Surface-to-air guided missile

Abstract

FIELD: military equipment.SUBSTANCE: invention relates to guided projectiles and missiles, in particular to the structural design of surface-to-air and surface-to-surface guided missiles containing a body, wings, engines, guidance and control system equipment, special software and a current source. A surface-to-air guided missile with a structural and layout appearance according to an X-shaped tiltrotor scheme with the placement of non-rotating nacelles with propellers at the ends of the wings comprises a body, engines with propellers in the nacelles, guidance and control system equipment, special software and a current source. Additional wings are installed on the missile body, located in a plane perpendicular to the longitudinal axis of the missile at an angle of 45° to the main wings with nacelles. Individually controlled electric motors are used to drive the propellers in the nacelles, the rotation axes of which in the nacelles are installed with a mirror multidirectional deviation of their axes relative to the vertical and horizontal planes of symmetry of the missile. Destruction of targets is achieved by kinetic impact on the target by the missile body, the main wings with nacelles, the propellers and the additional wings.EFFECT: increasing the manoeuvrability of the missile and the accuracy of its guidance; achieving a larger area of kinetic destruction of targets; achieving safety of manufacturing, storage and operation of missiles; simplifying the design; reducing the weight of the missile; reducing the cost of manufacturing the missile; enabling the production, storage and operation of missiles at enterprises that do not have a license from the Federal Service for Environmental, Technological and Nuclear Supervision to carry out activities related to the handling of explosive materials.1 cl, 1 dwg

Description

[0001] Field of technology to which the invention relates

[0002] The invention relates to the field of military technology, namely to guided projectiles and missiles, and can be used in the development of anti-aircraft guided projectiles and missiles (SAMs) for intercepting low-speed and hovering mini-class unmanned aerial vehicles, unmanned battlefield reconnaissance and artillery fire adjustment systems, kamikaze drone-type strike vehicles, and unmanned attack boats.

[0003] Technology Level

[0004] There are known ultra-short-range surface-to-air guided missiles, for example, domestic missiles: 9M33, 9M311, 9M330, 9M331, 9M335, 9M338, 9M340, man-portable air defense systems such as 9M333, 9M336, etc., a large number of similar missiles have been developed abroad.

[0005] All of the listed missiles were developed for the task of combating aircraft and helicopters, ships and ground targets, and high-precision weapons: guided aerial bombs and cluster munitions,

[0006] anti-radar, anti-ship and other universal and specialized missiles.

[0007] Despite the high efficiency of hitting the listed classes of targets, a significant drawback of all the listed SAMs is their high cost in serial production, which is incomparable with the price of currently used unmanned aerial vehicles (UAVs) of the "mini" class and unmanned boats (UCB), the high flight speed of the SAM, which limits the near boundary of the engagement zone and, accordingly, combat capabilities in combating UAVs in the tactical depth of the front, the defense of particularly important objects in the depths of the country's territory, UCB in the waters adjacent to ports and naval bases.

[0008] These missiles with varying degrees of deployment are described in: “Arsenal-info.rf”; “Physical principles of the design and functioning of small arms, gun, artillery and missile weapons. Part II. Physical principles of the design and functioning of missile weapons: Textbook for universities / edited by prof. V.V. Vetrov and prof. V.P. Strogalev. - Tula: Publishing house of Tula State University, 2007; “Fakela” missiles, M., MKB “Fakel” named after academician P.D. Grushin, 2003; Analytical review of military-scientific information 3 (152), Research Institute of KiV VMF VUNC VMF “VMA named after Admiral of the Fleet of the Soviet Union N.G. Kuznetsov”, St. Petersburg, 2013; Karpenko A.V. Russian missile weapons 1943-1993, reference book, second edition, St. Petersburg, "PIKA", 1993; Russian air defense aviation and scientific and technological progress: combat complexes and systems yesterday, today, tomorrow, edited by E.A. Fedosov, Moscow, Drofa, 2001; Karpenko AV, VTS, "NEVSKY BASTION", 11.03.2018; "Wings of the Motherland", No. 8, 1993, "Equipment and weapons yesterday, today, tomorrow ..." No. 5-6, 1999; Military information sites: Deagel.com; Guide to Military Equipment, svpressa.ru, bmpd.livejournal.com; dambiev.livejournal.com; www.globalwarnews.ru: military-informant.com; china-inc.ru and others.

