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Large-loading multi-point coordinated undercarriage fixed connection structure

A multi-point coordination and landing gear technology, applied in the chassis and other directions, to achieve the effect of realizing comprehensive utilization of structures, improving structural efficiency, and increasing strength and rigidity

Active Publication Date: 2015-12-02
CHINA ACAD OF LAUNCH VEHICLE TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] In order to solve the problem of how to withstand large impact loads when the UAV lands, the present invention provides a fixed connection structure for large load-carrying multi-point coordinated landing gear

Method used

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  • Large-loading multi-point coordinated undercarriage fixed connection structure
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  • Large-loading multi-point coordinated undercarriage fixed connection structure

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Embodiment Construction

[0038] The present invention will be further described below in conjunction with the accompanying drawings.

[0039] figure 1 and figure 2It is a schematic diagram of the overall installation of the fixed connection structure of the landing gear and the fuselage. The fixed connection structure mainly includes: the main landing gear fixed connection joint beam 1, the inner pressure rod 2, the outer pressure rod 3, the landing gear diagonal stay rod joint 5, and the landing gear diagonal stay rod adapter 4 can be selected according to the actual situation. The fixed connection structure is connected with the following parts of the aircraft: the side beam of the landing gear compartment opening 6, the landing gear bulkhead 7, the reinforcement beam of the landing gear bulkhead 8, the intersection frame 9 of the landing gear, the rear reinforcement frame 10 of the landing gear compartment opening, and the side wall of the fuselage Plate 11, main landing gear 12, main landing ge...

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Abstract

The invention relates to a large-loading multi-point coordinated undercarriage fixed connection structure which comprises a main undercarriage fixed connection joint girder, an inside pressure bar, an outside pressure bar and an undercarriage diagonal draw bar joint, and an undercarriage diagonal draw bar adaptor can be selectively arranged according to practical situations. An undercarriage diagonal draw bar is connected to the undercarriage diagonal draw bar joint through the undercarriage diagonal draw bar adaptor, the undercarriage diagonal draw bar joint is connected with an undercarriage bulkhead stiffening girder and an undercarriage intersection frame, and two ends of the inside pressure bar and the outside pressure bar are respectively connected with the main undercarriage fixed connection joint girder and the undercarriage diagonal draw bar adaptor so as to form an integral force transfer system, thereby dispersing the load of the main undercarriage fixed connection joint girder, effectively reducing the load transferred from the undercarriage diagonal draw bar joint to the undercarriage bulkhead stiffening girder and the undercarriage intersection frame, also reducing the load transferred from the main undercarriage fixed connection joint girder to a fuselage, and further effectively solving the problem of large landing load of the undercarriage.

Description

technical field [0001] The invention relates to a fixed connection structure of a large load-carrying multi-point coordinated landing gear, belonging to the technical field of unmanned aerial vehicle structure design. Background technique [0002] Advanced high-performance UAVs are subjected to large impact loads when they land, and due to factors such as the overall layout of the body structure, it is impossible to directly use the longitudinal beams of the fuselage to directly transmit the landing load of the main landing gear. [0003] According to literature research, the current domestic related design schemes are mainly traditional structural configurations, which are directly connected to the main landing gear to transfer loads through the comprehensive use of fuselage frames, beams or wing ribs, beams or wall joints, which cannot be applied to a class of advanced unmanned aerial vehicles. Man-machine structure. [0004] How to solve the transmission of large impact ...

Claims

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Application Information

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IPC IPC(8): B64C25/06
Inventor 顾春辉熊艳丽唐青春张沥田甜崔深山崔占东张帆李晓乐许健吴迪韩威
Owner CHINA ACAD OF LAUNCH VEHICLE TECH
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