Integrated drag reduction design method of missile wiring trough and sliding block separation socket

An integrated drag reduction design method for a missile wire duct and a sliding block separation socket comprises the steps of firstly obtaining aerodynamic characteristic data of independent designof the missile wire duct, the sliding block and the separation socket, and then according to the requirements of a missile guiding and launching frame for the sliding block and the separation socket,combining with the requirements of a cable for the internal space of the wire duct; designing main parameters of the sliding block and the separation socket; according to the aerodynamic performance requirement of the missile, designing the integrated drag reduction molding structure appearance of the wire groove, the sliding block and the separation socket in sequence; designing and determining section shapes and positions of the sliding block and the separation socket according to missile launching and structural strength design requirements, finally obtaining an integrated resistance reduction structure of the missi