Controlled missile

FIELD: weapons and ammunition.

SUBSTANCE: controlled missile includes a body, aerodynamic wings and rudders, a wiring duct arranged along the body in the vee of rudders and wings. Spread of the wings, in the vee of which the wiring duct is arranged, is less than spread of the rest wings.

EFFECT: increasing target guidance accuracy.

1 dwg


The invention relates to the field of rocket technology, in particular to the guided missiles, and can be used in different types and classes of missiles, the construction of which provides for garrote.

This component, which is essentially volume, oriented in the longitudinal direction and located outside the housing, closes the control wiring, piping and electrical wire protruding outside the main dimensions of the hull, and is widely known in aviation, space and rocket technology.

In particular, in relation to aeronautical engineering, from the patent of Russian Federation №2207968, class VS 30/00 1999 known design highly maneuverable multirole supersonic aircraft, containing the fairing, and of application No. 2008115362, class B64D 27/00, 2009 - the presence of garrote in unmanned aircraft.

The presence of garrote in aerospace engineering is also known from the patent of Russian Federation №2072949, class B64D 37/02, 1997.

In the book "I. I. Toropov - Founder and first chief designer of Gomb "Vympel". To the centenary of the birth". Publishing house "Avenir", 2007 shows the appearance of the missile of class "air-air" R-33 (page 162), R-73 (p. 161), RF-AE (p. 164, the closest analogue), X-29 (p. 274), each of which comprises a housing arranged in the housing the propulsion system, control system equipment, combat gear.In this case symmetrically arranged main airfoils - wings and rudders. Also on the body of the rocket placed the fairing, speaker for its size and protects electrocommunication from external influence.

When flying missiles with attack angles in any plane of the fairing is at an angle to the incident flow and, as a low aspect ratio wing that creates lift in all the control channels forming the parasitic cross coupling between them and, at high angles of attack, leading to a three-band instability.

The technical result, which is the claimed invention is the creation of the guided missile, the construction of which would exclude the above, introduced by the lack of fairing, i.e. significantly reduce the impact of this deficiency on the aerodynamics of the missile and the accuracy of its targeting.

Obtaining the specified technical result is achieved in that in the claimed a guided missile, comprising a housing with symmetrically arranged on it the main airfoil of the wings and rudders and fairing placed in their collapse, the wingspan, the collapse of which are placed in the fairing, is made smaller than the scale of the rest of the wings on the size, reducing the load-bearing properties of these wings on a value comparable with the value of the load-bearing properties of garrote for uravnovesena�ia its lifting force.

The invention is illustrated by figure 1, which shows a view along the axis of the missile, comprising a housing 1, symmetrically located on the housing of the aerodynamic surfaces, in particular the wings 2, 3, and placed in the camber of the wings 3, the fairing 4. Wings 3 have a lower height (wingspan) than the wings 2. The magnitude of this amplitude or the difference in height between the wings 2 and wings 3, as the value of the square of these wings is chosen in each case, given the obvious technical (structural) constraints and should provide the wings 3 reduction of the load-bearing properties, compared with wings 2, by an amount comparable with bearing properties of garrote, to neutralize emerging from garrote moment relative to the longitudinal axis of the rocket.

Thus, the proposed design implementation of the wings in flight of the missile at high angles of attack and control in the plane of the wings to balance the moment generated from garrote 4, which in turn will eliminate the parasitic aerodynamic link between the control channels and channel instability.

A guided missile, comprising a housing with symmetrically placed on it the main controls - aerodynamic wings and rudders and a fairing placed along the body in the breakdown of the rudders and wings, characterized in that the wingspan, in the collapse �which placed the fairing, is made smaller than the scale of the rest of the wings, reducing their load-bearing properties by an amount comparable to the magnitude of the load-bearing properties of garrote.


Same patents:

FIELD: weapons and ammunition.

SUBSTANCE: two-stage rolling cruise missile (CM) with five degrees of freedom of spatial movement includes a housing stabilised as to the sixth degree of freedom by rotation in the form of a rotation figure with wings, rudders and an active aerodynamic nozzle, a single-duct control system, a steering gear, a detachable launching accelerator with an axial turbo-jet engine with a gas-dynamic nozzle, a cruise stage with an n duct system of formation of lift capacity in a rotation mode and a small-size disposable turbo-jet engine with a folded air intake, and a self-guidance head.

EFFECT: simpler control and stabilisation of a cruise missile, lower weight and dimensions of the cruise missile.

2 dwg

Guided missile // 2542692

FIELD: weapons and ammunition.

SUBSTANCE: guided missile is made based on canard configuration. The missile with a single-channel control system and rotating in roll direction. The missile contains a main propulsion system, a steering wheel in one plane and a stabiliser with the location of fixed bearing surfaces by X-shaped pattern relating to the plane of the steering wheel console. At the head part of the housing of the guided missile in a plane perpendicular to the plane of the steering wheel console, the pylons are mounted. The fixed consoles of the pylons in a transverse plane are located at an angle of 45-60 degrees relative the consoles of the stabiliser. The consoles of the pylon on the geometric shape in the plan are made like consoles of the steering wheel with the ratio of areas of the pylon and the steering wheel as 0.5-1.0. The ratio of areas of the console of the pylon and the console of the stabiliser are made as 0.05-0.1.

EFFECT: improved control efficiency, improved ballistic and dynamic properties of the missile.

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FIELD: weapons and ammunition.

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EFFECT: invention enables to improve the efficiency of the guided missile.

3 cl, 4 dwg

FIELD: weapons and ammunition.

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EFFECT: improvement of accuracy of projectile shooting.

4 cl, 2 dwg

Guided missile // 2540903

FIELD: weapons and ammunition.

