RU2843385C1 - Combined jet aviation ammunition (cjaa), method of cjaa functioning and method of enemy air defense means destruction using two cjaa (embodiments) - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: combined jet aircraft ammunition (CJAA) comprises a planning module, an anti-aircraft guided missile (AAGM) with their standard target guidance systems and flight control elements and unguided MLRS projectiles, having the ability, after launching from an aircraft, to perform a controlled flight in height, direction and speed. Variants of the use of CJAA are dropping from a carrier aircraft at altitude of 10–13 km or more, “cold gliding” of CJAA, using only the gliding module, without the MLRS and AAGM projectiles jet engines switching on, to a low altitude, at which, depending on the distance to the target, MLRS and AAGM projectiles rocket engines are switched on in turn or all at once, or dropping from a carrier aircraft at altitude of 10–13 km or more, switching on all the MLRS rocket engines at once, climbing an additional flight altitude, after switching off all the MLRS rocket engines from a higher flight point, switching to the CJAA “cold gliding” mode, when low flight altitude is achieved and when AAGM jet engine is switched on, controlled flight is performed in the mode of cruise missile or two CJAAs are simultaneously launched.

EFFECT: combined jet airborne ammunition for application of point rocket-and-bombing strikes against ground or surface fixed or moving targets of the enemy.

5 cl, 10 dwg

Description

The invention relates to the field of aviation munitions, in particular to the design of airborne combined intelligent air-to-surface munitions, which include a planning module, a surface-to-air guided missile (SAM) with its standard target guidance systems and flight control elements, and unguided MLRS projectiles, which have the ability, after launch from an aircraft, to carry out a controlled flight in altitude, direction, and speed, when the SAM jet engines and MLRS projectiles are activated, including at low altitudes, following the folds of the terrain with control in speed, altitude, and direction, for delivering pinpoint missile and bomb strikes against ground or surface stationary or moving enemy targets, possibly including air targets.

The existing level of technology includes devices for anti-aircraft missile systems, for example, the Buk SAM system of 1979 with anti-aircraft guided missiles (SAM), for example, 9M38, weighing 690 kg, 5.5 meters long and 400 mm in diameter, which is a homing solid-fuel missile that is guided to the target using a homing head that has two guidance channels - photocontrast and infrared in accordance with L [1], which has already been removed from service, but stocks of 9M38 SAMs are presumably in warehouses. Also known are devices for multiple launch rocket systems (MLRS), and ready-made rocket projectiles for MLRS, high-explosive fragmentation action of 122 mm caliber or volumetric detonation action of 220 mm caliber for flamethrower systems, which are already mass-produced by industry.

However, from the existing level of technology, there is no known intelligent air-to-surface jet munition containing a planning module, ready-made industrially produced MLRS rockets and a surface-to-air guided missile (SAM), combined into a common structure with additional mounting hardware that allows, after launch from a carrier aircraft, to carry out a controlled flight using a planning module in range, speed, altitude and direction, with sequential and/or simultaneous activation of the MLRS rocket engines and the SAM rocket engine, during flight, including at low altitudes, following the folds of the terrain with control in altitude and direction, for delivering pinpoint missile and bomb strikes against ground or surface stationary or moving enemy targets.

Thus, the task of creating a jet intelligent air-to-surface type munition containing a planning module, ready-made industrially produced MLRS rockets and a surface-to-air guided missile (SAM), combined into a common structure with additional fastening fittings, allowing after launch from a carrier aircraft to carry out a controlled flight using the planning module, in range, speed, altitude and direction, with sequential and/or simultaneous activation of the jet engines of the MLRS projectiles and the jet engine of the surface-to-air guided missile (SAM), during flight, including at low altitudes, following the folds of the terrain with control in altitude and direction, for delivering pinpoint missile and bomb strikes against ground or surface stationary or moving enemy targets.

The objective of achieving the technical result to which the claimed invention is directed is the creation of an intelligent air-to-surface type jet aircraft munition containing a planning module, ready-made industrially produced MLRS rocket projectiles and an anti-aircraft guided missile (SAM), combined into a common structure with additional fastening fittings, allowing, after launch from a carrier aircraft, to carry out a controlled flight using the planning module, in range, speed, altitude and direction, with sequential and/or simultaneous activation of the MLRS projectile jet engines and the anti-aircraft guided missile (SAM) jet engine, during flight, including at low altitudes, following the folds of the terrain with control in altitude and direction, for delivering pinpoint missile and bomb strikes against ground or surface stationary or moving enemy targets.

