A330 landing gear sensor simulation device

Abstract

The utility model relates to the field of airplane system ground test simulation technology especially, and more particularly to a kind of A330 landing gear sensor simulation equipment.The equipment includes: equipment shell and buffer isolation pad, the buffer isolation pad adopts buffer cover and the structure of evenly distributed buffer partition, wherein two main frame simulation devices and front landing gear simulation device are respectively provided, four 5.4mH inductors and four 4.7mH inductors are respectively integrated in two main frame simulation devices, and front landing gear simulation device is provided with two 5.4mH inductors and two 4.7mH inductors, and each inductor is connected with airplane system through special navigation plug.The equipment matches the standard inductance parameter of landing gear sensor, simulates the signal that airplane is in ground state, ensures that relevant airborne system function test can still be normally carried out after landing gear removal, significantly shortens airplane maintenance parking period, improves overhaul efficiency and reduces maintenance cost, and has important engineering application value.

Description

Technical Field

[0001] This utility model relates to the field of aircraft system ground test simulation technology, and in particular to an A330 landing gear sensor simulation device. Background Technology

[0002] In aircraft maintenance engineering, to ensure flight safety, aircraft must undergo high-level scheduled maintenance after a specific flight cycle or calendar period. During such scheduled maintenance, the landing gear, as a critical load-bearing component, often needs to be completely removed for in-situ inspection, repair, or refurbishment. However, the removal of the landing gear raises a significant technical challenge: the aircraft's critical avionics systems, especially the Landing Gear Control and Interface Unit (LGCIU), cannot receive "ground status" logic signals from proximity sensors on the landing gear.

[0003] Therefore, when the landing gear is removed, all proximity sensors are out of position, and the LGCIU interface unit cannot receive the correct inductance signal, thus continuously determining that the aircraft is in an "airborne" state. This directly results in a large number of inspection items being unable to be performed during the landing gear removal window, forcing the maintenance workflow to be interrupted. The aircraft must wait for the landing gear to be inspected, reinstalled, and calibrated before testing can resume. This waiting period is usually as long as 4 to 5 days, causing a serious waste of aircraft downtime, greatly reducing aircraft operating efficiency, and generating high downtime and resource idle costs. For airlines with large fleets, the accumulated economic losses from this problem are particularly significant.

[0004] Currently, the industry lacks a safe, reliable, and standardized solution to this common problem. Existing methods involve complex wiring modifications or the use of non-standard temporary wiring to simulate signals, but these methods suffer from inaccurate signals, poor stability, susceptibility to interference, safety hazards, and the risk of damaging the aircraft's original systems. Summary of the Invention

[0005] (a) Technical problems to be solved This invention provides an A330 landing gear sensor simulation device to overcome the problems of existing technologies where, after the landing gear is removed, the aircraft cannot obtain the correct ground signal, resulting in passive waiting for related tests, excessive downtime, and high maintenance costs.

[0006] (II) Technical Solution To achieve the above objectives, this utility model provides an A330 landing gear sensor simulation device, comprising: a device housing; The device housing is provided with a buffer isolation pad, which includes a buffer partition and a buffer outer sleeve. The buffer outer sleeve has a hollow rectangular structure, and a plurality of buffer partitions are evenly arranged in the buffer outer sleeve. The buffer isolation pad is equipped with two main frame simulation devices and a front landing gear simulation device. The two main frame simulation devices include a left main frame simulation device and a right main frame simulation device. The main frame simulation device includes: a main frame simulation equipment box, the outer wall of which is provided with a main frame simulation connector, and the main frame simulation equipment box is provided with: four 5.4mH inductors and four 4.7mH inductors, which are respectively connected to the main frame simulation connector; The nose landing gear simulation device includes: a nose landing gear simulation equipment box, the outer wall of which is provided with a nose landing gear simulation connector, and the nose landing gear simulation equipment box is provided with: two 5.4mH inductors and two 4.7mH inductors, which are respectively connected to the nose landing gear simulation connector.

[0007] Preferably, the device housing includes: a device base and a device cover, the device base and the device cover being rotatably connected, and a tool storage bag being fixed to the inner wall of the device cover.

[0008] Preferably, the bottom of the device housing is provided with a plurality of movable wheel mounting seats, each movable wheel is provided in a movable wheel mounting seat, a bearing is provided between the movable wheel and the movable wheel mounting seat, the outer sleeve of the bearing is fixedly connected to the movable wheel mounting seat, and the inner sleeve of the bearing is fixedly connected to the movable wheel.

