RU2151370C1 - Method for destruction of moving target by guided projectile with active guidance system and pre-acceleration engine - Google Patents

Abstract

FIELD: rocketry, in particular, homing projectiles with a rocket or artillery launching. SUBSTANCE: use is made of a combination fire trajectory, including the ballistic and grazing sections, with starting of the pre-acceleration engine, in one case - according to the data of the homing head, and in the other case-according to the preliminary computed command from the on-board control system. Selection of the respective criterion of engine actuation depends on the type of the target to be destructed. EFFECT: expanded fire capabilities of complexes for destruction of high-speed sea targets and provided maximum target approach speeds within the range of fire. 4 dwg, 2 tbl

Description

 The invention relates to the field of rocketry, and more particularly to homing missiles of the ship-to-ship and shore-to-ship class, designed to deal mainly with high-speed maneuverable naval targets.

A feature of firing at targets such as a missile boat, corvette, hydrofoil and hovercraft is:
1. A wide range of distances for possible use: from the minimum "dead zone" - to the maximum range determined by the "energy potential" of weapons, as well as the availability of firing target designation (TS).

 2. The large value of the zone of the probable target position (HCV) relative to the coordinates according to the control data, determined by the "departure" of the target ship during prelaunch weapons and delivery of weapons to the point of use of autonomous target search means.

 Typical anti-ship weapons targets also include larger, but less high-speed, ships of the “transport”, “tanker” class and stationary radio-contrast objects such as port facilities and floating platforms.

 The main means of combating the above targets at distances of up to 40-50 km and more are homing tactical anti-ship cruise missiles (ASM) such as Sea Killer (Italy), Cormoran (Germany), Rb-04 (Sweden), "ASM-1" (Japan), "C-801" (PRC), etc. Their combat use is provided, as a rule, with information from radar carriers, and search and targeting are carried out by active radar homing heads (GOS) ("Winged missiles in naval combat. "B. I. Rodionov, N. N. Novichkov," Military Publishing, 1986, p. 15).

 The use of active centimeter range seekers on most modern anti-ship missiles is explained by the greatest range and azimuthal sector of the visor’s view, as well as the least criticality to weather conditions (Anti-ship missile guidance systems, Radioelectronics, vol. 3, review, NIIER, Moscow, 1986 , p. 1-5). However, the condition for their normal operability is the sighting of the target at sharp (up to 10-15 degrees) angles to the surface, when the target has the greatest contrast, especially against the background of side reflections from the "excitement" of the sea surface. It is this feature, along with the desire to reduce the likelihood of intercepting missiles of ship’s air defense, that predetermined the choice of a low-altitude approach profile to the target of all existing anti-ship missiles.

 With the development and spread of anti-aircraft missile (SAM) and high-speed automatic artillery systems (ZAK) in the naval forces of various states, the probabilistic indicators of solving combat missions by subsonic anti-ship missiles are reduced. This causes interest in the creation of supersonic means of destruction of surface ships, since supersonic speeds, especially in the range of air defense systems, can not only increase the likelihood of overcoming fire resistance, but also significantly increase the damaging effect on the target due to the growth of penetrating ability.

 However, the supersonic flight of cruise missiles at low altitude is associated with significantly greater aerodynamic drag, which leads to a limitation of the range of missiles with a significant increase in their mass. For example, the supersonic (M ~ 1.4) version of the Chinese anti-ship missile system "FL-7" with a larger launch weight (1800 vs. 1550 kg) has a shorter (30 vs. 50 km) range compared to the subsonic (M = 0.9) missile variant "FL-2" (reference book "Jane's naval weapon systems", 1992).

 A known method of firing homing missiles with artillery and missile launch, flying to the target along ballistic trajectories. For example: foreign guided missiles — a Copperhead projectile with laser semi-active guidance and a Merlin mine with a millimeter-wave seeker (“Ammunition with high-precision military elements”, V. Anisimov, “Foreign Military Review”, N 10, 1994, p. 28 - 32); Russian experimental ballistic missile R-17 with an optical seeker ("Russian missile weapons 1943-1993", A.V. Karpenko, reference book, "PIKA", 1993, p. 42) and others. The firing range of such shells is controlled by giving them at the stage of dispersal an appropriate speed at a certain angle to the horizon. Aiming at the target detected by the seeker is carried out by correcting the final portion of the passive trajectory by means of forces and moments created by the projectile controls.

