A Control Mechanism of Spatial Linkage Missile Rudder Surface

Abstract

The invention discloses a spatial linkage type missile control plane control mechanism. Currently, a large amount of missile body space needs to be occupied when a steering engine is installed. According to the spatial linkage type missile control plane control mechanism, each first rudder room and an adjacent second rudder room are fixed through a connecting room; each first rudder room is connected with a first rudder; each second rudder room is connected with a second rudder; a first rudder shaft fixed to each first rudder and the corresponding first rudder room form a revolute pair; a shaft sleeve fixed to one end of each first connecting rod is fixed to the corresponding rudder shaft; each sliding block and a corresponding guide rail form a sliding pair, wherein a boss is arranged at the top of the sliding block; two ends of each second connecting rod are hinged to the corresponding boss and the other end of the corresponding first connecting rod; one end of each third connecting rod is fixed to the corresponding sliding block; a nut block fixed to the other end of each third connecting rod and a corresponding lead screw form a screw pair; one end of each lead screw and an output shaft of the corresponding second rudder are connected through a coupler; a second rudder shaft of each second rudder and the corresponding second rudder room form a revolute pair; and an output shaft of each first steering engine and the corresponding second rudder shaft are fixed. According to the spatial linkage type missile control plane control mechanism, the steering engines of some rudders are transferred into the rudder room of another rudder, occupation on the missile body volume is reduced, and the space utilization efficiency is improved.

Description

technical field [0001] The invention belongs to the field of weapons and equipment, and in particular relates to a control mechanism for a space link type missile rudder surface. Background technique [0002] The missile rudder rotates around the rudder axis during flight to adjust the position and attitude of the missile and generate a control force (moment) on the missile, so that the missile can adjust its flight trajectory in time to achieve the purpose of precise strike. At present, the rotation of most rudder surfaces is mainly controlled by the steering gear, and the steering gear is installed in the body of the projectile, which occupies a large volume of the projectile body. During design, the size of the projectile body must be increased to ensure the installation space of the steering gear and other related mechanisms. With the continuous development of missile technology, special requirements have been put forward for the overall size of the missile, the position...

AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to provide a space link type missile rudder surface control mechanism to solve the problem that the current steering gear takes up more volume of the projectile during placement, which can effectively save space while maintaining the existing aerodynamic shape of the projectile. The installation space can effectively reduce the occupancy of the volume of the projectile by the placement of the steering gear

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