[0009] Preferably, the outer wall of the equipment housing is provided with two symmetrical side handles, which are rotatably connected to the equipment housing.

[0010] Preferably, a telescopic rod seat is fixedly connected to one side of the outer wall of the equipment housing. The telescopic rod seat is provided with a telescopic rod. The telescopic rod includes two symmetrically arranged telescopic rods and a handle. The handle is located at the top of the two telescopic rods and is fixedly connected to the telescopic rod.

[0011] Preferably, both the device base and the device cover are hollow rectangular structures, and the device base and the device cover are connected by a number of rotating hinges.

[0012] Preferably, the left mainframe simulation device, the right mainframe simulation device, and the front landing gear simulation device are respectively isolated by the buffer partition.

[0013] (III) Beneficial Effects This invention provides an A330 landing gear sensor simulation device. It enables precise simulation of air-to-ground sensor signals from different landing gears of the A330 aircraft using inductors with specific inductance values ​​set in the left mainframe, right mainframe, and nose landing gear simulation devices. This provides correct ground logic signals for the aircraft system, ensuring that relevant testing can proceed after landing gear removal. The integrated encapsulation of the buffer pads and simulation devices within the device housing provides basic physical protection for the internal precision electrical components, facilitating overall transport, storage, and on-site deployment, thus improving the device's portability and field applicability. The buffer pads inside the housing isolate and buffer the left mainframe, right mainframe, and nose landing gear simulation devices, effectively reducing the impact of external shocks and vibrations on the internal inductors during transport to the aircraft maintenance platform. This achieves the goals of ensuring safe and efficient ground testing, significantly shortening maintenance downtime, and reducing maintenance costs. Attached Figure Description

[0014] Figure 1 This diagram illustrates the structure of an A330 landing gear sensor simulation device according to the present invention. Figure 2 This invention relates to a side view of an A330 landing gear sensor simulation device. Figure 3 This invention provides a schematic diagram of the main frame simulation device of an A330 landing gear sensor simulation equipment. Figure 4 This invention relates to a schematic diagram of the front landing gear simulation device of an A330 landing gear sensor simulation equipment.

[0015] The components are: 1: Equipment casing; 2: Buffer pad; 3: Tool storage bag; 4: Telescopic pull rod; 5: Side handle; 6: Left main frame simulation device; 7: Right main frame simulation device; 8: Front landing gear simulation device; 9: Casters. Detailed Implementation

[0016] The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0017] In the description of this utility model, it is necessary to understand that the orientation or positional relationship indicated by terms such as "upper", "lower", "left", "right", "inner", "outer", "top", and "bottom" are all based on the orientation or positional relationship shown in the accompanying drawings. The purpose is only to facilitate the description of this utility model and simplify the description, and is not intended to indicate or imply that the indicated component must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, it should not be construed as a limitation of this utility model.

[0018] like Figure 1-4As shown, this utility model provides an A330 landing gear sensor simulation device, including: device housing 1; The outer shell 1 of the device adopts a composite structure of engineering plastic and metal frame. The outer shell 1 includes: device base and device cover. The device base and device cover are rotatably connected. The inner wall of the device cover is fixed with a tool storage bag 3. The tool storage bag 3 is used to load the connection cable of the simulation device. The device base and device cover are both hollow rectangular structures. The device base and device cover are connected by several rotating hinges. The bottom of the outer casing 1 of the device is evenly provided with several movable wheel mounting seats. Each movable wheel mounting seat is provided with a movable wheel 9. The movable wheel 9 is used to support the movement of the A330 landing gear sensor simulation device. A bearing is provided between the movable wheel 9 and the movable wheel mounting seat. The outer sleeve of the bearing is fixedly connected to the movable wheel mounting seat, and the inner sleeve of the bearing is fixedly connected to the movable wheel 9, so that the movable wheel 9 can rotate. The outer wall of the equipment housing 1 is symmetrically provided with two side handles 5. The side handles 5 are rotatably connected to the equipment housing 1. The gripping part of the side handles 5 is covered with non-slip soft rubber. Its rotatable connection structure allows the handles to fit snugly against the housing when not in use, reducing space occupation. A telescopic pull rod seat is fixedly connected to one side of the outer wall of the equipment housing 1. The telescopic pull rod seat is provided with a telescopic pull rod 4. The telescopic pull rod 4 adopts a three-section aluminum alloy sleeve structure. The height adjustment range covers the needs of operators of different heights. The telescopic pull rod 4 includes: two symmetrically arranged telescopic rods and a pull rod handle. The pull rod handle is located at the top of the two telescopic rods and is fixedly connected to the telescopic rods.