[0009] Devices for combating UAVs and unmanned aerial vehicles are known by:

[0010] - installations of ground minefields (RU 198365 U1);

[0011] - installations of ground barriers releasing balloons filled with lighter-than-air gas (RU 191584 U1);

[0012] - spraying a target UAV from an interceptor UAV with quickly hardening drops of polyurethane foam mixtures (RU 208980 U1);

[0013] - destruction by multi-barrel firing modules placed on a quadcopter or on the ground and forming a fragmentation field of continuous destruction of UAVs (RU 222488 U1, RU 213791 U1);

[0014] - damage by grenades on parachutes dropped from UAVs (RU 145279 U1);

[0015] - interception of a UAV with a decoy net of various designs and its release from the board of an interceptor UAV (RU 202673 U1, RU 200588 U1, RU 185949 U1, RU 185949 U1, RU 150610 U1);

[0016] At present, attempts are being made to destroy UAVs with similar UAVs by ramming them in manual control mode.

[0017] The disadvantage of all the listed methods of combating UAVs and UAVs using anti-aircraft missiles is either significantly higher flight speeds of anti-aircraft missiles compared to the target UAV, which significantly limits the effectiveness of intercepting target UAVs (UECs) in real detection ranges, or comparable flight speeds and available overloads of the target UAV (UEC) and the interceptor UAV, in accordance with [“Physical principles of the design and functioning of small arms, artillery and missile weapons. Part II. Physical principles of the design and functioning of missile weapons: Textbook for universities / edited by prof. V.V. Vetrov and prof. V.P. Strogalev. - Tula: Publishing house of Tula State University, 2007] the effectiveness of target interception can be ensured only if the speed and available overloads (at least 1.5 ... 2 times) of the interceptor missile exceed those of the target.

[0018] The technical limitation of using UAVs to intercept UAVs (unmanned aerial vehicles) is the helicopter-based design, using lift solely from the rotors rotating at transonic speeds. This limits the flight speed of all helicopters. While the fixed-wing design allows for higher speeds, it requires a high initial airspeed to generate wing lift (takeoff or ejection).

[0019] To combine the positive properties of the helicopter and aircraft design schemes of aircraft, in the 50s, an aerodynamic scheme of a convertiplane was proposed, made according to a normal aerodynamic scheme with the placement of rotary propeller engines, and later turbojet engines, at the ends of the aerodynamic surfaces, which contains a body, engines, guidance and control system equipment, special software, and the engines are fixed at the ends of the wings on rotary consoles and are equipped with drives for turning the engines from a vertical to a horizontal position (convertiplanes Bell V-22 "Osprey", Bell D-188A, X-22, EWR VJ 101, TsAGI-11EA, Mi-30, Ka-22, ADA TR 4 ... 100, etc.).

[0020] The disadvantage of the considered analogs in relation to the problem of intercepting targets is the aircraft design, which requires a preliminary turn of the aircraft in the bank to turn along the course, a long time of acceleration and reduction of engine thrust, which makes it difficult to use engine thrust for operational control of the direction of flight.

[0021] The design of the V-758 (22D) anti-aircraft missile [“Fakel Missiles”, Moscow, Academician P.D. Grushin “Fakel” Design Bureau, 2003] may be considered as a close analogue of the invention. The missile comprises a body, wings installed according to an X-shaped design and layout, engines attached to the ends of the wings, guidance and control system equipment, special software that ensures a vertical launch of the missile according to a helicopter scheme with subsequent transfer of the missile to horizontal flight using the lifting force of the wings, a safety actuator, a remote detonator, combat equipment and a power source.

[0022] A drawback of the closely related invention, as applied to the problem of intercepting small targets, is the use of ramjet engines on the B-758 missile. This, on the one hand, requires the use of a booster to accelerate the missile to the ramjet's initial firing speed, limiting the near-field target engagement zone. On the other hand, the limited throttle capabilities of ramjet engines prevents their effective use for directional control and necessitates the use of traditional aerodynamic control surfaces to steer the missile toward the target. Limited downwash angles at the ramjet's air intake prevent their operation from surge-free at the significant angles of attack required to achieve the acceleration required for target interception.

[0023] The design of the anti-aircraft missile according to Russian Patent No. RU 2837930 C1 may be considered as a prototype of the invention. The missile comprises a body and wings mounted in an X-shaped configuration with fixed propeller propulsion units located at the ends of the wing consoles. Individually controlled electric motors are used to drive the propellers. A control system with specialized software ensures a vertical launch of the missile using a helicopter configuration and subsequent transition to horizontal flight using the lift of the wings. A homing head, a safety actuator, a remote fuse, combat equipment, and a power source are also included. Pitch and yaw control is achieved by controlling the thrust of the propeller propulsion units, while roll control is achieved by controlling the torque of the propeller propulsion units.

[0024] The disadvantages of the prototype are the limited lateral overloads of the missile when intercepting a target, caused by the small aerodynamic surface of the wings, significant cross-influence of the missile movement control in different planes on each other, the significant mass of the missile associated with the need to carry in its composition a combat load, including a safety-actuating mechanism, a remote detonator and a warhead with explosives and striking elements, as well as significant restrictions on the manufacture, storage and operation of analog missiles and the prototype missile associated with the use of explosives in the missile.

