Method for preparing composite material through hot-pressing strengthening

Abstract

The invention relates to a method for preparing a composite material through hot-pressing strengthening. The method comprises the following steps that (1) a base body (4) is machined to the designed size; (2) a lining plate (3) is sleeved with the base body (4), the base body (4) is internally supported and clamped, and then a reinforcing body (5) is laid on the surface of the outer side of the base body (4); (3) the base body (4) on which the reinforcing body (5) is laid is integrally hooped by using an outer side hoop (6), and the fastening torque of the outer side hoop (6) is adjusted through a bolt; (4) a high-frequency induction coil (8) is arranged on the outer side of the outer side hoop (6) to be heated; and (5) cooling is conducted to reach room temperature, and finish machining is performed on the outer molded surface by taking the inner molded surface as a positioning reference to obtain the composite material. Compared with the prior art, the requirement of an aircraft shell for an original material performance of a product is lowered by the method, and a structural part can be strengthened as required in the product level stage by adopting traditional cast magnesium alloy or wrought magnesium alloy.

Description

technical field [0001] The invention relates to the field of composite material manufacturing, in particular to a method for preparing composite materials through hot pressing strengthening. Background technique [0002] In the field of aerospace, the pursuit of lightweight design for aircraft, launch vehicles, and missile products has never stopped. As one of the currently mature and light-density metal materials, magnesium and aluminum alloys are widely used in various types of missile cabins and aircraft cabins. Segment, satellite platform important structural parts products. [0003] As the flight conditions of various new-generation aircraft and missiles become more and more severe, the requirements for mechanical properties such as tensile strength and fatigue strength of the main structural materials continue to increase, and traditional aluminum alloy materials have been difficult to meet the flight requirements of complex limits in some fields. working conditions. ...

AI Technical Summary

Problems solved by technology

[0003] As the flight conditions of various new-generation aircraft and missiles become more and more severe, the requirements for mechanical properties such as tensile strength and fatigue strength of the main structural materials continue to increase, and traditional aluminum alloy materials have been difficult to meet the flight requirements of complex limits in some fields. Condition

At present, the commonly used solutions use titanium alloys or other metal alloys with better mechanical properties, which means that a large number of payloads of aircraft and missile weapons are sacrificed, and it is difficult to meet the design indicators and mission requirements of model products.

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