RU2722218C1 - Onboard antimissile defense system of aircraft - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: invention relates to aircraft engineering, particularly, to aircraft defense systems. Onboard complex of anti-missile defense AC (1) contains simulator AC (1) in form of airframe (5) on flexible connection (3) with possibility of high-speed separation from AC (1) and towing to it. On simulator (2) there are means of simulating characteristic features AC (1), combat part (6) of rear orientation with explosive substance and fuse (9 and 14), made with possibility of its anticipatory blasting at safe from AC (1) distance and specified distance to enemy weapons (18), attacking from rear hemisphere. Warhead of simulator (2) is made consisting of at least two identical modules (7 and 12) equipped with individual combat charges (8 and 13) and means of operation of latter (10 and 15). Modules (7 and 12) are installed in tail part of simulator (2) with possibility of controlled separation from it by one, braking and blasting at safe distance from simulator (2).

EFFECT: higher durability of AC (1).

5 cl, 4 dwg

Description

The invention relates to military affairs, specifically to means of defense of an aircraft (LA) from enemy air attack equipment, mainly missiles.

A number of airborne missile defense systems of aircraft are known to be used in practice (aircraft, helicopters, unmanned aircraft).

For example, infrared (IR) countermeasures, using

- false thermal targets;

- generator of pulsed infrared interference;

- laser jamming station

[1. Means of infrared counteraction // Wikipedia. URL: https: // ru.wikipedia.org/w/index.php?title= Infrared_resistance tools &oldid=95981642 (Date of access 11/22/2019)].

However, these means, first of all, relate to passive defense means.

Or with laser, radio frequency or electromagnetic suppression [2. Air defense systems from modern weapons. URL: https://tehnowar.ru/12090-sistemy-zaschity-aviacii-ot-sovremennyh-sredstv-porazheniya.html (Date posted September 28, 2014, accessed November 22, 2019); 3. Gregory of Budland. Means of protection against MANPADS // Army Bulletin. URL: https://army-news.ru/2011/11/sredstva-zashhity-ot-pzrk/ (Display date 11/25/2011; Date accessed 11/22/2019; 4. RU 2658513 C2, F41H 11/02, 06/21. 2018; 5. RU 2298760 C1, F41H 11/02, 05/10/2007].

However, such systems are not always suitable due to the limitations and selectivity of their capabilities.

A close analogue is the aircraft’s airborne missile defense system (“Missile defense device”), which contains an aircraft simulator in the form of a flexible glider (cable) with the possibility of high-speed separation from the aircraft, release and deployment of a parachute, and towing by an aircraft, placed on a simulator of a means of simulating the characteristic features of the aforementioned aircraft, necessary and sufficient for the regular operation of enemy weapons, and a warhead of a circular orientation with explosive and fuse [6. RU 22326 U1, F41H 11/02, 03/20/2002].

In it, the warhead of the simulator is made with a single warhead (disposable) and the means for its operation directly as part of the simulator (by means of a radio fuse provided for this).

The disadvantages of the well-known airborne complex include the equal loss ratio "simulator-enemy missile": 1: 1.

The closest in purpose (scope) and combination of essential features to the claimed device is (adopted) the on-board missile defense system of the aircraft (aircraft), containing the aircraft simulator in the form of a glider on a flexible connection (cable) with the possibility of high-speed separation from the aforementioned aircraft and towing him, placed on the simulator means of simulating the characteristic features of the aforementioned aircraft, necessary and sufficient for the regular operation of enemy means of destruction, and a warhead of the rear orientation with a fuse, made with the possibility of its preemptive detonation at a safe distance from the aforementioned aircraft and a given distance to enemy weapons, attacking from the back hemisphere [7. RU 2705730 C1, F41H 11/02; F41J 9/08; B64D 3/02, 11/11/2019].