[0019] The base of the device is equipped with a buffer pad 2. The main function of the buffer pad 2 is to protect and fix the internal precision simulation device. The buffer pad 2 includes a buffer partition and a buffer outer cover. The buffer outer cover is a hollow rectangular structure. The buffer outer cover and several buffer partitions evenly arranged therein together form a hollow rectangular protective unit. The buffer partitions divide the large hollow rectangular space in the buffer outer cover into several smaller rectangular spaces. These rectangular spaces are used to accommodate the simulation device. The buffer pad 2 effectively eliminates the risk of the simulation device shifting, colliding with each other, or even being damaged during transportation due to bumps and vibrations.

[0020] The buffer pad 2 is equipped with two main frame simulation devices and a front landing gear simulation device 8. The two main frame simulation devices include a left main frame simulation device 6 and a right main frame simulation device 7. The left main frame simulation device 6, the right main frame simulation device 7 and the front landing gear simulation device 8 are isolated by the buffer partition to avoid physical collisions with each other. The mainframe simulation device includes a mainframe simulation equipment box. The outer wall of the mainframe simulation equipment box has a mainframe simulation connector, which is identical to the original interface of the aircraft landing gear. The mainframe simulation equipment box contains four 5.4mH inductors and four 4.7mH inductors, which are connected to the mainframe simulation connector. This mainframe simulation equipment box is used to simulate the inductive characteristics of multiple adjacent sensors during the main landing gear's retraction and extension states. Each inductor is connected to a corresponding connector pin via internal wiring, forming a complete signal path. This mainframe simulation device can reproduce the ground logic signals required by the aircraft system, providing accurate and stable inductive analog quantities to the aircraft's LGCIU via the connector. This allows maintenance personnel to flexibly simulate different operating states of the main landing gear during the ground phase, constructing a complete and reliable ground logic environment for aircraft system ground testing, and ensuring that relevant functional tests can be conducted in advance. The nose landing gear simulation device 8 includes: a nose landing gear simulation equipment box, with a nose landing gear simulation connector on the outer wall of the box. The box contains two 5.4mH inductors and two 4.7mH inductors, corresponding to the proximity and distance signal states of key nose landing gear sensors, respectively. These inductors are connected to the nose landing gear simulation connector via internal circuitry, enabling accurate simulation of nose landing gear sensor signals. This nose landing gear simulation device can provide continuous and reliable ground status signals to the aircraft system even after the nose landing gear has been physically removed, allowing the core aircraft systems to still determine that the aircraft is in a safe ground mode. This allows maintenance personnel to perform relevant system tests and verifications in advance during the ground phase, significantly reducing unnecessary downtime caused by waiting for actual landing gear installation, and improving maintenance efficiency and fleet availability. Both the main frame simulator and the nose landing gear simulator 8 are passive designs, requiring no external power supply. This avoids the potential interference or damage to the aircraft system caused by introducing additional current, further ensuring the safety of the testing process and the purity of the signal.

[0021] The workflow of this A330 landing gear sensor simulation device includes: Step S1: Confirm that the aircraft has performed all standard isolation procedures before the frame failure, including disconnecting the probe heating and other related trip switches, and that the external power supply has been connected. Unplug the trip switches of LGCIU 1 and LGCIU 2, and confirm their status on the ECAM trip switch page to prepare for safe access to analog signals. Step S2: Connect the nose landing gear simulator 8 to the original interface of the aircraft nose landing gear area via its dedicated cable, and connect the left main frame simulator 6 and the right main frame simulator 7 to the original interfaces of the left and right main landing gear areas via corresponding cables. In step S3, the previously pulled-out LGCIU 1 / 2 switch is closed, and the inductive simulation signals of the nose landing gear simulator 8, the left main frame simulator 6, and the right main frame simulator 7 are accurately received and identified by the aircraft's LGCIU system.

[0022] It is understood that the above-mentioned embodiments mentioned in this utility model can be combined with each other to form combined embodiments without violating the principle and logic. Due to space limitations, this utility model will not elaborate further.

