RU2740828C1 - Method of side firing by fire weapons of target destruction from aircraft and device for implementation thereof - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: group of inventions relates to aircraft engineering, and more particularly to method of side firing and device for its implementation. Method of side firing by target fire weapons from aircraft board involves application of fire weapons. At that firing is carried out by controlled weapons from manned or from unmanned aircraft. AC moves along ellipse trajectory. Trajectory of the enemy air defence facilities not touching the boundary of the zone of destruction. Large axis of closed ellipsoidal trajectory is perpendicular to firing direction along target. Output of the line of sight stabilization system is connected to the input of the automated electric drive performing turn-around and stabilization of launching containers. Missiles are oriented to the left and to the right relative to the aircraft motion direction.

EFFECT: higher durability of aircraft and higher reliability of combat mission.

10 cl, 10 dwg

Description

The invention relates to methods of using aircraft weapons systems and devices for their implementation, and in particular to the placement of launch containers for guided and unguided missiles on unmanned and manned aerial vehicles (LA) and control of their fire.

The known method of firing from an aircraft using a suspended container rotary cannon and unguided missile weapons, made with a rotary lower part and allowing the use of weapons in the entire circular space [Suspended container rotary weapons. - Application for invention RU 93055844. - Priority 16.12.1993].

There is a method of firing from an aircraft with unguided projectiles using a block of barrel assemblies oriented perpendicular to the longitudinal axis of the aircraft [A method of deploying firing systems, a method of ejecting multiple projectiles (options) and an aircraft. - Application for invention RU 2002130578. - Priority 04.05.2001].

Known hanging machine gun module of a helicopter [Patent RU 2601999. - Priority 06/22/2015], equipped with a mechanism for reorienting machine gun cartridges from one position to another.

A known method of side firing from a standard airborne small arms mounted on pivot mounts inside the fuselage of the helicopter, on the left and / or right sides of the cargo compartment, allowing to hit manpower and lightly armored ground equipment of the enemy at ranges of 800-1000 m [Instructions for the crew of the helicopter Mi-24V ... Ed. third. Book. II. Combat use. - M .: Military Publishing, 1987. - 250 p.].

The closest to the claimed invention in terms of technical essence is a device that implements the method of side firing and includes a launch swivel suspended container suspended under the aircraft fuselage on external suspension nodes, made with a rotary lower part, inside which a movable cannon and unguided rocket armament is installed [Suspended rotary weapon container. - Application for invention RU 93055844. - Priority 16.12.1996].

The disadvantages of the described methods of shooting and devices for their implementation (analogs and prototype) are: short range of destruction of targets; impossibility or low efficiency of destruction of armored targets and stationary objects; the danger and high probability of aircraft being hit by the enemy's military air defense (air defense); lack of guarantees and / or low efficiency of the successful completion of the second and subsequent attacks of other targets due to the inevitable hit of the aircraft in the area of operation of military air defense assets; impossibility and / or low efficiency of destruction of maneuvering targets.

The objective of the invention is to eliminate the noted drawbacks, namely: increasing the combat effectiveness of the use of unmanned attack aircraft (UAVs) and manned aircraft (PLA) aircraft through the implementation of the method of side firing with guided missiles of the "air-to-surface" and / or "air-to-air" class and increasing survivability shock UAVs and submarines due to the exclusion of their entry into the zone of operation of the enemy's military and / or object air defense, that is, the exclusion of combat contact between the aircraft and the enemy's weapons.

The problem of the invention is solved by applying the method of lateral firing with guided weapons, choosing an elliptical flight trajectory of an attack aircraft - a carrier of weapons, passing close to and parallel to the line of contact with enemy air defense systems, using in-fuselage and / or suspended launch containers with guided missiles oriented perpendicular to the direction flight of the aircraft in both directions, to the right and to the left, relative to the direction of flight, using a device for controlling the orientation of launch containers and launching missiles and stabilizing the line of sight when guiding a guided missile at a target, which ensures high combat effectiveness of the use and survivability of an attack aircraft by eliminating its hitting the area of action of enemy air defense and high accuracy of hitting targets due to firing guided missiles.