In it, the warhead of the simulator is made with a single combat charge (disposable) and the means of its operation directly as part of the simulator. At the same time, at least two such simulators are placed on the aircraft, which are separated from the aircraft, as necessary, one at a time, after undermining the previous simulator.

However, such a device, with all its positive aspects, has the following disadvantages, which make it still not very significant for self-defense against enemy weapons, mainly air-to-air and ground-to-air missiles, from the rear hemisphere:

1) the authorized sequential undermining of the warheads of the simulators together with the simulators themselves, and, consequently, the need for at least two identical simulators on board the aircraft, determine the high cost of the complex: the proactive destruction of each attacking missile is spent on the whole simulator (and the simulator at its cost, as usually exceeds the cost of a rocket);

2) preparing, separating and entering standby mode of the next (second, third, ...) simulator after undermining the previous (first, second, ...) - it takes time and a new maneuver to combine three points (LA-simulator-carrier of the attacking missile “air- air "or directly the ground-to-air missiles)), which increases the likelihood that there will simply not be any time left to preemptively detonate a subsequent simulator;

3) the concept of sequential separation from the aircraft of its simulators in flexible communication (“high-speed winch”) in an amount of more than one complicates the separation device;

4) the undermining of the entire simulator necessitates a long flexible connection, to ensure the safety of the aircraft itself;

5) two or more sets of simulators increase the overall dimensions of the aircraft (“complex”) and, therefore, worsen its flight performance.

The task to which the claimed airborne missile defense system of the aircraft is aimed is to improve its tactical, technical and economic indicators, including increasing the survival rate of aircraft with lower overall dimensions.

The solution to this problem is ensured by the fact that in the airborne missile defense system of an aircraft containing an aircraft simulator in the form of a glider in flexible communication with the possibility of high-speed separation from the aircraft and towing them, means placed on the simulator simulate the characteristic features of the aircraft, which are necessary and sufficient for regular operation enemy means of destruction, and a rear-facing warhead with a fuse, configured to preemptively detonate it at a safe distance from the aforementioned aircraft and a predetermined distance to enemy weapons attacking from the rear hemisphere, according to the claimed invention, the warhead of the simulator is made up of at least , of two identical modules equipped with individual warheads and means of actuation of the latter, while the modules are installed in the tail of the simulator with the possibility of controlled separation one from the simulator, braking and detonation at a safe distance from the simulator ..

The private set of essential features of the device is also aimed at solving the problem within the framework of the main set of its features formulated in the previous paragraph and in the claims, namely:

- the detonator of each module of the warhead can be connected with a folded tension cable, as the said means of detonation, with the simulator part directly in front of it, with the possibility of automatic operation when pulling the unwound cable (this is a very simple and reliable stand-alone device for automatically activating the fuse);

- with the previous set of features, an individual parachute can be built into the back of each warhead module, with the possibility of its opening by a counter flow of air and braking of the separated module (this minimizes the duration of the warhead reaching the blast line, as well as the geometry of the trajectory of the detachable warhead) ;

- modules of the warhead can be installed in series (this also contributes to the stability of the geometry of the trajectory of the detachable warhead, optimizes the simulator for compactness in relation to diameter);

- as an alternative feature, warhead modules can be installed in parallel (this optimizes the simulator in terms of compactness in terms of length, and also further expands the tactical and technical capabilities of the complex in combat effect on attacking enemy weapons - not only sequentially detach and undermine warhead modules, but at the same time, according to the "parallel scheme").

Implementation (implementation) of the claimed complex is possible both by using known component devices (material objects), as well as new ones that differ from the currently existing small changes (upgrades), which, on the one hand, can obviously follow for specialists from the modern level of technology and, on the other hand, through essentially new devices at the level of inventions and utility models.

