RU2502042C1 - Guided jet projectile - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: proposed projectile comprises control and booster units. Control unit is composed of two modules: nose module with projectile controls and tail module. Control unit modules are interconnected by ball hinge with pin aligned with booster lengthwise axis. Control unit tail module is integrated with booster unit. Ball hinge pin rigidly coupled with booster supports torque motor rotor. Motor stator is rigidly coupled with control unit nose module case. Nose module outer surface accommodates two aerodynamic fins rigidly connected with nose module outer surface. Said fins are arranged at fixed angle to control module lengthwise axis.

EFFECT: simplified design, higher efficiency of control.

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Description

The present invention relates to the field of military equipment, in particular to guided missiles (URS) unstabilized in roll angle.

An analogue of this technical solution is a guided rotating projectile (Patent RU No. 2438095 of 12/27/2011). The projectile contains electronic control equipment, controls made in the form of aerodynamic rudders, and sensitive elements of the deviation of the projectile from a given trajectory, which are arranged on the basis of two micromechanical gyroscopes (MMGs) placed on two mutually perpendicular circuit boards with radio elements installed on them, providing signal combination MMG entering the electronic control equipment, with its own signals that go to the controls. The boards are fixed on a common base mounted perpendicular to the longitudinal axis of the projectile X so that the MMG sensitive axes are perpendicular to each other and aligned with the respective transverse axes Y and Z of the projectile, the base being rotated in the direction of rotation of the projectile relative to the aerodynamic rudders at an angle equivalent to the formation time commands for governing bodies. Improves accuracy and increases the range of artillery shells

The disadvantage of this missile is the decrease in its accuracy with increasing flight time, due to cumulative errors caused by the rotation (together with the shell of the projectile) of the sensing elements that determine the orientation and navigation of the projectile on the trajectory.

The device is implemented in the way the URS functions (Patent RU No. 2164657 of 03/27/2001). The URS is launched towards the target along the standard ballistic trajectory (for a specific homing head (GOS)) (including from a moving base and along a moving target). When approaching the target, the GOS scans the affected area, selects the target of the attack and goes into homing mode on the target. Coordination of the dynamic characteristics (speed) of the control drives and the geometry of the aerodynamic steering wheels (gas-dynamic control performance) of the URS with the capabilities of a particular type of GOS, inertial and aerodynamic parameters of the PC is done (with the aim of eliminating the modifications of the regular uncontrolled PCs) solely by varying the design and layout features of the control unit modules (UB). A fundamentally important point is the stabilization of the nose module UB. It should be noted that the use of a ballistic type PC with stabilizing roll rotation within the framework of this technical proposal makes it possible to exclude expensive and complicated inertial navigation systems from on-board control equipment that are mandatory for "non-ballistic" aircraft (which do not have a long so-called " passive "part of the flight path up to the zone of inclusion of the GOS).

The disadvantage of the prototype is the complexity of the execution and the operating conditions of the control drives for aerodynamic (or other) rudders, two pairs of which must provide the necessary values of the course and pitch angles while maintaining a zero roll angle.

The technical objective of this solution is to simplify the design and increase the combat effectiveness of missile control by expanding the range of flight ranges, increasing the effectiveness of the action in the target area.

The technical task is solved as follows. URS includes control and overclocking blocks, and the control block is made in the form of two modules: a bow with PC controls, and a tail. These modules are interconnected by means of a cylindrical hinge with an axis of rotation coinciding with the longitudinal axis of the booster unit, while the tail module of the control unit is made as a single structural unit with the booster unit; on the axis of the cylindrical hinge (rigidly connected to the booster block) is the rotor of the electric torque motor, the stator of which is rigidly connected to the body of the nose module of the control unit (control module); on the outer surface of the nose module of the control unit (control module) there is one pair of aerodynamic rudders rigidly connected to the specified surface (without the possibility of rotation relative to the specified surface), mounted at a fixed angle to the longitudinal axis of the control module.

The invention is illustrated by graphic material.

Figure 1 shows the design of the URS.