The method of side firing from an aircraft with guided missiles is illustrated by the drawings:

- fig. 1 is a diagram of the combat application of the method of lateral firing of guided missiles from an aircraft;

- fig. 2 is a diagram of side firing in opposite directions, perpendicular to the direction of aircraft movement;

- fig. 3 - options for the in-body placement of guided anti-tank missiles;

- fig. 4 is a diagram of the combat use of the side firing method when breaking through the enemy's defense;

- fig. 5 - a diagram of the combat use of aircraft in the classical method of direct fire;

- fig. 6 is a diagram of repelling a tank attack using the side firing method;

- fig. 7 - the application of the method of side firing when destroying air targets on the example of an airmobile group.

FIG. 1-7 the following designations are used: 1 - shock aircraft; 2 - elliptical flight trajectory of aircraft 1; 3 - line of combat contact; 4 - hitting targets (objects) of the enemy; 5 - zone of destruction by means of military and / or object air defense of the enemy; 6 - direction of side firing; hOX is the vertical plane in FIG. one; ОХ ₁ - the direction of the longitudinal axis of the aircraft or the direction of flight of the aircraft; OZ ₁ , - OZ ₁ - direction of fire with controlled weapons; V _p , V _in - vectors of velocities of the rocket and the aircraft, respectively (see Fig. 2); 7 - launch container with guided weapons installed in it; 8-11 - options for ventral and intra-fuselage placement of launch containers for anti-tank guided missiles (see Fig. 3): 8 - eight missiles: four - right and four - left launch orientation; 9 - twelve missiles: six - right and six - left launch orientation; 10 - four missiles: two - right and two - left launch orientation; 11 - variant of the combined placement of guided missiles (four missiles: two - right and two - left launch orientation) and unguided missiles (one and / or two blocks (one block is shown in Fig. 3); 12 - front line; 13 - flying up to targets guided means of destruction; 14 - letters of the left side of the aircraft (in Fig. 4 pos. 2 - an elliptical trajectory, which is a zone of unlimited time for launch; 1 ... 8 - launch points of guided missiles on the trajectory 2 of the flight of the aircraft); 15 - letters of the right side LA; 16 - flat turns; 17 - group of additional reconnaissance of targets; 18 - landing group; 19 - cover group; ω - angular velocity of flat turn (see Fig. 6).

The use of guided weapons, for example, anti-tank guided missiles of the "air-to-surface" class, makes it possible to increase the range of destruction of targets up to 5-10 km and to hit armored mobile targets and stationary objects of the enemy at these ranges: command posts, depots of weapons and ammunition, railway stations , oil storages, gas stations, etc. The choice of the flight trajectory of the aircraft carrier, excluding it from entering the affected area by enemy air defense means, consists in the fact that the onboard guided weapons and the means of their guidance and launch are oriented perpendicular to the longitudinal axis OX _{1 of the} aircraft in the associated coordinate system at an angle of ± 90 °, that is, along the OZ ₁ axis as shown in FIG. 2, where ОХ ₁ is the direction of the longitudinal axis of the aircraft or the direction of flight of the aircraft; OZ ₁ , - OZ ₁ - direction of fire with controlled weapons.

FIG. 3 shows some options for ventral or intra-fuselage placement of launch containers for anti-tank guided missiles (eight missiles: four - right and four - left launch orientation, pos. 8); option for placing unguided missiles (twelve missiles: six - right and six - left orientation, pos. 9, and two containers of two missiles, pos. 10); a variant of the combined placement of guided (four missiles: two - right and two - left launch orientation) and unguided aircraft missiles (one and / or two blocks (in Fig. 3, pos. 11, one block is shown).

