A kind of method for preparing composite material by hot pressing

Abstract

The invention relates to a method for preparing a composite material by hot-pressing strengthening. The method comprises the following steps: (1) processing a base body (4) to a design size; (2) sheathing the base body (4) on a lining plate (3) , and clamp the inner support of the matrix (4), and then lay the reinforcement (5) on the outer surface of the matrix (4); (3) use the outer hoop (6) to integrate the matrix (4) on which the reinforcement (5) is laid as a whole. hoop, adjust the tightening torque of the outer hoop (6) through bolts; (4) place the high-frequency induction coil (8) on the outside of the outer hoop (6) for heating; (5) cool down to room temperature, and then The inner profile is used as the positioning reference, and the outer profile is finished to obtain a composite material. Compared with the prior art, the present invention reduces the requirement of the aircraft shell on the performance of the original material of the product, and the traditional cast magnesium alloy or wrought magnesium alloy can be used to realize on-demand strengthening of the structural parts at the product stage.

Description

technical field [0001] The invention relates to the field of composite material manufacturing, in particular to a method for preparing composite materials by hot pressing. Background technique [0002] In the aerospace field, the pursuit of lightweight design for aircraft, launch vehicles and missiles has never stopped. Magnesium and aluminum alloys, as one of the currently mature and lighter metal materials, are widely used in various missile cabins and aircraft cabins. Segment and satellite platform important structural products. [0003] With the increasingly severe flight conditions of various new-generation aircraft and missiles, the requirements for mechanical properties such as tensile strength and fatigue strength of main structural materials have been continuously improved, and traditional aluminum alloy materials have been difficult to meet the complex limit of flight in some fields. working condition. At present, the commonly used solutions use titanium alloys o...

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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