[0025] The purpose of the proposed invention is to expand the combat capabilities of anti-aircraft guided missiles to destroy low-speed and hovering mini-class UAVs deep within enemy combat formations, unmanned aerial vehicles (UAVs) in sea and river waters, counter reconnaissance by such means on the battlefield and artillery fire adjustment, prevent strikes by kamikaze drones and UAVs on ground, coastal and surface targets, and expand the number of enterprises for the manufacture, storage and operation of anti-aircraft guided missiles.

[0026] Disclosure of the essence of the invention

[0027] The essence of the proposed technical solution is that:

[0028] - the design and layout of the rocket, based on the X-shaped convertiplane configuration with the placement of engine nacelles with non-rotating propeller propellers at the ends of the wings, is expanded by the use of additional wings placed in a plane perpendicular to the missile's line axis at an angle of 45° to the main wings with engine nacelles;

[0029] - the axes of rotation of the propeller propellers in the nacelles are installed with a mirror image of their axes in different directions relative to the vertical and horizontal planes of symmetry of the rocket;

[0030] - the missile composition excludes the combat equipment, which includes explosives, striking elements, a safety-actuating mechanism and a remote detonator, necessary for the functioning of the combat equipment;

[0031] - Target destruction is achieved by the kinetic impact of the missile body, the main wings with propeller propeller nacelles and additional wings located at an angle of 45° to the main wings with nacelles.

[0032] The technical result of the proposed technical solution is:

[0033] - increasing the maneuverability of the missile and the accuracy of its targeting by increasing the area of ​​the aerodynamic surfaces and a corresponding increase in the available lateral overloads of the missile, using the propeller thrusters shifted along the axis of action of the forces relative to the vertical and horizontal planes of symmetry of the missile;

[0034] - achieving a larger area of ​​kinetic destruction of targets through the use of additional wings placed at an angle of 45° to the main wings with engine nacelles and covering the space between the main wings;

[0035] - achieving the safety of manufacturing, storage and operation of missiles by eliminating the use of explosives in the composition of the missile;

[0036] - simplification of the design compared to existing anti-aircraft guided missiles and rocket engines;

[0037] - reducing the weight of the missile compared to known ultra-short-range missiles such as 9M33, 9M311, 9M330, 9M331, 9M333, 9M335, 9M336, 9M338, 9M340 by 20...35 times;

[0038] - reducing the cost of manufacturing the missile in comparison with known ultra-short-range missiles such as 9M33, 9M311, 9M330, 9M331, 9M333, 9M335, 9M336, 9M338, 9M340 by 20...25 times with a proportional increase in serial production capacity;

[0039] - ensuring the possibility of production, storage and operation of missiles at enterprises that do not have a license from the Federal Service for Ecological, Technological and Nuclear Supervision to carry out activities related to the handling of explosive materials.

[0040] Brief description of drawings

[0041] Fig. 1. Structural layout diagram of the rocket.

[0042] 1 - optical-electronic homing head (OEGSN);

[0043] 2 - nacelles with electric motors and propeller propellers;

[0044] 3 - main wings;

[0045] 4 - additional aerodynamic surfaces - wings.

[0046] Implementation of the invention

[0047] The invention is implemented by:

[0048] - the use of non-rotating propeller propellers at the ends of the wings according to the design and layout scheme of an X-shaped convertiplane and the use of additional aerodynamic surfaces - wings located at an angle of 45° between the main wings with engine nacelles;

[0049] - by applying a shift in the axis of application of the propeller thrusters relative to the vertical and horizontal planes of symmetry of the rocket;

[0050] - propeller drive with individually controlled electric motors of greater power;

[0051] - destruction of targets by the kinetic impact of the missile body, main wings with propeller engine nacelles and additional wings located at an angle of 45° between the main wings with engine nacelles.

Claims

An anti-aircraft guided missile with the structural and layout appearance of an X-shaped convertiplane with the placement of non-rotating engine nacelles with propeller propellers at the ends of the wings, comprising a body, engines with propeller propellers in the engine nacelles, guidance and control system equipment, special software and a power source, characterized in that additional wings are mounted on the missile body, located in a plane perpendicular to the missile's combat axis at an angle of 45° to the main wings with engine nacelles, individually controlled electric motors are used to drive the propeller propellers in the engine nacelles, the axes of rotation of which in the engine nacelles are installed with a mirror image of the multidirectional deviation of their axes relative to the vertical and horizontal planes of symmetry of the missile, the destruction of targets is achieved by the kinetic impact on the target of the missile body, the main wings with engine nacelles, propeller propellers and additional wings.

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