RU2762168C1 - 9m100 anti-aircraft guided missile - Google Patents

Abstract

FIELD: military technology.

SUBSTANCE: invention relates to weapons, namely anti-aircraft missiles. The missile includes wings, a warhead with a fuse, control equipment with a fiber-optic gyroscope mounted on the axis of the missile, steering mechanisms and a power source. The missile design includes three fiber-optic gyroscopes mounted on three axes of the rocket, three integrators and three-channel control equipment for the steering mechanisms of the rocket separately on three channels: roll, yaw and pitch without spinning the missile around its axis.

EFFECT: increasing the accuracy of missile guidance and ensuring maximum controllability of the missile.

1 cl

Description

The technical field to which the invention relates.

The invention relates to the field of military technology, namely to guided missiles and missiles, and can be used in the development of guided missiles and missiles.

State of the art.

Known invention "Rotating rocket" (patent GB No. 1188651, F42B 15/00, priority from 1970), which has wings, warhead with a fuse, control equipment with a gyroscope and a power source. The purpose of the gyroscope is to create a reference frame (coordinate system) on the rocket, relative to which it would be possible to measure the parameters of its movement, in particular, the angular velocity of rotation. But the presence of a mechanical gyroscope on the rocket, a structurally complex mechanism that requires a significant amount of time to bring it into operation (spinning the rotor), is its disadvantage.

This missile with varying degrees of deployment is described in:

- "Designing SAM" - M .: MAI, 1999, p. twenty;

- invention "Guided projectile", patent RU 2114383 C1, F42B 15/00, publication date: 06/27/1998;

- invention "Guided projectile", patent RU 2066832, F42B 15/00, publication date: 20.09.1996;

- invention "Guided projectile with power and control mechanism", patent US 7431237 B1, F42B 15/01, publication date: 02.10.2008.

The technical solution proposed in the invention "Rocket" (patent RU 2477444 C1, F42B 15/00, publication date 03/10/2014) can be considered as a prototype of the invention.

The essence of the invention lies in the fact that a series-connected fiber-optic gyroscope is introduced into the design of a rotating rocket containing wings, a warhead with a fuse, control equipment, steering gears and a power source, which performs the function of an angular roll sensor of the rocket and an integrator connected to the equipment management.

The disadvantages of the prototype of the invention are:

- the impossibility of controlled stabilization of the rocket along all axes, which in the prototype is carried out due to the rotation of the rocket around its axis;

- poor controllability of the rocket, associated with the resistance of a rotating rocket to control the position of its axis as a conventional gyroscope and precession of the rocket axis when its position in space changes;

- redundancy of control equipment associated with the need for a special computer to form two orthogonal reference signals - two reference voltages periodically varying with the rocket rotation frequency, shifted relative to each other by a quarter of the rocket rotation period, and the subsequent generation on their basis of commands for controlling the rocket along the course and pitch, respectively ... The control signals obtained as a result of comparison are logically added in the "exclusive OR" block, forming a signal to control the rocket steering organs. In this case, the integrator's output through a decoder is connected to two read-only memory devices (ROM), into which the values of the functions describing the shape of the reference signals when the argument changes from 0 to 2π, shifted relative to each other by π / 2, are entered with the required sampling level. As the readings of the integrator (digital adder) increase, the decoder connected to it sequentially polls the ROM cells, providing the output of the values of the functions written in them, describing the shape of the reference signals with the required accuracy, to the inputs of the comparators, where they are compared with the commands for controlling the missile along the course and pitch coming, for example, from the onboard missile radio command receiver;

- significant alternating loads on the steering mechanisms and continuous energy consumption for regular, with the rocket speed, shifting the projectile rudders to control alternately in the pitch and yaw channels;

- the limited strip of the missile control loop in the pitch and yaw channels, determined by the mechanical time constant of the rudder shift lag for control alternately in the pitch and yaw channels.

These disadvantages significantly reduce the accuracy of missile guidance, determine the impossibility of achieving a direct hit on a small target.

The task of the proposed design is to eliminate the shortcomings of the prototype, namely to maximize the controllability of the missile and, thus, to ensure high accuracy of its guidance, to achieve the possibility of direct hitting a small target.

Disclosure of the essence of the invention.

The essence of the proposed technical solution lies in the fact that in order to increase the controllability of the rocket, its design includes three fiber-optic gyroscopes, three integrators and three-channel control equipment that provides stabilization and control of the rocket steering mechanisms separately along three channels: roll, yaw and pitch without spinning the projectile around its axis.

Implementation of the invention.

The implementation of the invention is achieved by excluding two orthogonal reference signals from the composition of the missile control equipment of a special computer - two reference voltages periodically changing with the rocket rotation frequency, shifted relative to each other by a quarter of the rocket rotation period and a special computer for generating, on their basis, periodic commands for controlling the rocket along the course and pitch respectively, and the inclusion of three fiber-optic gyroscopes, three integrators and three control channels in the missile control equipment, providing stabilization and control of the rocket steering mechanisms separately in three channels: roll, yaw and pitch without spinning the projectile around the axis.

The positive effect of the proposed technical solution is:

- in a significant increase in the controllability of the missile and the associated high accuracy of the missile guidance to the target;

- significant simplification of control equipment;

- a significant reduction in the energy consumption of steering mechanisms.

Claims (1)

A rocket with wings, a warhead with a fuse, control equipment with a fiber-optic gyroscope installed along the rocket axis, steering mechanisms and a power source, characterized in that the rocket design includes three fiber-optic gyroscopes installed along the three axes of the rocket, three integrator and three-channel equipment for controlling the rocket steering mechanisms separately in three channels: roll, yaw and pitch without spinning the rocket around its axis.