[0023] Those skilled in the art will understand that, in the above-described method of the specific implementation, the order in which each step is written does not imply a strict execution order and does not constitute any limitation on the implementation process. The specific execution order of each step should be determined by its function and possible internal logic.

[0024] This utility model provides an A330 landing gear sensor simulation device. Through inductors with specific inductance values ​​set in the left main frame simulation device 6, right main frame simulation device 7, and nose landing gear simulation device 8, it achieves accurate simulation of air-to-ground sensor signals on different landing gears of the A330 aircraft. This provides correct ground logic signals for the aircraft system, ensuring that relevant testing can be carried out after landing gear removal. The integrated encapsulation of the buffer isolation pad 2 and each simulation device by the device housing 1 provides basic physical protection for the internal precision electrical components, facilitating overall handling, storage, and on-site deployment of the equipment, improving its portability and on-site applicability. The buffer isolation pad 2 set inside the device housing 1 isolates and buffers the left main frame simulation device 6, right main frame simulation device 7, and nose landing gear simulation device 8, effectively reducing the impact of external impacts and vibrations on the internal inductors during transportation of the simulation equipment to the aircraft maintenance platform. This achieves the goals of ensuring safe and efficient aircraft ground testing, significantly shortening maintenance downtime, and reducing maintenance costs.

[0025] The various embodiments of the present invention have been described above. These descriptions are exemplary and not exhaustive, nor are they limited to the disclosed embodiments. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments. The terminology used herein is chosen to best explain the principles, practical applications, or technical improvements to the embodiments in the market, or to enable others skilled in the art to understand the embodiments disclosed herein.

Claims

1. An A330 landing gear sensor simulation device, characterized in that, include: Equipment casing (1); The equipment housing (1) is provided with a buffer isolation pad (2), which includes a buffer partition and a buffer outer cover. The buffer outer cover is a hollow rectangular structure, and a plurality of buffer partitions are evenly arranged in the buffer outer cover. The buffer isolation pad (2) is provided with two main frame simulation devices and a front landing gear simulation device (8). The two main frame simulation devices include: a left main frame simulation device (6) and a right main frame simulation device (7). The main frame simulation device includes: a main frame simulation equipment box, the outer wall of which is provided with a main frame simulation connector, and the main frame simulation equipment box is provided with: four 5.4mH inductors and four 4.7mH inductors, which are respectively connected to the main frame simulation connector; The nose landing gear simulation device (8) includes: a nose landing gear simulation equipment box, the outer wall of which is provided with a nose landing gear simulation connector, and the nose landing gear simulation equipment box is provided with: two 5.4mH inductors and two 4.7mH inductors, which are respectively connected to the nose landing gear simulation connector.

2. The A330 landing gear sensor simulation device according to claim 1, characterized in that, The device housing (1) includes: a device base and a device cover, the device base and the device cover are rotatably connected, and a tool storage bag (3) is fixed on the inner wall of the device cover.

3. The A330 landing gear sensor simulation device according to claim 2, characterized in that, The bottom of the equipment housing (1) is uniformly provided with several movable wheel mounting seats, each movable wheel mounting seat is provided with a movable wheel (9), and a bearing is provided between the movable wheel (9) and the movable wheel mounting seat. The outer sleeve of the bearing is fixedly connected to the movable wheel mounting seat, and the inner sleeve of the bearing is fixedly connected to the movable wheel (9).

4. The A330 landing gear sensor simulation device according to claim 3, characterized in that, The outer wall of the equipment housing (1) is symmetrically provided with two side handles (5), and the side handles (5) are rotatably connected to the equipment housing (1).

5. The A330 landing gear sensor simulation device according to claim 4, characterized in that, A telescopic rod seat is fixedly connected to one side of the outer wall of the equipment housing (1). The telescopic rod seat is provided with a telescopic rod (4). The telescopic rod (4) includes two symmetrically arranged telescopic rods and a handle. The handle is located at the top of the two telescopic rods and is fixedly connected to the telescopic rod.

6. The A330 landing gear sensor simulation device according to claim 5, characterized in that, Both the device base and the device cover are hollow rectangular structures, and the device base and the device cover are connected by several rotating hinges.

7. The A330 landing gear sensor simulation device according to claim 6, characterized in that, The left main frame simulation device (6), the right main frame simulation device (7), and the front landing gear simulation device (8) are respectively isolated by the buffer partition.

Images