Composite airborne equipment stand for aircraft

Abstract

The invention relates to a composite on-board device rack for an airplane. A traditional on-board device rack is formed by riveting aluminum alloy non-standard section bars and has the main defects of being large in number of parts, large in mass and poor in vibration resistance and fatigue resistance, and in order to overcome the defects and achieve an airplane part weight reduction purpose, a special composite on-board device rack used for installing and fixing operation and control instruments and meters and in-built instruments on the airplane. A multi-box hollow frame structure formed by a carbon fiber composite laying layer in an overall co-curing manner is mainly composed of an upper panel, a front panel, a rear panel, wing plates, supporting columns, a bottom plate, a middle partition, maintenance opening cover plates and the like, and the structure is formed through a die in a one-time heating and co-curing manner. The composite on-board device rack is small in structure mass, good in vibration resistance and fatigue resistance, small in number of parts and easy to assemble. The mass of the composite on-board device rack is smaller than that of the same aluminum alloy structure by about 30%, and the composite on-board device rack is suitable for being used for occasions such as the airplane with the weight reduction requirement.

Description

technical field [0001] The invention relates to a composite material airborne equipment stand for aircraft. Background technique [0002] At present, the airborne equipment stand for aircraft is an aircraft component. An important goal in the process of aircraft design and development is to minimize its weight under the premise of ensuring its use function and quality. The traditional airborne equipment stand is generally riveted by aluminum alloy non-standard profiles. The main disadvantages are: many parts, heavy weight, high production cost, easy deformation, poor corrosion resistance and oxidation resistance, vibration resistance, impact resistance and fatigue resistance. Poor, complex assembly process, complex equipment installation and maintenance, and short service life, resulting in shortened life of electrical components in the control platform, reduced control accuracy of airborne equipment, decreased payload of the whole machine, and decreased cruising range; exis...

AI Technical Summary

Problems solved by technology

[0003] The technical problem to be solved by the present invention is that during the design and development process of the aircraft airborne equipment stand, the original aluminum alloy structure stand has many parts, heavy weight, poor resistance to vibration shock and fatigue, and complex assembly process. Accurate control of airborne equipment is difficult. The existing airborne equipment platforms made of composite materials mainly have the disadvantages of not forming the overall structure and reinforcing ribs first and then gluing, resulting in increased glue consumption and weight gain; in order to overcome the existing Insufficient, it is possible to design a kind of composite material airborne equipment platform for aircraft, which adopts the overall co-cured structure of composite materials, reasonably designs the number of layers and direction of carbon fiber composite materials, and enhances the strength of the overall structure (the specific strength is higher than that of aluminum alloy 3 times), stiffness (specific stiffness is more than 2 times higher than that of aluminum alloy) and fatigue resistance (anti-fatigue life is more than 10 times higher than that of aluminum alloy), reducing the structural weight as much as possible

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