Winding forming method for carbon fiber composite material shell precision missile wing seat

The invention discloses a winding forming method for a carbon fiber composite material shell precision missile wing seat. The method comprises the following steps of 1) adhering an elastic film to thelower surface of an missile wing seat mounting seat; 2) positioning and fixing the missile wing seat by adopting a positioning tool; 3) removing the positioning tool after heating and curing; 4) selecting high-modulus carbon fiber unidirectional prepreg, and carrying out at least three cycles of prepreg paving according to a paving structure; 5) dipping continuous carbon fibers into the resin glue solution, and winding at least six layers of annular carbon fibers on the missile wing seat mounting seat; 6) positioning and fixing the missile wing seat again by adopting the positioning tool; and7) heating and curing the laid and wound carbon fiber layer, and dismounting the positioning tool after curing is completed. According to the winding forming method, the paving designability of different loads is realized, th