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.