 It is also known the use of guided missiles, for example, artillery active-reactive ammunition, self-propelled rocket engines used to increase the firing range. An example is the artillery shell ERGM (Extented-Range Guided Munition), developed by Reiteon (controlled ammunition of extended (increased) range.) This shell is equipped with a solid-fuel accelerator to ensure maximum range, as well as folding nose surfaces and tail rudders for control flight. It is intended for attacking targets using data from the GPS satellite navigation system, as well as for destroying interference transmitters to this system, in homing mode at the source of interference ("Aviation Week & Space Technology", 12.10.98, v. 149, No. 15, p. 48-49).

However, the profile of approach to the target, implemented in the framework of the specified method, taken as a prototype, in relation to the conditions of firing at sea targets in the range of application distances is characterized by:
1. Large values of the angle of inclination of the final section of the trajectory and, as a result, irrational (for active radar seeker centimeter range) viewing angles, which is expressed in a sharp decrease in the range of possible detection of the latter;
2. The extremely limited possibilities of "working out" the target’s departure from the aiming point due to the high required overloads corresponding to large values of the "mismatch parameter" (especially when shooting at high-speed targets) with a small length of the possible correction area.

 This is expressed either in missed missiles, when their maneuverability is lower than the required overloads, or to unacceptably low speeds of “meeting” with the goal of intensive braking in the process of creating overloads at the stage of passive flight.

 The aim of the proposed method is to expand combat capabilities in terms of hitting high-speed sea targets and ensure maximum speeds of approach to the target in the range of firing distances by rational use of the "energy potential" of the projectile in accordance with the specific situation of combat use (target situation, firing distance, etc.).

 This goal is achieved by the fact that the projectile is brought on a trajectory with a shortage to the zone of the possible position of the target, on the descending branch of the trajectory, on command from the on-board control system, previously calculated from the condition of ensuring acceptable viewing angles for the target at the near border of the zone of its possible position, the projectile is transferred to a flat trajectory, and the start of the overclocking engine is carried out in one case - according to the homing head, in the other - according to a previously calculated command from the side new management system. The selection of the appropriate sign of engaging the engine is carried out in the process of prelaunch preparation, depending on the nature of the target being hit.

 The proposed flight profile provides rational operating conditions for the active centimeter-wide range of seekers in the process of carrying out a continuous projectile flight, and the cyclogram of the use of its on-board systems allows varying the length of the possible correction section and the velocity of the projectile at the target over a fairly wide range.

 In the case of firing at maneuvering high-speed targets (which follows from the analysis of the control center data), which are characterized by an extended HCV zone, the projectile is started to start the projectile after the target is detected and captured by the GOS at a predetermined distance from it. Then the impulse of the self-propelling projectile engine is realized to increase the length of the flat section of the flight, on the one hand, and also to accelerate the projectile directly in the target area, on the other. Due to the relatively greater length of movement along the flat trajectory and, especially, when the projectile is accelerated to supersonic speeds, the use of this flight profile is associated with some loss of firing range.

 When firing stationary objects and "non-speedy" surface ships, when the target’s real place is known or well predicted, the engine is started regardless of the fact that the target was detected by on-board projectile means, only on the basis of calculating the maximum reach of the weapon (this, as a rule, correlates with a longer detection range such goals due to their large geometric dimensions and reflective characteristics).

 In this case, when firing at a distance shorter than "energetically possible", in both cases, the projectile speed is increased at the target due to a corresponding reduction in the length of the passive flight section, until the latter is completely absent in the case of firing at the minimum possible range (see below, Fig. 4 and table 1).

 The well-known subsonic low-altitude anti-ship missile system "Alpha" with a detachable stage having a booster engine (Russian Missile Weapon 1943-1993, A. V. Karpenko, reference book, PIKA, 1993, p. 65) is characterized by a fixed (independent of distance) shooting) speed approach to the target and does not have the indicated capabilities for a flexible increase in speed or range in accordance with a specific tactical situation.

The essence of the proposed method is illustrated in FIG. 1, which shows two types of paths (A and B), characterized by the above features of the projectile of the engine start, and also the trajectory of firing at a minimum distance (L _{p. Min).}

 Typical trajectories A and B include the active acceleration section 1; the passive phase of the flight, consisting of a ballistic section "with under-flying" 2 and a section of movement along a lay trajectory 3 (with non-zero normal overload); as well as the stage of operation of the after-booster engine 4.