FIG. 4 shows a diagram of the application of the proposed method of lateral firing of guided missiles when breaking through enemy defenses, where are indicated: 4 - a fragment (eight tanks) of an enemy tank company; 12 - front line; 13 - guided weapons flying up to targets; 3 - border of the zone of reach of the enemy's air defense systems; 14 - letter of the left side of the helicopter; elliptical trajectory 2 of the helicopter flight (zone of unlimited time for launch; numbers 1 ... 8 on the trajectory of the helicopter indicate the launch points of guided missiles); 15 - letters of the starboard side of the aircraft.

From FIG. 4 it follows that it is advisable for the carrier aircraft 1 to be in the zone of unlimited time for launching missiles (on trajectory 2) and below the reconnaissance aircraft (not shown in Fig. 4). Being in the launch zone of guided missiles, on trajectory 2, parallel to the front line, located at a distance of, for example, 6200 m, the pilot of an aircraft, for example, a helicopter, at its optimal flight speed in terms of vibration level of 180 km / h (50 m / s) has the ability in just 1 min. 20 s to make 4 launches of guided missiles from the left side and, after a 180 ° turn, 4 more launches from the starboard side, also in just 1 min. 20 s. In this case, the total time of fire impact on the enemy is 2 minutes. 50 s. The pilot is not constrained in time when he is on this trajectory, since he is outside the boundary of the 3rd zone of reach of the enemy's air defense systems. At the same time, when attacking similar targets in the classical way - by direct fire (see Fig. 5), even with the use of the most modern helicopters (for example, the Ka-52), the total time of fire impact is more than doubled; in this case, the period of time for re-entering the combat course (3 minutes 10 s) turns out to be completely ineffective. So, with the initial data: launch range - 6200 m, target detection time - 5 s, aiming time - 10 s, exit time from attack - 10 s, missile launch time in one run against two targets - 50 s, re-entry time to target - 60 s, helicopter speed - 200 km / h (≈55 m / s), - we get the following output data: the distance traveled by the helicopter in one run - 2750 m (including the launch of one rocket - 1100 m, for launch of the second missile and exit from the attack - 1650 m); maximum distance of the helicopter from the target at the beginning of the first approach - 8950 m; the total time of fire impact will be 4 × 50 s + 3 ± 60 s = 380 s = 6 minutes. 20 s, where 4 is the number of approaches to the target; 3 - the number of exits from the attack.

FIG. 5 marked: 4 - a fragment of an enemy tank company (8 tanks); 12 - front line; 13 - guided weapons flying up to targets; 3 - border of the zone of reach of the enemy's air defense systems; 2 - flight trajectory of a UAV or PLA (for example, a helicopter, 1 ... 8 - launch points of guided missiles on the trajectory of a helicopter flight); 1 - helicopter.

The side firing method is also effective in other types of combat operations, for example, when a tank column is detected advancing in a direction opposite to the aircraft's movement, for example, a helicopter. Taking into account the fact that even in the absence of covering a tank column by means of enemy military air defense, each tank has the ability to create a circular destruction zone around itself with an effective range (radius) of up to 2500 m (due to the use of large-caliber machine guns), the method of side firing allows after a simple maneuver ( for example, after two flat turns) and the transition to a trajectory parallel to the movement of the attacking tank column at a distance of 3000 m from it, immediately begin to destroy armored targets. FIG. 6 shows the scheme of repelling a tank attack: 4 - tank columns; 1 - aircraft, for example, a helicopter; 16 - flat reversals; 3 - border of the zone of destruction of tank machine guns; 2 - lateral firing trajectory (1 ... 8 - launch points of guided missiles on the helicopter flight path).

According to the calculations performed, in the situation depicted in FIG. 6, the method of side firing with anti-tank guided missiles allows in less than 3 minutes. inflict damage to a tank company of 17 tanks (8:17) × 100% = 47%. According to NATO tactical norms, inflicting such damage means “destroying a tank company”, followed by a refusal to continue the offensive.

