A single sliding block rolling spray mode variable
centroid aircraft model and a designing method for structural
layout parameters thereof relate to the field of
flight vehicle design, and aim to solve the problems of
ablation to an aerodynamic
rudder in a conventional hypersonic aircraft and complexity in sliding block
layout inside a conventional variable
centroid aircraft. The aircraft model provided by the invention comprises two fixed wings, a
projectile body, a rolling spray engine and a movable body, wherein the two fixed wings are symmetrically arranged on the two sides of the
projectile body; the tip of the cone-shaped body of the movable body is connected with the head of the
projectile body through a movably connecting point O1; a guide rail is arranged at the
tail end of the projectile body, the root part of the cone-shaped body of the movable body is connected with the O2 point of the guide rail at the
tail part of the projectile body in a sliding manner; since the movable body is further expanded to serve as a main body, the
mass of the movable body accounts for most part of the
mass of the entire
system, the projectile body is taken as a driven body, the purpose of maneuvering control can also achieved, the motion of the projectile body can be controlled through an
actuator on the movable body; the integral aerodynamic configuration of the projectile body is ensured. The aircraft model provided by the invention is applicable to the field of
flight vehicle design.