Bearing and ablative thermal protection integrated composite missile wing and rudder for hypersonic missile, and preparation method of bearing and ablative thermal protection integrated composite missile wing and rudder

Abstract

The invention discloses a bearing and ablative thermal protection integrated composite missile wing and rudder for a hypersonic missile, and a preparation method of the bearing and ablative thermal protection integrated composite missile wing and rudder. The preparation method comprises the following steps: (1) according to the situation that different hypersonic missile models have different requirements for the air flow temperature borne by the missile wing and rudder, the ablation time and the wing tip displacement under an aerodynamic load, the overall overlay structure of the missile wingand rudder is designed into two parts, namely a missile wing and rudder bearing layer and a missile wing and rudder ablation-resisting layer; and (2) one of a woven carbon / high-temperature epoxy prepreg cloth, a woven carbon / polyimide prepreg cloth and a woven carbon / bismaleimide prepreg cloth is selected as the missile wing and rudder bearing layer, and one of a carbon / phenol prepreg cloth, a carbon / benzoxazine prepreg cloth and a carbon / aryne resin prepreg cloth is adopted as the missile wing and rudder ablation-resisting layer, wherein the fiber mass content is controlled to be 65-75%. A carbon fiber prepreg cloth overlay one-time die-pressing process is adopted, and the performance defect caused by the fact that structural / functional layer matrix resin interpenetrates due to the excessively-high resin content, the early pressure applying moment and the excessively-large pressure, and consequently too much glue liquid of the missile wing and rudder ablation-resisting layer overflows is avoided.

Description

technical field [0001] The invention belongs to the technical field of composite materials, and specifically relates to a structure and a preparation method of a wing and a rudder, in particular to a wing, a rudder and a preparation method thereof of a composite material integrated with load bearing, ablation and heat protection for hypersonic missiles. Background technique [0002] The wings and rudders are the key components of hypersonic missiles, which provide flight lift for the missiles. In addition, they are subjected to complex air loads and aerodynamic heating during flight, so they need to have low weight, high strength, and ablation resistance requirements. [0003] At this stage, most of the wings and rudders are made of aluminum alloy, titanium alloy and other metal materials. Under the conditions of high strength and ablation resistance, the inert quality is significantly higher than that of composite wings and rudders, resulting in a significant effective range...

AI Technical Summary

Problems solved by technology

[0007] The present invention aims at the disadvantages of multiple macroscopic interfaces and poor strength in the application of the foam sandwich core to the fiber-reinforced resin-based composite material skin and the chopped fiber molded composite wing and rudder in the prior art for hypersonic missiles, and provides A hypersonic missile with bearing, ablation and heat-resistant integrated composite material wing and rudder, the composite material is a braided carbon / phenolic, benzoxazine, aryne resin, and carbon / high temperature ring Oxygen, polyimide, bismaleimide materials as the basis, combined with laying, vacuum molding and other processes, can solve the high-temperature micro-ablation high-temperature and micro-ablation composite material in a superb environment

Images