RU2164657C1 - Guided missile - Google Patents

Abstract

FIELD: high-accuracy guided missile weaponry. SUBSTANCE: the guided missile has control and booster units. The control unit is made in the form of a nose module with a homing head and missile controls and a real module rigidly attached to the nose cone of the booster unit by the mounting seat. The modules are interconnected by a cylindrical hinge joint, whose axis of rotation coincides with the longitudinal axis of the booster unit. EFFECT: expanded field of combat employment of guided missiles up to destruction of movable targets. 6 cl, 3 dwg

Description

 The invention relates to military equipment, mainly to complexes of guided missile (URO) and high-precision missile (VTRO) weapons.

 The URO (VTR) complexes are known that provide target destruction with guided missiles (UR) and guided missiles (UPC) - see, for example, S.A. Golovin, Yu.G. Sizov, A.L. Skokov, L.L. Khundanov "Precision weapons and the fight against them", M., publishing house "V.P.K.", 1996.

 Ballistic URs (URS) equipped with homing heads (GOS) are known for high-precision destruction of ground targets, for example, the American Pershing II missile (see, for example, “Technical Information” TsAGI N 7-8, 1986, p. 10 -11) is the closest analogue.

Both the prototype (a missile for high-precision destruction of targets of the class "ground" - "ground""PershingII"), and a guided missile according to the proposed technical solution have a number of common features, the most significant of which are:
- ballistic flight path to the target;
- the presence of a homing head, controls and on-board equipment for high-precision target destruction in the face of a complex masking background of the earth's surface at the final stage of a passive section of the flight path;
- placement of GOS and controls on the head unit, which provides correction of the flight path of the rocket.

 However, the Pershing II VTRO complex cannot hit mobile targets, which is related to the features ("steepness") of the ballistic trajectory of the rocket and the use of a correlation - extreme radar seeker, in addition to the technical implementation and operation of the complex (including the preparation and commissioning of the flight mission) differ in complexity and extremely high cost (for example, due to the use of a high-precision onboard inertial navigation system, preparation of reference sites standards (landmarks) for various heights GOS survey, the availability of specialized systems: real-time data processing, antenna-feeder devices, radio altimeters, etc.).

 The aim of the invention is the expansion of the combat use of ballistic missile defense systems to the point of defeating mobile ground (surface) objects, as well as reducing the cost of the missile defense system (VTRO) by creating missile defense systems based on existing unguided missiles (missiles) that realize flight to the target along a ballistic trajectory with stabilizing roll roll (for example, the creation of URS based on rockets of multiple launch rocket systems).

 This goal is achieved by the fact that the ballistic URS, including the control (UB) and booster (RB) blocks, is equipped with UB in the form of 2 modules: bow with on-board equipment (including GOS) and control (aerodynamic, gas-dynamic) controls of the URS - and tail, which, on the one hand, is rigidly attached to the head of the RB, on the other hand, is connected to the nose module of the UB through a cylindrical hinge with an axis of rotation coinciding with the longitudinal axis of the RB. In addition, in order to use a standard unguided rocket as an RB, to improve anti-missile characteristics in case of defeat of protected targets such as “ship”, “mobile launcher”, “tank”, etc., the landing socket of the UB tail module for mounting on the RB is carried out in in the form of a cup with a conformal recess (for the bypass of the head of the RB), on which at least two bearings are fixed (for example, angular contact roller bearings), in addition, the URS can be equipped with a striker with a sheared shoulder, azmeschennym axially receiving hole tail unit UB (cutting the bead and moving the hammer occurs at the moment of impact with the target); an anti-rheumatic tide (for example, an anti-rheumatic ring or “fangs”) with a diameter smaller than the diameter of the nose module of the UB (in order to cover the tide from the aerodynamic velocity head) is made on the outer surface of the landing nest. Additionally, in order to exclude modifications to regular unguided missiles (PCs) used as RBs, the tail module of the UB was mounted on the head of the RB (i.e. PC) by gluing, and in the body of the landing seat for preliminary mechanical fixation during gluing, and also, if necessary, through threaded holes are made for quick and easy removal of UB from the RB (if steel is used as a seat; if promising light alloys and high-strength plastics are used for this purpose New holes can be made in steel bushings pressed into the base material). Installation and dismantling of UB on RB (PC) is carried out using removable levers screwed into threaded holes.

The general structural layout of the URS for the proposed technical solution is presented in FIG. 1. Accepted notation:
1 - nose module UB;
2 - tail module UB;
3 - booster block (for example, on the basis of solid rocket multiple launch rocket);
4 - cylindrical hinge.

 The concept of installing a variety of optical, radio engineering and combined GOS (using, as a rule, inertial axes in the formation of a given viewing sector) on regular uncontrolled ballistic PCs, including stabilized by rotation (typical for most systems in service), it allows, in principle, to create various combinations (modifications) of VTRO using caliber, sub-caliber and super-caliber head parts (UB) for PC (RB) from existing arsenals, while the feasibility of of another variant of URS is relatively simple and fast determined by full-scale mining (firing) with simplified overall weight models of UB.