The stated task (achieving a technical result) is solved by the fact that a Combined Jet Aviation Ammunition is proposed according to paragraph 1 of the invention formula.

The stated task (achieving a technical result) is also solved by the fact that a Combined Jet Aviation Ammunition is proposed according to paragraph 2 of the invention formula.

The technical result is also achieved in the method of operation of the Combined Jet Aviation Ammunition according to paragraph 3 of the invention formula.

The technical result is also achieved in the method of operation of the Combined Jet Aviation Ammunition according to paragraph 4 of the invention formula.

The technical result is also achieved in the method of destroying enemy air defense systems using two combined jet aviation munitions according to paragraph 5 of the invention formula.

The essence of the invention is explained by Fig. 1, Fig. 2, Fig. 3, Fig. 4, Fig. 5, Fig. 6, Fig. 7, Fig. 8, Fig. 9 and Fig. 10 for the most preferred, in terms of the damaging factor, flamethrower version of the Combined Jet Aircraft Munition (hereinafter referred to as CRAB), containing, for example, four ready-made industrially produced MLRS projectiles, for example, the NURS MO.1.01.04M caliber 220 mm, length - 3700 mm, used for the flamethrower system of the MLRS and an anti-aircraft guided missile (SAM), for example 9M38, the weight of which is 690 kg, length 5.5 meters and diameter 400 mm, united into a common structure with additional fastening fittings, on which the standard suspension system is also fixed, like that of aircraft bombs on a carrier aircraft, and a rotary wing of the gliding module without control and wing mechanization, allowing after launch from an aircraft to carry out a controlled flight in speed, altitude and direction, when the jet engines of the MLRS projectiles and SAM are turned on, the control elements of which allow for a controlled flight, including at low altitudes, repeating terrain folds with control over altitude and direction, for delivering pinpoint missile and bomb strikes against ground or surface stationary or moving enemy targets.

Fig. 1 shows an explanatory sketch of the element for fastening MLRS projectiles as part of the general design of additional fastening reinforcement, where: 1 is a supporting plate, 2 is a front conical pipe with an input internal diameter of 220.5 mm, rigidly fixed, for example by welding, on the supporting plate 1, 3 and 4 are middle pipes with an input internal diameter of 220.5 mm, rigidly fixed, for example by welding, on the supporting plate 1, 5 is a rear pipe of reinforcement for fastening and fixing a MLRS projectile of 220 mm caliber, 6 is a projectile retainer 7 in the rear pipe of reinforcement for fastening MLRS projectiles.

Fig. 2 shows an explanatory sketch, where: 7 - a MLRS projectile, for example, NURS MO.1.01.04M, caliber 220 mm, length - 3700 mm, used for the flamethrower system of the MLRS.

Fig. 3 shows an explanatory sketch of the MLRS projectile fastening element as part of the general structure of the additional fastening fittings according to Fig. 1 assembled with the MLRS projectile 7 and together with the upper half rings 10 of the bandage fastening to the SAM and the suspension elements 8 to the carrier aircraft, where: 3 and 4 are the middle pipes according to Fig. 1, 7 is the MLRS projectile, 8 are the suspension fastenings to the carrier aircraft pylons, 9 is the upper fastening plate, secured by welding to the middle pipes 3 according to Fig. 1, to which the suspension fastening 8 is secured, 10 is the upper half ring of the front bandage, to which the middle pipes 3 are secured by welding with the fastening plate 9 and the suspension fastening 8, 11 are the tightening plates of the upper and lower half rings of the front bandage with a bolted connection.

Fig. 4 shows an explanatory sketch of a preferred variant of a possible design of a retainer 6, comprising a housing 13, a spring 12 with a latch 14, which secures the MLRS projectile 7 in the additional fastening fittings according to Fig. 3.

