A composite material aircraft fuselage barrel section integral molding die

An aircraft fuselage and integral molding technology, which is applied in the field of aviation mold equipment, can solve the problems of inconvenient operation and use by fixed personnel, long production cycle, and reduced work efficiency, so as to save design and manufacturing costs and the cost of standard rivets, reduce Production cost and the effect of improving production efficiency

Active Publication Date: 2017-12-29
GUANGLIAN AVIATION IND CO LTD
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0002] In the long-term work practice, when the staff carry out the overall molding process of the aircraft fuselage section, the ordinary molding mold has too many auxiliary parts, the strength and rigidity of the fuselage are low, the process is cumbersome, the production cycle is long, and the production cost is high. Convenient for fixed personnel to operate and use and reduce work efficiency

Method used

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  • A composite material aircraft fuselage barrel section integral molding die
  • A composite material aircraft fuselage barrel section integral molding die
  • A composite material aircraft fuselage barrel section integral molding die

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Embodiment Construction

[0009] refer to figure 1 figure 2 image 3 Described a composite material aircraft fuselage section integral forming die, it comprises fixed chassis 1, fixed bracket 2, rotating device 3, support bracket 4, combination module 5, it is characterized in that: described fixed chassis 1 upper top The front and rear edges of the surface are symmetrically fixedly connected with fixed brackets 2, and each of the fixed brackets 2 is equipped with a rotating device 3 on the top surface, and a support bracket 4 is fixedly connected at the center of the circle between the inner top surfaces of the two rotating devices 3. , the surrounding edge of the support bracket 4 is evenly distributed and fixedly connected with several combined modules 5, the upper top surface of the fixed bracket 2 in the front is in a concave shape, and the upper top surface of each of the fixed bracket 2 is fixedly connected with several supporting modules. Rotating shaft, each surface of the upper top of the ...

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Abstract

The invention discloses an overall forming die for a cylinder section of an airframe of a composite airplane and belongs to the technical field of aviation composite dies. The overall forming die comprises a fixing bottom frame, fixing supports, rotating devices, a supporting support and combined modules and is characterized in that the fixing supports are symmetrically and fixedly connected to the positions of the front edge and the rear edge of the surface of the upper top end of the fixing bottom frame; the surface of the upper top end of each fixing support is provided with one corresponding rotating device.; the supporting support is fixedly connected to the position of a circle center between the surfaces of the top ends of the inner sides of the two rotating devices; and the multiple combined modules are fixedly connected to the positions of the inner peripheral edges of the supporting support in an evenly-distributed manner. The overall rigidity and strength of the cylinder-section airframe are improved, the service life of the cylinder-section airframe is prolonged, the riveting and sealing processes are omitted as well, and meanwhile the design and manufacture cost of a riveting type frame and the cost of standard part rivets are saved.

Description

Technical field: [0001] The invention belongs to the technical field of aviation mold equipment, and in particular relates to an integral forming mold of composite material aircraft fuselage barrel section. Background technique: [0002] In the long-term work practice, when the staff carry out the overall molding process of the aircraft fuselage section, the ordinary molding mold has too many auxiliary parts, the strength and rigidity of the fuselage are low, the process is cumbersome, the production cycle is long, and the production cost is high. It is convenient for fixed personnel to operate and use and reduces work efficiency. Invention content: [0003] The purpose of the present invention is to combine the upper, lower, left and right four wall panels into one body to form a closed barrel fuselage at one time, which not only increases the overall rigidity, strength and barrel strength of the barrel fuselage. The service life of the fuselage is shortened, and the riv...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B29C33/00B29C33/30B29C70/54
CPCB29C33/00B29C33/301B29C33/305B29C70/54
Inventor 胡泉董俊福刘兴宇宋扬肖军刘凤艳杜晋国潘兴
Owner GUANGLIAN AVIATION IND CO LTD
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