The device is illustrated by drawings (diagrams) of FIG. 1-4, where the arrows show the direction of movement of the bodies:

in FIG. 1 schematically shows the main components of the complex, their location and relationship when towing the simulator and the appearance of the first attacking rocket, side view;

in FIG. 2 shows an enlarged simulator, an example with a sequential arrangement of two modules of its warhead, side view;

in FIG. 3 - simulator, an example with a parallel arrangement of two modules of its warhead, side view;

in FIG. 4 - a fragment of the complex at the initial moment of undermining the first module of the warhead of the simulator in order to destroy the attacking rocket, side view.

In the drawings, the positions indicated:

1 - aircraft (LA), for example an airplane; 2 - simulator LA 1 (false target); 3 - flexible connection, for example, cable simulator 2 with LA 1; 4 - a device for separating the simulator 2 from the aircraft 1, for example, a high-speed winch; 5 - a glider (body with wings) of the simulator 2; 6 - warhead (warhead) simulator 2; 7 - the first module warhead 6; 8 - explosive charge of the first module 7; 9 - charge fuse 8; 10 - fuse trigger device 9 (detonation device), for example, a tension cable; 11 - an individual parachute of the first module 7 in the installation with the possibility of opening behind the module 7; 12 - the second module of the warhead 6; 13 - explosive charge of the second module 12; 14 - charge fuse 13; 15 - fuse actuation device 14, for example a tension cable; 16 - an individual parachute of the second module 12 in laying with the possibility of disclosure behind the module 12; 17 is a diagram (zone) of the lesion for charge 8 when it is triggered; 18 - the first enemy attacking rocket.

The inventive airborne missile defense system LA 1 contains:

- an aircraft simulator 1 in the form of a glider 5 with flexible connection 3 with the possibility of high-speed separation from the aircraft 1 and tow them;

- located on the simulator 2 (glider 5) means of simulating the characteristic features of LA 1, necessary and sufficient for the regular operation of enemy means of destruction 18 (for example, rocket 18);

- located on the simulator 2 (glider 5), the warhead (warhead) 6 of the rear orientation (in Fig. 1-4 to the right) with a fuse (9 and 14), made with the possibility of its preemptive detonation at a safe distance from the aircraft 1 and a given distance to enemy means of destruction 18 (for example, rocket 18), attacking from the rear hemisphere.

Warhead 6 of simulator 2 is made up of at least two identical modules - the first 9 and second14. Each module (9, 14) is equipped with an individual explosive charge (8 and 13 for the first and second modules 7 and 12) of the explosive and a means of detonating (triggering) the latter. In this case, the modules 7 and 12 are installed in the rear part of the simulator 2 with the possibility of controlled separation one by one from the simulator 2, braking and detonation at a safe distance from the simulator 2.

The further description extends to particular, recommended as rational, cases of execution of the claimed device.

The fuse 9, 14 of each module 7, 12 of the warhead 6 can be connected with a folded tension cable 10 and 15, respectively, as the said means of detonation, with the part of the simulator 2 located directly in front of it, with the possibility of automatic operation when the unwound cable 10, 15 is automatically pulled.

At the same time, an individual parachute (11, 16) can be integrated into the back of each module (7, 12) of the warhead 6 - see Fig. 2, 3), with the possibility of its opening by a counter flow of air and braking of the separated module (see Fig. 4).

Modules 7 and 12 of warhead 6 can be installed either sequentially (see Fig. 2) or (as an alternative feature) in parallel (see Fig. 3).

A signal wire may be provided (as in the prototype), combined with a flexible connection (cable) 3 and connected to a simulator 2 (not shown).

The inventive device operates as follows (method of operation).

Upon detection of a threat of defeat of LA 1 (an enemy attack in the rear hemisphere), they release on a flexible connection (for example, a cable) 3 from the aircraft LA 1 (for example, on a high-speed winch 4) a planning false target - simulator 2. The latter imitates the widest range of signs of LA 1 , which is identified by the attacking rocket 18. At the same time, LA 1 muffles, if possible, its signs. The control system of LA 1, for example, through the mentioned signal wire, aligns the flight path in a straight line: LA 1 → simulator 2 → attacking enemy rocket 18. Closing itself with simulator 2 from the attacking rocket 18, LA 1 simultaneously reduces lateral wind load on the flexible connection (cable ) 3.

