A space linkage control mechanism for missile rudder surface

Abstract

The invention discloses a missile control surface space linkage type control mechanism to solve the problem that steering engine installation requires occupying more missile body space currently. The missile control surface space linkage type control mechanism is characterized in that each first cockpit and an adjacent second cockpit are fixed through a connecting compartment; the first cockpits are connected with first rudders; the second cockpits are connected with second rudders; a first rudder shaft fixed to one first rudder and one first cockpit form a rotation pair correspondingly; rotation blocks are fixed to the first rudder shafts; a sliding rod and a second through hole of one rotation block form a sliding pair correspondingly; a guide rail and a sliding block with a boss formed at the top form a sliding pair correspondingly; the two ends of a first connecting rod are hinged to one boss and one sliding rod correspondingly; one end of a second connecting rod and one sliding block are fixed correspondingly; a nut block fixed to the other end of each second connecting rod and a screw rod form a helical pair correspondingly; one end of each screw rod is connected with an output shaft of a second steering engine through a coupler; a second rudder shaft of each second rudder and a third through hole of the corresponding second cockpit form a rotation pair; and an output shaft of a first steering engine and one second rudder shaft are fixed correspondingly. According to the missile control surface space linkage type control mechanism, the steering engines of certain rudders are moved to the cockpits where the other rudders are located, and the size occupation of a missile body is reduced.

Description

technical field [0001] The invention belongs to the field of weapons and equipment, and in particular relates to a space linkage control mechanism for a missile rudder surface. Background technique [0002] The rudder surface of the missile rotates around the rudder axis during the 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 the 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 the design, the size of the projectile body is increased to ensure the installation space of the steering gear and other related devices. With the continuous development of missile technology, higher requirements are put forward for the overall dimensions of the missile a...

AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to solve the problem that the current steering gear takes up more space in the projectile body during installation, and to provide a space linkage control mechanism for the missile rudder surface, which can effectively save the installation space under the premise of maintaining the existing aerodynamic shape of the projectile body , thus effectively reducing the occupation of the projectile volume by the placement of the steering gear

Images