Fig. 5 shows an explanatory sketch of the general design of the additional fastening reinforcement, the upper 10 and lower 15 half rings of the front bandage, on which the middle pipes 3 for four projectiles 7 are welded. Fig. 3, the plates of the upper and lower half rings of the front bandage without MLRS and SAMs, not tightened by a bolted connection, where: 16 is the lower fastening plate, welded on the middle pipes 3 by analogy with the upper fastening plate 9, 17 is a rotating device containing an electromagnetic latch and a rotating spring (not shown in the sketch), 18 is a rotating wing with a straight rectangular flat-convex profile without in-flight control elements, fixed on the rotating device 17 as part of the gliding module.

Fig. 6 shows an explanatory sketch of the general design of the additional fastening reinforcement, the upper 10 and lower 15 half rings of the front bandage, on which the middle pipes 4 for four projectiles 7 are fixed by welding. Fig. 3, the plates of the upper and lower half rings of the front bandage are already tightened by a bolted connection, but without MLRS and SAM, where: 19 is the lower fastening plate, fixed by welding on the middle pipes 4 by analogy with the lower fastening plate 16.

Fig. 7 shows an explanatory sketch, where 20 is a surface-to-air missile (SAM), for example 9M38, weighing 690 kg, 5.5 meters long and 400 mm in diameter, before assembly with the general structure of the additional CRAB mounting fittings.

Fig. 8 shows an explanatory sketch of the assembly order of the general structure with additional reinforcement for fastening the CRAB, when the upper 10 and lower 15 half rings of the front bandage with the middle pipes 3 and middle pipes 4, when the plates of the upper and lower half rings of the front and rear bandages are not yet tightened with a bolted connection.

Fig. 9 shows an explanatory sketch of the general design of the additional reinforcement for fastening the CRAB assembled with the SAM 20 (the bolted plates of the upper and lower half rings of the front and rear bandages are not shown in the sketch) and in the transport position of the rotary wing 18 along the SAM axis as part of the gliding module when suspended from the pylons of the carrier aircraft.

Fig. 10 shows an explanatory sketch of the general design of the additional reinforcement for fastening the CRAB assembled with the SAM 20 (not shown in the sketch) with the plates 11 already assembled with a tightening bolt connection and with the rotary wing 18 already in the flight position across the SAM axis as part of the gliding module during independent flight of the CRAB after being dropped from the carrier aircraft.

For the CRAB design variants containing additional wind generators that can be located and secured, for example, on the plates 11 of Fig. 10 assembled with a tightening bolt connection, as well as a system for launching the rocket part of the MLRS projectiles (not shown in the sketches), which, upon command from the SAM control unit, supplies an electric impulse to the contacts of the pads for triggering the electric igniters that ignite the ignition charge, which ignites the main charge of the rocket part of the MLRS projectiles. The use of a wind generator in the CRAB design is advisable when greater power consumption is expected during flight in the mode of sufficiently long maneuvering of a guided cruise missile, including at low altitudes, following the folds of the terrain with control by altitude and direction, for delivering pinpoint missile and bomb strikes against ground or surface stationary or moving enemy targets. In various variants of the functioning of the CRAB in accordance with the formula of the invention and depending on the type of MLRS projectiles, it is possible to use them either without standard fuses, or with installed standard MLRS projectile fuses, or with the installation of special fuses, for example, radio-controlled, etc.

The operation of the most preferred embodiment of the CRAB described in Figs. 1-10 occurs as follows. The assembly of the CRAB is carried out in the process of preparing the CRAB suspension through the standard suspension elements 8 to the carrier aircraft. First, on the SAM 20 Fig. 7, in a vertical position, a general structure of additional fastening reinforcement is installed, secured by tightened bolted plates 11 of the upper and lower half rings 10 and 15 of the front and rear bandages Fig. 5 and Fig. 6, with the fixed position of the rotary wing 18 as part of the planning module along the axes of the SAM installation and MLRS projectiles using a rotary device 17 containing an electromagnetic latch and a rotary spring (not shown in the sketches). Additional wind generators and contact pads of electric igniters for igniting the ignition charges of the main charge of the rocket part of the MLRS projectiles are installed, for example, also by a bolted connection on plates 11. Then the general structure of the additional fastening fittings together with the SAM, through the standard suspension elements 8 to the carrier aircraft is secured on the preparatory horizontal traverse and installed from the side of the rear pipe 5 of the fittings for fastening and fixing the MLRS projectile with fixation of the projectile 7 in the rear pipe of the fittings for fastening the MLRS projectiles by the lock 6 Fig. 1. All electrical connections of the control from the SAM control unit of the rotary device 17, containing an electromagnetic latch and a rotary spring (not shown in the sketches), and the electric igniters for igniting the ignition charges of the main charge of the rocket part of the MLRS projectiles are also connected. After the final assembly of the CRAB and testing of the control systems, the entire CRAB structure is installed on the pylons of the carrier aircraft and at least three tactical options for the operation of the CRAB are possible in accordance with the formula, in which the target engagement distance can be increased to 150 km or more depending on weather conditions.