At a safe distance not only from LA 1 (as in the prototype), but (which is fundamentally important) and from simulator 2, in a continuation of approximately the same straight line from simulator 2, a meeting occurs and a pre-emptive detonation of the attacking rocket 18 with a warhead 8 explosives of the first module 7 warhead 6 simulator 2 (see figure 4).

In the example of a device with a tension cable 10 of the fuse 9 of module 7, this undermining occurs automatically as a result of braking of the detached (by command) module 7 by the opening individual parachute 11 of module 7 (in the example with a parachute) and the inevitable subsequent complete tension of the cable 10. Parachute 11 is not a significant barrier to the damaging factors of the explosion of module 7 warhead 6.

Undermining the first module 7 causes damage to the attacking rocket 18. Simulator 2, due to the “safe distance” from module 7 to it (2), as well as the aforementioned “rear orientation” of the damage diagram 17 (see Fig. 4), remains intact and ready for further fulfillment of their functions.

In case of a repeated threat (attack by a second enemy missile, which is not shown), the described process is repeated (s) in relation to the second module 12 of warhead 6 of simulator 2, regardless of whether it is sequential (see Fig. 2) or parallel (see Fig. 3) modules 7 and 12 are connected to simulator 2.

However, with a parallel circuit (see Fig. 3), it is possible to simultaneously separate from simulator 2 and trigger two (or more if available) modules (7 and 12) of warhead 6, which may be appropriate if there is a need for a more powerful attack on the attacker ( ii) in the rear hemisphere, the enemy (s) object (s) 18.

Additionally, it becomes possible to solve new combat missions of the operational-tactical level. A high-speed unmanned aircraft LA 1 with the described method of defense (defense) is capable of provoking the enemy to use ammunition of ground-to-air missiles and thereby create air corridors on the territory of the enemy for the further entry of manned combat aircraft into them.

The proposed airborne complex is simple, technologically uncomplicated, provides high reliability and is able to guaranteedly close the rear hemisphere of an airplane, helicopter or other aircraft from being hit by air-to-air, air-to-air or other attacking means.

The technical result consists in improving the tactical, technical and economic indicators of the airborne missile defense system and the aircraft as a whole, including increasing the survival of the aircraft with lower overall dimensions.

Thus, the use of the claimed device solves the problem.

Claims (5)

1. On-board missile defense system of an aircraft, containing an aircraft simulator in the form of a glider in flexible communication with the possibility of speedy separation from the aforementioned aircraft and towing them, means placed on the simulator to simulate the characteristic features of the aircraft, which are necessary and sufficient for regular operation of enemy weapons, and a warhead rear orientation with an explosive and fuse, made with the possibility of preemptive detonation at a safe distance from the aforementioned aircraft and a given distance to enemy weapons attacking from the rear hemisphere, characterized in that the warhead of the simulator is made up of at least two identical modules equipped with individual warheads and means of actuation of the latter, while the modules are installed in the rear of the simulator with the possibility of controlled separation one by one from the simulator, braking and detonation at a safe distance from the simulator. 2. The on-board complex according to claim 1, characterized in that the fuse of each module of the warhead is connected by a folded tension cable, as a means of detonation, with the part of the simulator directly in front of it, with the possibility of automatic operation when pulling the unwound cable. 3. The airborne complex according to claim 2, characterized in that an individual parachute is built into the back of each module of the warhead, with the possibility of opening it with a counter flow of air and braking the separated module. 4. The airborne complex according to claim 1, characterized in that the warhead modules are installed in series. 5. The airborne complex according to claim 1, characterized in that the warhead modules are installed in parallel.

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