When shooting at high-speed targets, the “A” trajectory is used, the profile of which is predetermined by the need to “view” the GOS projectile of a sufficiently extended HCV zone 5 relative to the coordinates of target 6 according to the firing control data. The parameters of the projectile movement in the acceleration sections 1 and the lay trajectory 3 at the time of switching on the GPS 7 are programmed from the condition of ensuring acceptable target viewing angles, starting from the near border 8 of the HCV zone, on the one hand, and the reach of the targets up to the far border of zone 9, on the other ( see Fig. 2). The command to start the autonomous engine 4 is formed by the onboard control system based on the data of the GOS on the real position of the target at a given time. Implemented as a result of "maneuvering speed" of the projectile in the target area, it increases the efficiency of overcoming enemy fire resistance and increases the damaging effect on the target. Therefore, the firing range along trajectory "A" in FIG. 1 and below is referred to as effective (L _p . _Eff ).

The use of trajectory "B" implies reliable knowledge of the position of target 10 at the time of switching on the GPS 7. In this case, the start of engine 4 is carried out either immediately after the completion of the active section, or later at the stage of passive flight. In this case, due to the possibility of choosing the “energetically rational” moment of starting the engine and the obviously shorter length of the lay flight at low altitude, the maximum values of the firing range (L _p.max ) are _realized , but at a lower projectile speed at the target.

 In order to evaluate the positive effect of the proposal, calculations were carried out to determine the attainable level of performance characteristics (TTX) of one of the possible anti-ship projectile variants that implement the proposed method of use.

 Guided anti-ship projectile 11 (Fig. 3) consists of a homing combat unit 12 and a detachable launch and booster stage 13.

 The combat unit 12 weighing 400 kg is equipped with an autonomous solid-fuel engine 14 and aerodynamic controls. The engine 14 has a solid fuel charge of 90 kg with a specific impulse of ~ 240 sec and a thrust variable in time (the first 3 sec - 4000 kg, the next 5 - 800 kg).

 The starting and starting stage 13, weighing 500 kg, is equipped with a solid-fuel engine and gas-dynamic controls. Said engine has a charge of 340 kg of solid fuel of a similar type and a constant thrust of 15,000 kg in time.

The calculations were carried out in relation to the case of the use of shell 11 on a single surface ship under the following conditions:
- ship speed - targets ~ 30 knots. (58 km / h);
- range detection target radar carrier ~ 40 km;
- the time of information obsolescence at the moment of switching on the GOS ~ 155 sec;
- the target detection range of the GOS ~ 12 km (with a viewing angle of up to 12 ^o );
- start of an overclocking engine on trajectory “A” - at a distance of 5 km to the target; on trajectory "B" - from the condition of maximum firing range.

 Table 1 presents the results of the calculation of typical flight paths of the anti-ship projectile 11, in FIG. 4 - dependence of its speed at the target on the firing range.

The comparative effectiveness of the anti-ship missile 11 and the subsonic tactical anti-ship missiles - analogues, the performance characteristics of which are shown in Table 2, was also analyzed. When evaluating, the URO frigate with a displacement of 1,500 tons equipped with short-range air defense systems was considered as a typical target (L _page. ~ 1-5 km), and ZAK (L _p.Zak ~ 0.4-2 km).

 Due to the shorter time in the SAM and ZAK zones and, correspondingly, a smaller number of possible shelling, as well as a reduced single probability of intercepting a supersonic projectile, at a distance of ~ 40 km, a two-fold reduction in the required cost of funds to carry out a combat mission is provided (2 shells against four subsonic anti-ship missiles) .

 With a smaller firing range, the positive effect of the proposal becomes even more significant due to the increasing in this case the velocity of the projectile in the fire resistance zones of air defense.

 It seems that the effectiveness and flexibility of the combat use of anti-ship weapons provided within the framework of the proposed method, as well as the simplicity of its technical implementation, are a good enough reason for the introduction and distribution as a promising means of fighting at sea.

Claims (1)

 A method for hitting a moving target with a guided projectile with an active guidance system and an overclocking engine, which consists in launching and accelerating the projectile, including by means of an overclocking engine up to speed, the magnitude and direction of which ensures flight into the zone of the possible target position, subsequent passive flight of the projectile along a ballistic trajectory correction of its final section, performed according to the data from the homing head, characterized in that the projectile is brought out onto a trajectory with a shortage to the zone of a possible position ate on the descending branch of the trajectory by command from the onboard control system, previously calculated from the condition of ensuring acceptable target homing angles for the target at the near boundary of the zone of its possible position, the projectile is put on a flat trajectory, and the self-propelling engine is started after the target is detected and captured by the homing head projectile or on a pre-calculated command from the onboard control system.

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