RU2032139C1 - Guided missile with rotating warhead - Google Patents

Abstract

FIELD: ammunition. SUBSTANCE: missile consists of front and rear parts coupled by means of a detachable joint. The rear part has a body, engine and stabilizer. The front part has a body and a unit mounted on bearings inside the body and stabilized in the trajectory plane. The unit has an orientation system, deflection engine and fragmentation warhead with ready striking members. High altitude explosion of missile occurs due to a noncontact fuse of the missile which makes it possible a sequential starting of deflection engine and warhead initiating unit at specified altitudes above earth. For low altitude explosion the missile has a remote fuse providing the deflection engine starting at a specified trajectory point. Besides the missile has a noncontact fuse providing the starting of warhead initiating unit at a specified altitude above earth. EFFECT: enhanced efficiency. 3 cl, 4 dwg

Description

 The invention relates to ammunition, and more particularly to fragmentation ammunition intended to engage ground targets. Known fragmentation ammunition for creating a circular field of destruction [1], also known is a projectile for combating ground targets, containing a fragmentation warhead with ready-to-use striking elements placed on the surface of the charge [2].

 Closest to the proposed one is a guided cumulative projectile of pan-target action [3]. The projectile is rotating and has a housing consisting of two parts with a detachable connection. A jet engine and stabilizers are located at the rear, a cumulative warhead with an explosive charge, a control system, an orientation system in the plane of the trajectory, and a jet do-it-yourself engine are located at the front. The orientation system and the engine turn are placed in the block turn. The do-it-yourself unit is placed in front of the bearings, and as a result of the orientation system, the axis of the do-it-yourself engine is aligned with the trajectory during the entire flight.

 The main action of this shell is cumulative cumulative. When using a warhead as a fragmentation fragment with a circular field of destruction, when detonating at a high altitude, a significant unimpeded space arises under the discontinuity point, and when striving to realize a discontinuity at a low altitude due to the terrain and the dispersion of the trajectory in height and time of operation of the remote fuse, it is possible to stick the projectile into ground to break.

 The task of the invention is the elimination of these disadvantages.

 This is achieved by the fact that in a guided projectile with a rotary warhead, which consists of a front and rear parts connected by a detachable or destructible connection, the back part comprising a housing, an engine and a stabilizer, and the front housing, a warhead with an initiation unit and stabilized in the plane of the trajectory, a block placed in a housing on bearings and containing an orientation system and an engine for turning, for the implementation of high-altitude detonation, the warhead is made fragmentation containing a charge in the form of a truncated cone Conjugate base with small hemisphere, and arranged on the surface ready submunitions, and is disposed in the front housing forward hemisphere, the projectile is provided with a proximity fuse with a motor providing sequential resetting and switching node initiation of the warhead at a predetermined height above the ground.

 To realize the warhead rupture at low altitude in the proposed guided projectile, the warhead is made of fragmentation with ready-made striking elements placed on the surface of the charge, while the projectile is equipped with a remote fuse to enable the turn-on engine at a given point on the trajectory and a non-contact fuse to enable the initiation unit of the warhead at a given height above the surface of the earth.

 In FIG. 1 shows a diagram of a projectile with a high-altitude discontinuity on the trajectory (option I); in FIG. 2 - scheme of the projectile with a forced reduction of the rotary part to a small fixed height (II option); figure 3 - the effect of a projectile with a high-altitude gap on the trajectory; figure 4 - the effect of the projectile with a forced reduction to a small fixed height.

 The guided projectile consists of a rear 1 and front 2 parts connected by a detachable or destructible connection 3. A jet engine 4 and stabilizers 5 are placed at the rear of the projectile. At the front of the projectile is a fragmentation warhead 6 with a shell of ready-made striking elements 7 and an explosive charge 8 and initiation node 9. Finished damaging elements are made of steel or heavy alloys, for example, based on tungsten.

 In the embodiment shown in Fig. 1 and intended for high-altitude rupture, the charge of the warhead is made in the form of a truncated cone, paired with a small base with a hemisphere and located in front of the projectile behind the fairing 10 hemisphere forward. The initiation unit 9 is located at the rear end of the warhead.

 In the embodiment shown in FIG. 2 and intended for breaking at a low height, the fragmentation warhead is made in the form of a cylinder or in the form of a body of revolution with flat ends and a curved generatrix, both concave and convex. The shape of the generatrix, the number and location of detonators in the initiation node are determined depending on the required value of the meridional expansion angle Δ φ (Fig. 4) and the distribution law of the striking elements in this angle, determined by the statistical dispersion of the angle of deviation of the warhead axis from the vertical at the time of detonation and the height of the blasting , type of target and other conditions.

