Sled landing gear drop test apparatus

Abstract

The utility model relates to a skid -type undercarriage drop test device, including gantry, electric hoist, electromagnet, metal section tool rest, counterweight, the metal section tool rest is used for installing counterweight, and still include the undercarriage installation tool of skid -type undercarriage, electric hoist fixed mounting is below the gantry, is used for driving the lift of electromagnet, the electromagnet can adsorb the metal section tool rest when electrification.

Description

Technical Field

[0001] This utility model relates to the field of aircraft testing equipment, specifically a skid-type landing gear drop test device. Background Technology

[0002] Landing gear drop test apparatuses are critical testing devices used to simulate the impact loads experienced by aircraft landing gear during landing. They are primarily used to verify the structural strength, energy absorption performance, and reliability of the landing gear. Drop testing is a crucial step in the landing gear design process. Professional drop test benches are expensive and are often used in the verification phase of model design. For the initial stages of landing gear structural research and development, low-cost and easy-to-use drop test apparatuses are essential. Summary of the Invention

[0003] This utility model provides a skid-type landing gear drop test device, including a gantry frame, an electric hoist, an electromagnet, a metal profile tooling frame, and a counterweight;

[0004] The metal profile tooling frame is used to install counterweights, and also includes a landing gear mounting fixture for installing skid-type landing gear. The electric hoist is fixedly installed below the gantry frame and is used to drive the lifting and lowering of the electromagnet. When the electromagnet is energized, it can attract the metal profile tooling frame.

[0005] Furthermore, the metal profile tooling frame is provided with multiple first mounting holes, and each counterweight is provided with a second mounting hole. The first mounting holes and the second mounting holes cooperate to fix the counterweight on the metal profile tooling frame.

[0006] Compared with existing landing gear shock devices, this invention has the advantages of simple structure, convenient assembly and configuration, and low cost, and is especially suitable for the initial stage of landing gear structure research and development. Attached Figure Description

[0007] Figure 1 This is a schematic diagram of the skid-type landing gear drop test device. Detailed Implementation

[0008] See Figure 1 The skid-type landing gear drop test device includes a gantry frame 1, an electric hoist 2, an electromagnet 3, a metal profile tooling frame 4, and a counterweight 5.

[0009] The metal profile fixture 4 is provided with multiple first mounting holes, and each counterweight 5 is provided with a second mounting hole, so that one or more counterweights 5 can be installed on the metal profile fixture 4 (for example, by bolt connection), thereby achieving flexible adjustment of the delivery quality and realizing the purpose of step-by-step testing.

[0010] The metal profile fixture 4 also includes a landing gear mounting fixture for mounting the skid-type landing gear 6. The electric hoist is fixedly installed below the gantry 1 and is used to drive the lifting and lowering of the electromagnet 3. In use, the skid-type landing gear 6 is mounted on the lower part of the metal profile fixture 4 using the landing gear mounting fixture. A counterweight 5 is installed as needed. The electromagnet 3 is energized, attracting the metal profile fixture 4 to the electromagnet 5. Then, driven by the electric hoist 2, the electromagnet 5 moves the metal profile fixture 4 (with the counterweight 5 and skid-type landing gear 6 fixed on it) upwards as a whole. After reaching a preset height, the electromagnet is de-energized, and the metal profile fixture 4 falls freely. Thus, the counterweight 5 and the metal profile fixture 4 can simulate the weight of different aircraft, and the lifting motion of the electric hoist 2 can simulate different heights, thereby completing various tests.

[0011] Compared with existing landing gear shock devices, this invention has the advantages of simple structure, convenient assembly and configuration, and low cost, and is especially suitable for the initial stage of landing gear structure research and development.

[0012] The above embodiments are only used to illustrate the technical solutions of this utility model, and are not intended to limit it. Although this utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this utility model.

Claims

1. A skid-type landing gear drop test device, characterized in that, Includes gantry frame (1), electric hoist (2), electromagnet (3), metal profile tooling frame (4), and counterweight (5); The metal profile tooling frame (4) is used to install counterweights (5), and also includes a landing gear mounting tool for installing skid-type landing gear (6). The electric hoist (2) is fixedly installed below the gantry frame (1) and is used to drive the lifting of the electromagnet (3). When the electromagnet (3) is energized, it can attract the metal profile tooling frame (4).

2. The skid-type landing gear drop test device according to claim 1, characterized in that, The metal profile tooling frame (4) is provided with multiple first mounting holes, and each counterweight (5) is provided with a second mounting hole. The first mounting holes and the second mounting holes cooperate to fix the counterweight (5) on the metal profile tooling frame (4).

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