A landing gear limiting device for an aircraft engine during a test run

Abstract

The utility model belongs to the technical field of aircraft ground equipment, disclose a kind of landing gear limiting device when aircraft engine test run, including stop block and baffle, stop block side is attached on the curved surface of the main landing gear strut of aircraft by connecting piece, stop block other side is equipped with boss, baffle is L-shaped structure that has added triangular reinforcing rib, the top side of baffle is resisted in the boss side below of stop block.Using swing arm type landing gear aircraft, after using the limiting device of the utility model, when engine test run is carried out, it can withstand huge reaction force under full thrust of engine, baffle is fixed on ground device by bolt and cannot slide or fall down, without security risk.And aircraft short takeoff can be simulated.

Description

Technical Field

[0001] This utility model belongs to the field of aircraft ground equipment technology, and relates to a landing gear limiting device, specifically a landing gear limiting device during aircraft engine testing. Background Technology

[0002] Traditionally, wheel chocks and brakes are used to secure the aircraft during engine testing. However, using wheel chocks and brakes to secure the aircraft during afterburner testing has the following disadvantages: 1. Conventional wheel chocks are designed to prevent movement when stationary, but they cannot withstand the huge reaction force under full thrust and may be pushed away or damaged.

[0003] 2. Improper placement may cause the wheel chocks to slip or tip over when under force, failing to effectively secure the aircraft.

[0004] 3. Soft, wet, or snowy ground conditions can reduce the friction and stability of wheel chocks, increasing the risk of failure.

[0005] For aircraft using rocker-arm landing gear, the stress points during engine testing differ from those of conventional landing gear. Under afterburner, the enormous thrust, due to its interaction, causes a large torque transmitted from the wheel chocks to the buffers via the rocker arm. This torque could compress the buffers, causing the wheels to overshoot the wheel chocks and the aircraft to lose control, posing a significant safety hazard. Utility Model Content

[0006] To address the aforementioned issues, this invention proposes a landing gear limiting device for aircraft engine testing. The baffle is fixed to the ground with bolts, preventing the device from sliding or tipping over and eliminating any safety hazards.

[0007] The technical solution of this utility model is as follows: A landing gear limiting device for aircraft engine testing includes a block and a baffle. One side of the block is attached to the curved surface of the main landing gear strut of the aircraft via a connector, and the other side of the block is provided with a boss. The baffle is an L-shaped structure with added triangular reinforcing ribs, and the top side of the baffle abuts against the lower side of the boss of the block.

[0008] Furthermore, the stop is connected to the main landing gear strut via fixing bolts.

[0009] Furthermore, there are two fixing bolts, which replace the original lower pivot stop bolts of the main landing gear strut.

[0010] Furthermore, the bottom of the baffle is fixedly connected to the ground.

[0011] Furthermore, elastic pads are provided between the stop block and the curved surface of the main landing gear strut.

[0012] Furthermore, the elastic gasket is specifically a rubber gasket.

[0013] The advantages of this utility model are as follows: For aircraft using rocker-arm landing gear, the limiting device of this invention can withstand the enormous reaction force under the full thrust of the engine during engine testing. The baffle is fixed to the ground with bolts and will not slide or tip over, posing no safety hazard. It can also simulate short takeoffs. Attached Figure Description

[0014] Figure 1 The installation method of this utility model and the main landing gear is shown; Figure 2 The installation method of the stop block and the main landing gear strut is shown; Figure 3 A three-dimensional structural diagram of the upper part of this utility model is shown; Figure 4 A three-dimensional structural diagram of the baffle is shown.

[0015] Among them, 1—stop block; 2—rubber pad; 3—fixing bolt; 4—baffle; 11—nut; 22—main landing gear strut; 33—rocker arm; 44—buffer. Detailed Implementation

[0016] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions of the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this utility model, not all embodiments. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this utility model.

[0017] The features and illustrative embodiments of various aspects of this utility model will now be described in detail. In the following detailed description, numerous specific details are set forth in order to provide a comprehensive understanding of this utility model. However, it will be apparent to those skilled in the art that this utility model can be practiced without requiring some of these specific details. The following description of embodiments is merely intended to provide a better understanding of this utility model by illustrating examples of it. This utility model is by no means limited to any specific arrangements and methods set forth below, but covers any improvements, substitutions, and modifications to the structure, method, and apparatus without departing from the spirit of this utility model. In the accompanying drawings and the following description, well-known structures and techniques are not shown to avoid unnecessarily obscuring this utility model.

[0018] In the description of this utility model, it should be noted that the directions or positional relationships indicated by terms such as "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer" are based on the directions or positional relationships shown in the accompanying drawings and are only for the convenience of describing this utility model and simplifying the description. They should not be construed as limiting this utility model. In addition, the use of ordinal numbers (e.g., "first and second," etc.) is for distinguishing objects and is not limited to this order, and should not be construed as indicating or implying relative importance.

[0019] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly, encompassing both direct connection and indirect connection via an intermediate medium. Those skilled in the art can understand the specific meaning of these terms in this utility model based on the specific circumstances.

[0020] It should be noted that, where there is no conflict, the embodiments of this utility model and the features therein can be combined with each other, and the various embodiments can be referenced and cited in turn. The present utility model will now be described in detail with reference to the accompanying drawings and embodiments.

[0021] Example 1: A landing gear limiting device for aircraft engine testing includes a block 1 and a baffle 4. One side of the block 1 is attached to the curved surface of the main landing gear strut 22 of the aircraft via a connector, and the other side of the block 1 is provided with a boss. The baffle 4 is an L-shaped structure with added triangular reinforcing ribs, and the top side of the baffle 4 abuts against the lower side of the boss of the block 1.

