Canard configuration missile general structure with roll and despun stabilizing function

Abstract

The present invention provides a canard configuration missile general structure with a roll and despun stabilizing function, comprising a front section (1) and a rear section (2); and the front section (1) and the rear section (2) are connected by a roll and despun stabilizing device. The canard configuration missile general structure divides a missile into the front section and the rear section,a canard system is mounted at the front section, the rear section rotates around the longitudinal axis by an inclined tail under the aerodynamic action, and the front section realizes the roll stabilizing by the roll and despun stabilizing control, which solves the roll channel control problem caused by the canard wash of the canard configuration missile. At that same time, for the canard system,only pitch motion control and yaw motion control are needed and can be realized only by two sets of motor servo systems, so that the design of the canard system is greatly simplified, and the requirement for the structure space and the development cost are reduced. A guidance assembly is installed in the front section of the despun stabilized missile body, so that the disadvantageous influence oflarge roll angular velocity on the system stable imaging is avoided.

Description

technical field [0001] The invention relates to the technical field of missile frame design, in particular to the general frame of a canard layout missile with roll derotation stability. In particular, it relates to the overall design framework of a canard aerodynamic layout missile. Background technique [0002] The canard aerodynamic layout is an important aerodynamic layout method adopted by various missile weapons. Its control actuator is located in the front section of the missile body, which is conducive to the overall structural layout and simplified design of the missile. Compared with the normal layout, the canard rudder The response speed is fast, the rudder deflection produces positive lift, and the control efficiency is higher. Nevertheless, the roll control efficiency of the canard rudder is low, and the rudder surface wash acts on the tail of the missile body to generate a disturbance moment, which may cause the roll control to be ineffective, which brings gre...

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Problems solved by technology

[0006] The above-mentioned schemes all have certain deficiencies. Although the scheme (1) can simplify the control system, the guidance and control components must bear a large roll angular velocity; The layout is difficult when the space is limited; scheme (3) the empennage has a large size and is not easy to fold, which is not conducive to cylindrical storage and launch

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