Skid-mounted stabilizers 2 are located on the housing 1 (the booster unit with the warhead). The housing 1 is made as a single structural unit with the tail module of the control unit, which is a shaft 3 of a cylindrical hinge, the axis of rotation of which coincides with the longitudinal axis of the housing 1. On the shaft 3 in bearings 4 mounted nose module of the control unit (control module) 5. In the housing 6 of which is installed an electric torque motor 7, which includes:

- rotor 8, rigidly connected with the shaft 3;

- stator 9, rigidly connected with the housing 6;

- angle sensors 10, determining the relative position of the rotor 8 and the stator 9.

The chassis 11 is rigidly attached to the housing 6 of the control module 5, on which, in turn, are attached:

- one pair of stationary relative to the control module 5 rudders 12, rotated relative to the longitudinal axis of the projectile by a fixed angle α, the value of which, depending on the type of URS, can lie within 6 ° ... 14 °;

- power source 13;

- flight information loading unit 14;

- roll control unit 15;

- flight control unit 16;

- block navigation and orientation system 17, the longitudinal axis of which coincides with the longitudinal axis of the projectile containing a block of micromechanical sensitive elements and a satellite navigation system.

The device operates as follows. When starting the URS, the housing 1 begins to rotate relative to its longitudinal axis due to sliding along the screw guide of the starting device (launch container). In flight, the rotational speed of the URS can vary due to tangential forces caused by skewed stabilizers 2. The specified rotation due to the friction forces acting in the bearings 4 is transmitted to the control module 5. As a result, the control module 5 begins to rotate relative to the longitudinal axis of the projectile. The deviation of module 5 from a predetermined (relative to the vertical) position (not necessarily zero) is fixed by the navigation and orientation system unit 17 and fed to the input of flight control unit 16. Flight control unit 16, taking into account the data received from the flight information loading unit 14, forms a command the signal supplied to the input of the roll control unit 15. In accordance with the incoming commands and the signal from the angle sensor 10, the roll control unit 15 supplies the necessary voltage to the stator 9 of the electric torque motor 7. In result occurs electromagnetic torque acting on the rotor 8, the control unit 5 returns to a predetermined position.

If it is necessary to change (correct) the flight path of the URS at the heading and / or altitude, the flight control unit 16, taking into account the data received from the flight information loading unit 14, and data on the current coordinates of the URS coming from the navigation and orientation system block 17, generates the corresponding command signals. In accordance with the incoming commands and the signal from the angle sensor 10, the roll control unit 15 supplies the necessary voltage to the stator 9 of the electric torque motor 7. As a result, an electromagnetic moment acts on the rotor 8, which rotates the control module 5 by a predetermined angle, which, in its in turn, changes the direction of the rudder lift vector relative to the axes of the coordinate system associated with the Earth. Thus, when the control module is rotated relative to its longitudinal axis by angles that lie within the range of 0 ° ... ± 90 °, the URS is controlled along the course, and when rotated through an angle of 180 ° - in height, up to the URS verticalization. This technical solution allows you to:

- to simplify the design of the URS by replacing two pairs of steering wheel drives (or other controls) with one pair of fixed wheels (or other controls) and an electric torque motor;

- increase the flight range of the URS by implementing the subplanning mode, due to the fixed angle of the rudders relative to the longitudinal axis of the URS;

- increase the effectiveness of the URS in the target area, due to its verticalization.

Claims (1)

A guided missile, including a control and booster blocks, the control block being made in the form of two modules: a bow with the controls of a rocket and a tail, while the modules are interconnected by a cylindrical hinge with an axis of rotation coinciding with the longitudinal axis of the booster, different the fact that the tail module of the control unit is made as a single structural unit with an overclocking unit; on the axis of the cylindrical hinge (rigidly connected to the booster block) is the rotor of the electric torque motor, the stator of which is rigidly connected to the body of the nose module of the control unit (control module); on the outer surface of the nose module of the control unit (control module) there is one pair of aerodynamic rudders rigidly connected to the specified surface (without the possibility of rotation relative to the specified surface), mounted at a fixed angle to the longitudinal axis of the control module.