The first tactical variant of the operation of the CRAB according to point 3 of the formula, when, on command from the SAM control unit, the rotating device 17, containing an electromagnetic latch and a rotating spring (not shown in the sketches) deploys the rotating wing 18 to the flight position across the SAM axis Fig. 10 as part of the planning module during independent flight of the CRAB after dropping from the carrier aircraft, at an altitude of 10-13 km or more, at a safe distance from destruction by enemy air defense systems, and "cold planning" of the CRAB is carried out, using only the planning module, without turning on the jet engines of the MLRS and SAM shells to a low flight altitude that makes detection by air defense systems difficult, at which, depending on the distance to the target, the rocket engines of the MLRS and SAM shells are turned on one by one or all at once, which allows the CRAB, when turning on the jet engines of the MLRS and SAM shells already in the cruise missile mode, including at low altitudes, repeating the folds of the terrain with control by altitude and direction, to deliver pinpoint missile and bomb strikes against ground or surface stationary or moving enemy targets.

The second tactical variant of the CRAB operation according to point 4 of the formula, when after being dropped from a carrier aircraft at an altitude of 10-13 km or more, at a safe distance from being hit by enemy air defense systems, the rotary wing 18 is turned to the flight position across the SAM axis Fig. 10 as part of the planning module and the activation of all or one by one of the rocket engines of the MLRS projectiles, which allows the CRAB, when the jet engines of the MLRS projectiles are activated in the cruise missile mode, to gain an additional higher flight altitude and, after turning off all the rocket engines of the MLRS projectiles from a higher point in the flight, to switch to the CRAB "cold planning" mode, using only the planning module and the SAM flight control system, which also allows to increase the target engagement distance, and already at a low flight altitude, on command from the SAM control unit, the SAM cruise rocket engine is activated, which in the guided cruise missile mode is capable of, at low altitudes, repeating the folds of the terrain with control by altitude and direction, delivering pinpoint missile and bomb strikes against ground or surface stationary or moving enemy targets.

The third tactical variant of the CRAB operation according to paragraph 5 of the formula is advisable to use for the destruction of enemy air defense systems, according to the "live bait hunting" principle, when after the simultaneous release of two CRABs from a carrier aircraft at an altitude of 10-13 km or more, at a safe distance from destruction by enemy air defense systems, the first tactical variant of the CRAB operation according to paragraph 3 of the formula is carried out for one CRAB, and the second tactical variant of the CRAB operation according to paragraph 4 of the formula is carried out for the other CRAB, which allows us to assume with a high degree of probability that the CRAB will be attacked by enemy air defense systems, with the activation of all or one by one the rocket engines of the MLRS projectiles in the cruise missile mode, and the other CRAB, implementing the "cold gliding" mode of the CRAB, without the activation of the rocket engines of the MLRS projectiles, will not be attacked by enemy air defense systems and, accordingly, after detecting the coordinates of the active enemy air defense systems, will be able to destroy the target according to the detected coordinates according to the first tactical variant of the CRAB operation.

Obviously, there may be other combinations based on the described tactical options for the operation of the CRAB, depending on the tasks set for the use of the CRAB with the installation or absence of standard or special fuses for MLRS shells as part of the CRAB, as well as a different number and types of shells for the MLRS. It is also possible to use the CRAB to engage air targets in a contactless manner by detonating a volumetric explosion munition below the air target, when the engines of the air target simply turn off due to the burning of oxygen in a large volume of the atmosphere.

The operating algorithm of other versions of the CRAB and with other options for functioning and configuration, as well as a different number and types of shells for MLRS and SAMs, as well as with an additional source of electricity such as a wind generator or without it, are similar to those described above.

