| description abstract | First, this article proposes a driving method for multilink mechanisms under a standard mode. Applying specific constraints transforms motion forms from rotational to linear motion. Meanwhile, several standard multilinkage models' transmission characteristics and driving efficiency are analyzed, and the effective internal space utilization rate under different schemes is evaluated. Second, aiming at the available annular space between the missile's external envelope and the engine nozzle, based on the standard multilink mechanism, the regular polygon drive module is extended to a circular configuration, and an optimal design method of the drive mechanism with boundary constraints is proposed. This approach can be applied to missiles of varying dimensions, overcoming challenges associated with coordinated driving and synchronous motion transmission in confined annular spaces, thereby offering a new solution for adaptive stability control in missiles. Finally, under specified constraint conditions, an optimal parameter set was selected to design a deployable flared skirt mechanism. Theoretical analysis and simulation of the kinematics and dynamics performance of this mechanism were conducted, followed by prototype testing. Results indicate that the flared skirt mechanism exhibits excellent reciprocating performance, achieving a maximum unfolding angle of 10.6 deg within a continuous range of 0 deg to 10.6 deg. | |
