

[0029] Please see Figure 1 In this embodiment of the present invention, an aircraft landing gear status integrated simulation device includes: a device body 1, and a first adapter cable 2 and a second adapter cable 3 connected to the device body 1. A display 8 is embedded in the middle of one side of the device body 1, and a switch and socket assembly is arranged around the display 8. This application can realize automatic protection when the aircraft status logic is disordered and intuitive display of the aircraft status, ensuring normal aircraft performance and smooth inspection work.

[0030] In this embodiment, the switch and socket assembly specifically includes: a first quick-release cable socket 4 embedded on one side edge above the display 8; a second quick-release cable socket 5 embedded on one side of the first quick-release cable socket 4; a power switch 6 embedded on the side of the second quick-release cable socket 5 away from the first quick-release cable socket 4; a power socket 7 embedded on the side of the power switch 6 away from the second quick-release cable socket 5; a self-test button switch 9 embedded on one side of the display 8; and a first rotary switch 10, a second rotary switch 11, and a third rotary switch 12 horizontally arranged below the display 8. This application employs a well-designed human-machine interface, providing landing gear loading, retraction, and overall aircraft status display functions.

[0031] In this embodiment, one end of the first adapter cable 2 is connected to a first quick-release cable plug 13, and the other end of the first adapter cable 2 is connected to a third quick-release cable socket 15, a fourth quick-release cable socket 16, a fifth quick-release cable socket 17, and a sixth quick-release cable socket 18. The first quick-release cable plug 13 is connected to the first quick-release cable socket 4; the third quick-release cable socket 15 and the fourth quick-release cable socket 16 are connected to the external aircraft's nose landing gear bearing end point switch connector; and the fifth quick-release cable socket 17 and the sixth quick-release cable socket 18 are connected to the external aircraft's landing gear retraction end point switch connector. It should be noted that the first adapter cable 2 is designed with the adapter cable bundle combined, taking into account the proximity of the aircraft's nose landing gear bearing end point switch and landing gear retraction end point switch, thus reducing the number of connectors and sockets used and facilitating on-site use and storage.

[0032] In this embodiment, one end of the second adapter cable 3 is connected to a second quick-release cable plug 14, and the other end of the second adapter cable 3 is connected to a seventh quick-release cable socket 19 and an eighth quick-release cable socket 20. The second quick-release cable plug 14 is connected to the second quick-release cable socket 5, and the seventh quick-release cable socket 19, the eighth quick-release cable socket 20, and the external aircraft main landing gear bearing end-point switch docking plug are connected. It should be noted that this application adopts a self-defined end-point switch connection analog signal design, isolating the influence of power supply harness failures on the end-point switch mechanism and ensuring the reliability and safety of the device. Furthermore, this application also adopts an end-point switch connection analog signal retrieval design, possessing a device performance self-testing function.

[0033] In this embodiment, the first rotary switch 10, the second rotary switch 11, and the third rotary switch 12 all adopt the LW26-32 type changeover switch. This type of switch has the characteristics of long service life and high quality, and can realize the simultaneous switching of four sets of signals, meeting the requirement of synchronous provisioning of multiple channels of excitation signals of the on-board end switch.

[0034] In this embodiment, the main body 1 of the device is internally equipped with a power conversion module, a processor module, and an input / output interface module, as shown in the schematic diagram below. Figure 2 As shown, during use, the power conversion module converts 220V AC power into low-voltage DC power to power the input / output interface module, main processor module, and display 8, as well as to provide input signals for the status switching switches (i.e., the first rotary switch 10, the second rotary switch 11, and the third rotary switch 12) and the self-test button switch 9. When the corresponding switch is turned on, the +28V DC signal is transmitted to the input / output interface module, and after level conversion / optical isolation, it is transmitted to the main processor module. The main processor module comprehensively determines the aircraft's status based on the status of the switching switches and controls the input / output module to output the +28V DC signal through the socket to the aircraft's endpoint switch connector, thus turning on the corresponding endpoint switch on the simulator.