[0022] The stop block 1 is connected to the main landing gear strut 22 by fixing bolts 3.

[0023] There are two fixing bolts 3, which replace the original lower pivot stop bolts of the main landing gear strut 22.

[0024] The bottom of baffle 4 is fixedly connected to the ground.

[0025] An elastic pad is provided between the curved surfaces of the stop block 1 and the main landing gear strut 22.

[0026] The elastic gasket is specifically a rubber gasket 2.

[0027] Example 2: A landing gear limiting device for aircraft engine testing includes a stop block, a rubber pad, fixing bolts, and a baffle plate. The stop block is fixed to the main landing gear strut by two fixing bolts through a curved surface that conforms to the main landing gear strut. The rubber pad is installed between the stop block and the main landing gear strut, providing cushioning and a tight fit. Two fixing bolts replace the original lower pivot bolts of the main landing gear strut, connecting and fixing the stop block, rubber pad, and main landing gear strut. The baffle plate, with two triangular reinforcing ribs stabilizing the sides and bottom, is installed on the ground by six bolts. The side of the baffle plate abuts against the stop block installed on the main landing gear strut, preventing the aircraft from moving during testing. The baffle plate can be raised and lowered via a ground-based device to achieve short takeoff. The entire device consists of two sets, symmetrically arranged in front of the two main landing gear struts.

[0028] For details, please refer to [link / reference]. Figures 1-4 This utility model provides a technical solution: a landing gear limiting device for aircraft engine testing, comprising a stop block, a rubber pad, fixing bolts, and a baffle plate. The stop block is fixed to the main landing gear strut by two fixing bolts and nuts, with a rubber pad placed between the stop block and the main landing gear strut. The baffle plate is fixed to the ground by six bolts. The aircraft is pushed until the stop block and the baffle plate are in contact, allowing for engine testing. Specifically, when the baffle plate is installed on a ground device, controlling its erection and folding via the ground device can simulate short takeoff.

[0029] Specifically, the stop is made of high-strength aluminum alloy, with an inner surface designed to conform to the curvature of the main landing gear strut. Two bolt holes are located on one side of the stop for securing it to the main landing gear strut with bolts. The stop's design ensures it conforms to the curvature of the main landing gear strut and effectively prevents aircraft movement during testing. During afterburner testing, a longitudinal torque is generated, causing the aircraft to pitch down. The main landing gear extends slightly, changing the contact position between the stop and the baffle. The curved design of the outer side of the stop ensures that the stop and baffle maintain effective contact at all times.

[0030] Specifically, a rubber pad is installed between the stop block and the main landing gear strut. The rubber pad is made of a material with high elasticity and wear resistance. The rubber pad acts as a buffer, preventing metal-to-metal collisions and scratches caused by direct contact between the stop block and the main landing gear strut, while also increasing the friction between the two to ensure that the stop block is stably attached to the main landing gear strut.

[0031] Specifically, the fixing bolts are used to replace the original lower pivot stop bolts on the main landing gear struts, thereby installing the stop blocks and rubber gaskets on the main landing gear struts.

[0032] Specifically, the baffle is equipped with triangular reinforcing ribs on its sides, which are used to stabilize the sides and bottom of the baffle to enhance its structural strength and stability. The baffle is fixed to the ground with six bolts, which are symmetrically distributed on both sides of the baffle to ensure that the baffle is firmly installed on the ground of the test area.

[0033] Operating Principle: During aircraft engine testing, a stop block is installed on the main landing gear strut, ensuring a rubber pad is positioned between the stop block and the strut. Subsequently, a baffle is installed at a predetermined ground location and secured with six bolts. The side of the baffle presses against the stop block mounted on the main landing gear strut, forming an effective blocking structure to prevent the aircraft from moving or sliding due to thrust during engine testing. Specifically, when the baffle is mounted on a ground device, controlling its erection and folding via the ground device can simulate short takeoff.

[0034] Through the above embodiments, this utility model provides a reliable and efficient landing gear fixing device for aircraft engine testing, which can effectively ensure safety during the testing process. It has been verified in actual afterburner testing of a certain type of aircraft engine, and this utility model has successfully achieved its function and performed excellently.

Claims

1. A landing gear limiting device for aircraft engine testing, characterized in that, It includes a stop block (1) and a baffle (4). One side of the stop block (1) is attached to the curved surface of the main landing gear strut (22) of the aircraft via a connector. The other side of the stop block (1) is provided with a boss. The baffle (4) is an L-shaped structure with added triangular reinforcing ribs. The top side of the baffle (4) rests against the bottom of the boss side of the stop block (1).

2. The landing gear limiting device during aircraft engine testing according to claim 1, characterized in that, The stop block (1) is connected to the main landing gear strut (22) by fixing bolts (3).

3. The landing gear limiting device during aircraft engine testing according to claim 2, characterized in that, There are two fixing bolts (3), which replace the original lower pivot stop bolt of the main landing gear strut (22).

4. The landing gear limiting device for aircraft engine testing according to claim 1, characterized in that, The bottom of the baffle (4) is fixedly connected to the ground.

5. The landing gear limiting device for aircraft engine testing according to claim 1, characterized in that, An elastic pad is provided between the curved surfaces of the stop block (1) and the main landing gear strut (22).

6. The landing gear limiting device during aircraft engine testing according to claim 5, characterized in that, The elastic gasket is specifically a rubber gasket (2).

Images