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EFFECT: decreased length and weight, higher reliability and combat efficiency.

3 cl, 4 dwg

FIELD: weapons and ammunition.

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4 cl, 4 dwg

Controlled missile // 2539709

FIELD: weapons and ammunition.

SUBSTANCE: invention relates to missile engineering, namely to controlled missiles. A controlled missile includes a housing with the main control elements symmetrically arranged on it - aerodynamic surfaces and rudders, as well as a wire duct. The latter is arranged along the housing in the incline of rudders. An aerodynamic surface is additionally installed on the housing, on the side opposite to the wire duct.

EFFECT: improvement of aerodynamics of missile flight and improvement of its target guidance accuracy.

2 cl, 1 dwg

Guided bullet // 2538881

FIELD: weapons and ammunition.

SUBSTANCE: guided bullet comprises a balancing weight, stabilising elements, aerodynamic control bodies, the drive unit of control bodies, and the beam control system which comprises a photoreceiver and onboard equipment. The balancing weight is used as the warhead of kinetic action. The warhead is made in the form of armour-piercing rod. The stabilising elements are made in the form of two consoles and are arranged in a plane passing through the longitudinal axis of the guided bullet. The aerodynamic control bodies are made in the form of a pair of all-moving aerodynamic rudders arranged on one axis located behind the stabilising elements in the direction of motion in a plane passing through the longitudinal axis of the guided bullet and perpendicular plane of location of the stabilising elements. In the guided bullet an on-board power source is located, made with the ability to initiate at the time of firing.

EFFECT: increase in the firing range.

10 cl, 7 dwg

FIELD: weapons and ammunition.

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EFFECT: increase in the maximum range of the rocket flight.

4 cl, 9 dwg

Guided shell // 2537357

FIELD: weapons and ammunition.

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EFFECT: increase in efficiency of the shell operation.

2 cl, 6 dwg

FIELD: weapons and ammunition.

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EFFECT: improving missile acceleration speed for increase of firing distance and missile wounding power.

12 cl, 4 dwg

FIELD: aircraft engineering.

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4 cl, 7 dwg

FIELD: weapons and ammunition.

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3 cl, 3 dwg

FIELD: weapons and ammunition.

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EFFECT: improved accuracy of angular stabilisation.

2 cl, 1 dwg

FIELD: weapons and ammunition.

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EFFECT: higher efficiency of common rounds with smooth cylindrical parts.

11 cl, 6 dwg

FIELD: weapons and ammunition.

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EFFECT: optimised dimensional characteristics of aerofoil in the folded position when ensuring an unfolding force under conditions of a strong approach flow and higher reliability, possibility to fold repeatedly, for instance, during ground tests of rocket systems.

4 cl, 3 dwg

FIELD: weapons and ammunition.

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EFFECT: improving accuracy and enlarging the firing distance of artillery projectiles.

2 dwg

FIELD: weapons and ammunition.

SUBSTANCE: device comprises a sensor of angular deviations with a sensitive element, a unit of signals conversion and an actuator. The sensitive element is made in the form of a spherical float equipped with a permanent magnet and placed in a spherical chamber filled with liquid. The sensitive element is mechanically connected to a drive, signal and reference windings. The spherical chamber is made inside the rotor, having the shape of the cylinder with end surfaces in the form of a truncated cone. The diameter of the base of the truncated cone equals the diameter of the cylinder, the diameter of the truncated cone and its height are determined on the basis of the ratios d/D=0.4-0.6 and h/D=0.3-0.5, where d - diameter of the truncated cone, h - height of the truncated cone, D - rotor diameter. The drive is made in the form of an electric DC motor with excitation from a permanent magnet installed inside a hollow non-magnet anchor. The drive is electrically connected to a unit of signals conversion.

EFFECT: simplified design and increased operational reliability of the device.

2 cl, 2 dwg

Controlled shell // 2411444

FIELD: weapons and ammunition.

SUBSTANCE: shell comprises body, closing stabiliser, transceiving device and tray. Closing stabiliser is fixed on body with shear pin. Tray includes a tilter, fixed with a clearance on its back end. Tray is arranged in the form of two coaxial equidistant rings fixed to each other along internal surfaces by shell. Rings with shell form through asymmetric hole with segment cheek, height of which makes 0.25…0.35 of external diametre of tilter. Coaxial equidistant rings form a pocket open from external side, width of which makes 0.05…0.15 of external diametre of tilter.

EFFECT: improved reliability of target killing.

4 dwg

FIELD: weapons and ammunition.

SUBSTANCE: method is based on reduction of impact of flutter oscillations. Shell oscillation damping in action section of the trajectory is performed with the complex of devices: reduction (damping) device of twisting and bending oscillations of JVFS shell, synchronising device of rotation of head and tail parts of JVFS shell and balancing device of centre of gravity of JVFS shell.

EFFECT: reducing the probability of reduction of JVFS shells in flight, and improving shooting accuracy.

8 dwg

Jet projectile // 2244245

FIELD: salvo-fire system jet projectiles provided mainly with separable warheads.

SUBSTANCE: the jet projectile is provided with an aerodynamic warhead destabilizer made in the form of a shoulder with a height of 0.04 to 0.16 of the caliber and an area of cross-section projection onto the plane perpendicular to the projectile longitudinal axis not exceeding 0.002 of the total area of the blades of the aerodynamic stabilizer, the shoulder is positioned on the control system unit open to the projectile nose tip. The warhead aerodynamic destabilizer is removed from the projectile center of inertia at a distance not exceeding 1.75 of the distance from the projectile center of inertia to the aerodynamic stabilizer.

EFFECT: enhanced fighting efficiency of the projectile.

3 dwg