Due to the above, the invention achieves a technical result consisting in the creation of a Combined Air-to-Surface Jet Aircraft Munition containing a gliding module, ready-made industrially produced MLRS rocket projectiles and an anti-aircraft guided missile (SAM), combined into a common structure with additional fastening fittings, allowing, after launch from a carrier aircraft, to carry out a controlled flight using a gliding module, in range, speed, altitude and direction, with sequential and/or simultaneous activation of the MLRS projectile jet engines and the anti-aircraft guided missile (SAM) jet engine, during flight, including at low altitudes, following the folds of the terrain with control in altitude and direction, for delivering pinpoint missile and bomb strikes against ground or surface stationary or moving enemy targets.

Literature:

1. Vasily N.Ya., Gurinovich A.L. Anti-aircraft missile systems, p. 251.

2. Angelskiy R. Long-range salvo (Russian) // Equipment and weapons yesterday, today and tomorrow: magazine. - 2003. - March (No. 3). - P. 2-9.

Claims (5)

1. A combined jet aircraft munition (CRAB), characterized by the fact that it includes a planning module, four ready-made serially produced industrial unguided MLRS rockets and one anti-aircraft guided missile (SAM), united into a common structure with additional fastening fittings, allowing, after launch from a carrier aircraft, to carry out a controlled flight in range, speed, altitude and direction, with sequential and/or simultaneous activation of the jet engines of the MLRS projectiles and the jet engine of the anti-aircraft guided missile (SAM), during flight, including at low altitudes, following the folds of the terrain with control in altitude and direction, for delivering pinpoint missile and bomb strikes against ground or surface stationary or moving enemy targets, using the standard SAM guidance and flight control system. 2. A combined jet aviation munition according to paragraph 1, characterized in that it has an additional source of electrical energy in the form of at least one wind generator. 3. The method of operation of the Combined Jet Air Munition (KRAB), in which, after being dropped from a carrier aircraft at an altitude of 10-13 km or more at a safe distance from being hit by enemy air defense systems, the KRAB undergoes “cold gliding” using only the gliding module, without activating the jet engines of the MLRS and SAM shells, to a low altitude that makes detection by air defense systems difficult, at which, depending on the distance to the target, the rocket engines of the MLRS and SAM shells are activated one by one or all at once, which allows the KRAB, when the jet engines of the MLRS and SAM shells are activated, already in the cruise missile mode, including at low altitudes, following the folds of the terrain with control by altitude and direction, to deliver pinpoint missile and bomb strikes against ground or surface stationary or moving enemy targets, using the standard guidance and flight control system of the SAM. 4. The method of functioning of the CRAB, in which, after being dropped from a carrier aircraft at an altitude of 10-13 km or more at a safe distance from being hit by enemy air defense systems, all rocket engines of the MLRS projectiles are turned on at once, which allows the CRAB, when the jet engines of the MLRS projectiles are turned on in the cruise missile mode, to gain an additional higher flight altitude and, after turning off all the rocket engines of the MLRS projectiles from a higher point in flight, to switch to the CRAB “cold glide” mode using only the glide module to increase the target engagement distance, and upon reaching a low flight altitude, when the SAM jet engine is turned on, to carry out a controlled flight already in the cruise missile mode, including at low altitudes, following the folds of the terrain with control in altitude and direction, to deliver pinpoint missile and bomb strikes against ground or surface stationary or moving enemy targets, using the standard SAM guidance and flight control system. 5. A method of destroying enemy air defense systems, characterized in that it uses the simultaneous release of two CRABs from a carrier aircraft, for one CRAB the variant of the CRAB operating method according to paragraph 3 is carried out, and for the other CRAB the variant of the CRAB operating method according to paragraph 4 is carried out with the activation of all rocket engines of the MLRS projectiles at once in the cruise missile mode, and the other CRAB, implementing the CRAB "cold gliding" mode, without the activation of the rocket engines of the MLRS projectiles and SAMs, after detecting the coordinates of the active enemy air defense systems, the CRAB, implementing the "cold gliding" mode after aiming at the detected enemy attacking target, will have the ability to destroy the target using the CRAB operating method according to paragraph 3.