The inventive method of side firing is more effective compared to the method of direct fire and when destroying air targets, for example, an airmobile group (see Fig. 7), consisting of a group of additional reconnaissance targets 17, an amphibious group 18 and a cover group 19. In this case, the need to approach the tail of the enemy helicopters 17-19 and flat turns with an angular velocity of (16 in Fig. 6). Side firing from the left and right sides of an aircraft, for example, a helicopter, 1 flying along a trajectory 2, allows you to destroy the airmobile group 17-19 on a head-on and on a passing course by sequentially launching guided missiles from points 1 ... 8 of the trajectory 2 of the helicopter flight.

The claimed new method of placing and using guided weapons also makes it possible to apply such tactics as circular or fan-assisted destruction of targets, which is used in the event of an enemy encircling an airfield or a helicopter landing site. In this case, the combined use of aircraft weapons - guided and unguided - is effective.

The technical result of the implementation of the inventive method of lateral firing with guided weapons is achieved due to the fact that an intra-fuselage container and a target line of sight stabilization system are introduced into the device for implementing the inventive method of lateral firing with airborne weapons, including a launching rotary ventral container with unguided missiles. direction perpendicular to the direction of movement of the aircraft, while the ventral and intra-fuselage launch containers are equipped with guided missiles oriented in the direction perpendicular to the direction of movement of the aircraft, to the left and to the right relative to this direction, the output of the line of sight stabilization system is connected to the input of an automated electric drive that rotates and stabilizes both launch containers in the direction perpendicular to the direction of movement of the aircraft, and the missiles in the ventral and intra-fuselage launch containers are oriented relative to the direction Aircraft flight in opposite directions, to the left and to the right, relative to this direction.

The claimed device is illustrated by drawings:

- fig. 8 is a functional diagram of a device for implementing the method of lateral firing of guided missiles from an aircraft;

- fig. 9 is a diagram of the location of guided missiles in the launch container.

- fig. 10 - options for the placement of guided missiles in the suspended ventral and / or in the intra-fuselage launch containers.

FIG. 8-10 the following designations are used: 20 - sighting and navigation complex (PRNK); 21 - system for stabilizing the position of rotary launch containers (SS PPK) 7 in the direction of the line of sight of the target; 22 - automated tracking electric drive (AED) of the launch container 7; 23 - guided missile; 24 - aerodynamic steering wheel; 25 - rudder-feather, creating a lifting force; 26 is a schematic representation of a guided missile directed "towards us"; 27 is a schematic representation of a guided missile directed "away from us", while the output of the PrNK 20 is connected to the input of the stabilization system 21 of the line of sight of the launch container 4, which generates a control signal u (V _p ) proportional to the magnitude and direction of the ground speed vector V _p , which is fed to the input of the automated tracking electric drive 22, mechanically connected to the launch container 7 for turning and stabilizing its position in the direction of launching guided and / or unguided missiles; NP - aircraft flight direction; NPR - direction of missile launch.

управляемых ракет может быть внутрифюзеляжным и/или подвесным, подфюзеляжным. Ракеты размещены с возможностью пуска в противоположные стороны:

ракет ориентированы в сторону левого борта и перпендикулярно продольной оси ЛА;

ракет ориентированы в сторону правого борта и перпендикулярно продольной оси ЛА.The device works as follows. PrNK 20 issues a signal proportional to the ground speed V _p to the stabilization system 21 of the line of sight, which generates a control signal u (V _p ) supplied to the input of the automated electric drive 22, which, according to this signal, turns and stabilizes the direction of launch of guided missiles along the line of sight of the target, perpendicular to the direction of movement of the center of mass of the aircraft 1. The launch container 7 as a device for placing

guided missiles can be intra-fuselage and / or suspended, ventral. The missiles are placed with the possibility of launching in opposite directions:

missiles are oriented towards the left side and perpendicular to the longitudinal axis of the aircraft;

missiles are oriented towards the starboard side and perpendicular to the longitudinal axis of the aircraft.