 The dovor block 11 is placed in front of the projectile on bearings 12. The dovor block includes an orientation system 13 and a dovot engine 14. The latter is made in the form of a jet engine, as is done in the closest analogue and shown in Fig. 1, or in the form of a barrel 15 with a powder charge 16 located in it and a shot ballast mass 17 (Fig. 2). In the embodiment of FIG. 1, the recoil engine is electrically or pyrotechnically connected to a non-contact (temporary) fuse 18. A retarder 20 is installed between the ignitor of the recoil engine 19 and the initiation unit 9. In the embodiment of FIG. 2, the projectile is equipped with a remote fuse (not shown), and In the front part of the fairing, a non-contact fuse 21 of an altimeter type, for example, radar or optical, is installed. For guided projectiles with guidance on the target, the projectile may include a guidance system 22 and aerodynamic rudders 23 (figure 2).

 The action of the projectile with a high-altitude gap is shown in Fig. 3 (the case of the horizontal trajectory of the projectile characteristic of cruise missiles with a marching engine is considered). At point A, at a predetermined range U to the target, a non-contact (temporary) fuse gives a signal to turn on the dovot engine. Under the influence of an engine impulse, the front of the projectile is separated from the rear along the plane of the connector. Since the axis of the dovor engine is offset by a distance R from the center of mass of the rotary part, it receives translational and rotational motion. The selection of the values of the pulse I and shoulder R is carried out in such a way that the trajectory is small compared with the height of flight N. After the estimated time, the moderator 20 gives a command to undermine the warhead. Due to the spherical conical shape of the warhead and the presence of declination of the fragmentation flow provided by the bottom position of the initiation unit 9, a continuous lesion field is created on the surface of the earth, in the central part of which also lesions in the trenches and embankments are provided.

, ω =

где R, j - плечо приложения импульса относительно центра масс передней части снаряда и ее момент инерции соответственно.In FIG. 4 shows the effect of a projectile made according to the scheme of FIG. 2, with a forced reduction by a predetermined height of H ₂ . The general case of the projectile motion at an angle θ ₁ to the surface is considered. The start-up engine at point A is switched on by a remote fuse. The translational lateral velocity v _b and the angular velocity ω obtained by the action of momentum I are determined by the relations
v _In =

, ω =

where R, j is the shoulder of the impulse application relative to the center of mass of the front of the projectile and its moment of inertia, respectively.

The vertical component of the projectile velocity is defined as
v _H = v _B cos θ ₁ + V ₁ sin θ ₁ .

Перемещение вдоль поверхности земли составляет
v =

Время, за которое произойдет вертикальное перемещение на расстояние Н₁-Н_2, определяется соотношением
t = (H₁-H₂)/v_Н, а время доворота на угол

- θ₁
t=

-

/ω
Из условия равенства этих времен определяется необходимая величина импульса
I =

Включение узла инициирования боевой части обеспечивается неконтактным взрывателем на заданной высоте над поверхностью земли.After applying the pulse, the front of the projectile moves at an angle θ ₂ to the surface, and
θ ₂ = θ ₁ + θ, θ = arctg

Moving along the surface of the earth is
v =

The time during which there will be a vertical movement at a distance of H ₁ -H _{2 is} determined by the ratio
t = (H ₁ -H ₂ ) / v _N , and the turn-in time by an angle

- θ ₁
t =

-

/ ω
From the condition of equality of these times, the necessary momentum is determined
I =

The inclusion of the unit initiating the warhead is provided by a non-contact fuse at a given height above the ground.

Claims (3)

 CONTROLLED APPARATUS WITH A TURNING BATTLE PART (OPTIONS).  1. A guided projectile with a rotary warhead, consisting of a front and rear parts connected by a detachable or destructible connection, the rear part comprising a housing, an engine and a stabilizer, and the front housing, a warhead with an initiation unit and a block stabilized in the plane of the trajectory, placed in a housing on bearings and containing an orientation system and an engine turnaround, characterized in that the warhead is made fragmentation, containing a charge in the form of a truncated cone, paired with a small base with hemispheres minutes, and arranged on the surface ready submunitions, and is disposed in the front housing forward hemisphere, the projectile is provided with a proximity fuse with a motor providing sequential resetting and switching node initiation of the warhead at a predetermined height above the ground.  2. A guided projectile with a rotary warhead, consisting of a front and rear parts connected by a detachable or destructible connection, while the rear part contains a housing, an engine and a stabilizer, and the front includes a housing, a warhead with an initiation unit and a block stabilized in the plane of the trajectory, placed in a housing on bearings and containing an orientation system and a turnaround engine, characterized in that the warhead is made fragmentation with ready-made striking elements placed on the surface of the charge, while the projectile equipped with a remote fuse to ensure that the turn-on engine is turned on at a given point on the trajectory and a non-contact fuse to ensure that the warhead initiation unit is turned on at a predetermined height above the ground.

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