A structural diagram of the area of the cylindrical hinge connecting the UB modules is shown in FIG. 2 (universal mounting slot for any type of PC) and FIG. 3 (simplified landing socket mainly for light subcaliber nose modules UB). Here:
1 - nose module UB;
2 - tail module UB (including a glass with a conformal recess, passes into the axial cantilever tube);
3 - booster block;
4 - a cylindrical hinge (bearing pair);
5 - union nut (mounting option);
6 - sleeve based (option fasteners);
7 - installation case (element of the nose module UB);
8 - explosive warhead PC;
9 - head fuse (in Fig. 2 - standard for PC; in Fig. 3 - for the option of "instant" detonation on an obstacle with a fire channel in the body of the axial cantilever tube);
10 - anti-rifle "fang" (element of the landing socket of the tail module UB);
11 - firing pin;
12 - cut flange (element of the striker body);
13 - latch - aerodynamic screen (hood) in a specialized threaded hole (layout option).

 The functioning (work) of the device according to the proposed technical solution is as follows. The URS is launched towards the target along the standard (for a specific GOS) ballistic trajectory (including from the moving base and along the 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 regular uncontrolled PCs) EXCLUSIVELY by varying the design and layout features of the UB modules. A fundamentally important point is the stabilization of the nose module of the UB, for example, relative to the vertical line, which allows the use of traditional algorithms for controlling the antenna system of the GOS and, accordingly, allows the use of previously created warheads of missiles, shells and bombs with homing systems with virtually no change in their mathematical software. 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 proposed structural scheme of the zone of the cylindrical hinge (see Fig. 2) allows the use of a standard PC head fuse when varying for a particular URS modification with the time to slow the detonation of the warhead (for example, when hitting targets like “ship” to enhance a high explosive incendiary effect). This is ensured by a change in the length of the striker (pos. 11), the movement of which inside the cantilever tube begins when the forward-lying elements of the URS deform at the moment it hits the obstacle (target) with the corresponding loading of the striker base up to the cutting of the collar (pos. 12). It should be noted that the launch and flight overloads of the URS do not lead to the cutting of the shoulder and premature detonation of the warhead.

 In some cases (for example, for small-sized lightweight seekers and when organizing the so-called “instant” blasting on an obstacle), it is advisable to simplify the UB tail module scheme by eliminating the “conformal” landing seat and the anti-ricochet ring (“fangs”), in this version the tail module of the UB is transformed into an axial cantilever tube, which is screwed into the place of the head fuse PC (with the corresponding placement of the head fuse of the URS in another place of the UB). In order to ensure a predetermined heating of the cantilever pipe and at the same time ensure the thrust bearing (relative to the flight direction) of the bearing, the “smooth” part of the pipe is separated from the screw threaded sleeve, for example, by an annular thickening (thrust flange, collar) with a sealing gasket. In other words, the part of the tail module of the UB that is stationary relative to the body of the RB can be modified depending on various design and layout considerations for various versions of the head parts and unmanaged PCs adopted as RB.

 Technical and economic assessments of the creation of VTRO complexes on the basis of ALREADY MANUFACTURED uncontrolled ballistic PCs and warheads with GOS, as proposed in the presented technical solution, indicate the possibility of a qualitative increase in the power of missile defense systems with minimal (at a fraction of a percent of the full-scale development of specialized missile defense systems with commensurate level of characteristics) costs. It seems that, taking into account the criterion of "cost - effectiveness", URO complexes based on the claimed technical solutions can make up the most numerous class of VTR in the near future.

Claims (6)

 1. A guided missile, including a control and booster blocks, characterized in that the control block is made in the form of two modules: a nose with a homing head and rocket controls, and a tail, rigidly fixed by a landing jack on the head of the booster, These modules are connected by means of a cylindrical hinge with an axis of rotation coinciding with the longitudinal axis of the upper stage.  2. Guided missile according to claim 1, characterized in that the landing socket of the tail module of the control unit for mounting on the head of the booster unit is made in the form of a glass with a conformal recess, on which at least two bearings are fixed.  3. A guided missile according to claims 1 and 2, characterized in that it is equipped with a striker with a cut-off shoulder located along the axis of the landing socket of the tail module of the control unit.  4. A guided missile according to claims 1 and 2, characterized in that on the outer surface of the landing nest an anti-rheumatic tide is made that does not protrude beyond the dimensions of the nose module of the control unit.  5. A guided missile according to claims 1 and 2, characterized in that the tail module of the control unit is fixed by gluing on the head of the booster block, and through the body of the seat socket there are through threaded holes for mechanical locks and removable levers for mounting and dismounting the control block on the booster block.  6. Guided missile according to claim 1, characterized in that the landing socket of the tail module of the control unit for mounting on the head of the booster unit is equipped with a screw threaded sleeve placed on the seat.

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