The automatic stabilization system of 21 line of sight performs the necessary turn, with a crosswind, and stabilizes the direction of missile launch perpendicular to the ground speed vector V _p , in the presence of a crosswind, or perpendicular to the longitudinal axis of the aircraft in the absence of a crosswind.

The technical result of the application of the claimed method of lateral firing from an attack UAV or PLA with controlled weapons and a device for its implementation is as follows:

• in the exclusion of the possibility of hitting aircraft by means of air defense;

• in providing the pilot with practically unlimited time to hit targets;

• in a significant reduction in the time for hitting group targets in comparison with the method of direct fire;

• saving the time allotted for the execution of a combat mission by eliminating the time required when using the direct firing method for repeated search, target detection and identification, aiming, guidance and use of guided weapons;

• in a sharp increase in the effectiveness of shooting, which consists in increasing the probability and decreasing the time of destruction of ground and air targets;

• in the effective elimination of all-round defense and the enemy's encirclement of liberated objects: helicopter landing sites, airfields, etc.

Claims (10)

1. A method of side firing with fire weapons to destroy targets from an aircraft, which consists in the use of fire weapons in the form of unguided missile weapons installed in a suspended rotary container, characterized in that the aircraft is manned or unmanned and is additionally equipped with guided missiles, the shooting is carried out guided and unguided missiles, the aircraft moves along an elliptical trajectory that does not touch the boundary of the affected area by enemy air defense means, while the major axis of the closed elliptical trajectory is perpendicular to the direction of fire at the target. 2. The method of lateral firing according to claim 1, characterized in that the firing is carried out when the aircraft moves along an elliptical trajectory both clockwise and counterclockwise, that is, regardless of the direction of movement of the aircraft. 3. The method of side firing according to claim 1, characterized in that the firing is carried out with controlled weapons or with the use of a combination of controlled and uncontrolled weapons. 4. The method of side shooting according to any one of paragraphs. 1-3, characterized in that guided and unguided weapons are located in ventral launch containers. 5. The method of side shooting according to any one of paragraphs. 1-3, characterized in that the guided and unguided weapons are placed in the intra-fuselage launch containers. 6. The method of lateral firing according to claim 3, characterized in that the controlled weapons are placed in a launch container with the possibility of launching in mutually opposite directions and are oriented perpendicular to the longitudinal axis of the aircraft. 7. The method of side shooting according to any one of paragraphs. 1-3, characterized in that when the aircraft moves in the air, the ventral and intra-fuselage containers with controlled and uncontrolled weapons placed in them are automatically stabilized in the direction perpendicular to the vector of the aircraft ground speed. 8. A device for implementing the method of lateral firing with fire weapons to destroy targets from an aircraft according to any one of paragraphs. 1-3, which includes a launching rotary ventral container with unguided missiles, characterized in that an intra-fuselage container and a target line of sight stabilization system are introduced into it in the direction perpendicular to the direction of movement of the aircraft, while the ventral and intra-fuselage launch containers are equipped with guided weapons oriented in the direction perpendicular to the direction of movement of the aircraft, to the left and to the right relative to this direction, the output of the line of sight stabilization system is connected to the input of an automated electric drive that rotates and stabilizes the launch containers in the direction perpendicular to the direction of movement of the aircraft, and the means of destruction located in ventral and intra-fuselage launch containers, oriented relative to the direction of flight of the aircraft in opposite directions relative to this direction. 9. The device according to claim 8, characterized in that the means of destruction, which are controlled means of destruction, located in the launching ventral container and / or in the launching intra-fuselage container, oriented in the direction perpendicular to the direction of the ground speed vector of the aircraft, are equipped with radar, infrared , television or laser homing heads with the ability to automatically control their launch in mutually opposite directions. 10. Device according to any one of paragraphs. 8, 9, characterized in that it is intended for installation on manned and unmanned aerial vehicles.

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