Joint-variable RTM integrally-formed composite material missile wing and manufacturing method thereof

Abstract

The invention discloses a joint-variable RTM integrally-formed composite material missile wing and a manufacturing method thereof, a root rib and an end rib are respectively arranged at two ends along the wingspan direction, a front beam and a rear beam are arranged between the root rib and the end rib, and the front beam and the rear beam are respectively vertical to the root rib and the end rib; the end parts of the front beam and the rear beam on the root rib side extend outwards and cross over the root rib, and the extending parts of the front beam and the rear beam are used as connecting joints of the front beam and the rear beam; and three areas divided by the front beam and the rear beam between the root rib and the end rib are filled with foam, the exterior of the overall structure filled with the foam is covered with the upper skin and the lower skin to obtain the missile wing, the missile wing is made of full-carbon-fiber composite materials, the bearing capacity of the missile wing is improved, and the problems of complexity, deformation and complex connection mode of metal parts in a mixed structure are solved. In addition, a missile wing structure is prepared through the RTM integral forming process, and a low-cost solution is provided for product joint form change.

Description

technical field [0001] The application belongs to the field of application of conformable materials, in particular to an RTM integrally formed composite wing with variable joints and a manufacturing method thereof. Background technique [0002] With the continuous improvement of missile performance requirements, more and more attention has been paid to the weight reduction of missile components. As a material with high specific strength and specific stiffness, carbon fiber composites can well meet this demand, so it is more and more widely used in missiles. [0003] At present, the wing mainly adopts all-metal or hybrid structure, among which, the hybrid structure is mostly metal skeleton + composite material skin or metal joint + composite material wing body. For the above two main forms of the wing, there are the following problems. The all-metal has the problem of large weight and small carrying capacity; and the hybrid structure is prone to deformation due to the differ...

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Problems solved by technology

[0004] In order to solve the deficiencies in the prior art, this application proposes a variable-joint RTM integral molding composite wing and its manufacturing method, which uses a full carbon fiber composite structure to improve the bearing capacity of the wing, and at the same time avoids metal in the hybrid structure. Complex parts, deformation and complex connection methods

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