[0035] The main workflow of the aircraft landing gear status integrated simulation device is as follows: Figure 3 As shown, specifically, during operation, the device continuously collects the positions of the nose landing gear load-bearing, main landing gear load-bearing, and landing gear retraction / extension switches. Based on the positions of these three switches, the device determines the overall aircraft status. Subsequently, the drive unit outputs a +28V DC signal to the corresponding terminal switch connector on the aircraft, and simultaneously displays the switch positions and the overall aircraft status on display 8. Furthermore, when the positions of the three switches do not conform to the actual aircraft operating logic (e.g., nose landing gear is load-bearing and main landing gear is not load-bearing), the signal output to the terminal switch connector remains unchanged, and the display 8 shows "Fault Status, Please Reset Switches," preventing system malfunctions caused by aircraft logic disorder and reminding personnel to operate according to the correct logic. In addition, this integrated simulation device has a self-test function. When the device is working normally, a self-test begins when the self-test button switch 9 is turned on. The self-test process is as follows: Figure 4 As shown, by sampling the signal output from the device to the terminal switch connector plug on the machine and comparing it with the position status of the three changeover switches, "self-test normal" is displayed when they match and "self-test abnormal" is displayed when they do not match.

[0036] This application enables automatic protection against aircraft status logic malfunctions and provides a clear visual display of the aircraft status, ensuring normal aircraft performance and smooth inspection procedures. Specifically, by switching the positions of the landing gear load, main landing gear load, and landing gear retraction / extension switch on the device, it simulates the state conditions required for a given aircraft during commissioning. This avoids the enormous workload and safety risks associated with frequent aircraft jacking and landing gear retraction / extension. The overall device is user-friendly, simple to operate, and suitable for on-site operators. Furthermore, this application features comprehensive judgment and fault protection functions for the position logic of the landing gear load, main landing gear load, and landing gear retraction / extension switch, preventing onboard system malfunctions caused by switch logic malfunctions and ensuring the normal progress of aircraft commissioning. This application also provides a comprehensive display function for landing gear load, main landing gear load, landing gear retraction / extension, and the overall aircraft status, facilitating intuitive operation and improving the ease of use and maintenance. Moreover, this application has a self-test function, which can check the device's own functionality, ensuring its reliability and safety.

[0037] Obviously, those skilled in the art can make various modifications and variations to this utility model without departing from its spirit and scope. Therefore, if these modifications and variations fall within the scope of the claims of this utility model and their equivalents, this utility model also intends to include these modifications and variations.

[0038] The above description is only a preferred embodiment of the present utility model, but the protection scope of the present utility model is not limited thereto. Any equivalent substitutions or changes made by those skilled in the art within the technical scope disclosed in the present utility model, based on the technical solution and the inventive concept of the present utility model, should be included within the protection scope of the present utility model.

Claims

1. An aircraft landing gear state synthesis simulation apparatus, characterized by, The utility model relates to a kind of device main body (1) and the first adapter cable (2) connected with the device main body (1), the second adapter cable (3), Wherein, the middle position of the side surface of the device main body (1) is embedded with display (8), and the periphery of display (8) is equipped with switch and socket assembly; The switch and socket assembly, specifically includes: the first quick-release cable socket (4) embedded in the side edge position above display (8), the side of the first quick-release cable socket (4) is embedded with the second quick-release cable socket (5), and the side of the second quick-release cable socket (5) away from the first quick-release cable socket (4) is embedded with power switch (6), the side of the power switch (6) away from the second quick-release cable socket (5) is embedded with power socket (7), the side of the display (8) is embedded with self-checking button switch (9), and the lower side of the display (8) is embedded with horizontally juxtaposed first rotary switch (10), second rotary switch (11) and third rotary switch (12). The end of the first adapter cable (2) is connected with the first quick-release cable plug (13), and the other end of the first adapter cable (2) is connected with the third quick-release cable socket (15), the fourth quick-release cable socket (16), the fifth quick-release cable socket (17) and the sixth quick-release cable socket (18), wherein, the first quick-release cable plug (13) is connected with the first quick-release cable socket (4), the third quick-release cable socket (15) is connected with the fourth quick-release cable socket (16) and the external aircraft nose landing gear bearing terminal point electric door interface plug, the fifth quick-release cable socket (17) is connected with the sixth quick-release cable socket (18) and the external aircraft landing gear retraction terminal point electric door interface plug.

2. The integrated simulation device for aircraft landing gear state according to claim 1, characterized in that, The end of the second adapter cable (3) is connected with the second quick-release cable plug (14), and the other end of the second adapter cable (3) is connected with the seventh quick-release cable socket (19) and the eighth quick-release cable socket (20), wherein, the second quick-release cable plug (14) is connected with the second quick-release cable socket (5), the seventh quick-release cable socket (19) is connected with the eighth quick-release cable socket (20) and the external aircraft main landing gear bearing terminal point electric door interface plug.

3. An aircraft landing gear state synthesis simulation device according to claim 2, characterised in that, The first rotary switch (10), the second rotary switch (11) and the third rotary switch (12) are all change-over switches.

4. An aircraft landing gear state comprehensive simulation device according to claim 3, characterized in that, ​

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