"Wasp" autonomous self-propelled anti-aircraft missile system
The development of an autonomous troop self-propelled anti-aircraft missile complex "Osa" (ind. 9К33, at the development stage of the TTT complex was given the name "Ellipsoid") was initiated in accordance with the Decree of the Council of Ministers of the USSR from 27.10.1960. The complex was designed to hit targets flying from 50-100 to 5000 meters at speeds up to 500 meters per second at ranges from 800-1000 m to 8000-10000 m. For the first time, the task was to develop an autonomous complex with accommodation on one floating self-propelled chassis not only of all combat weapons, including a missile launcher and radar stations, but also means of control, navigation, topographic binding, communications, and power sources. The new requirements also included the detection of air targets in motion with a further defeat by their fire during short stops.
The mass of the anti-aircraft guided missile is no more than 60-65 kilogram, which allowed the launcher to be manually charged by two military personnel.
The main purpose of the complex is to cover the means and forces of motorized rifle divisions from low-flying targets.
The same Decree asked the development of the Osa-M shipborne anti-aircraft missile system using part of the radio-electronic means and the Osa missile system.
Work on the complex "Wasp" was not easy. If the failures during the development of the Kub anti-aircraft missile system cost the two chief designers of the positions they occupied, then when designing the Wasps, they changed not only the chief designers, but also the organizations that developed the chassis of the self-propelled unit and the rocket.
The lead developer of the anti-aircraft missile system as a whole and the 9А33 combat vehicle have determined the NERC-NNXX. The chief designer of the machine and the complex is Kosichkin MM.
The development of the rocket was entrusted to the design bureau of the plant No. 82 of the Moscow City Narkhoz (head Potopalov AV). At the beginning of the 1950's This plant was the first in the USSR to master the mass production of anti-aircraft missiles, developed by the Lavochkin team, for the first-born of the country's anti-aircraft missile forces, Sistema-25. It was assumed that, like other design bureaus previously created at the factories and at the end of the 1950s that switched to independent design, the Potopalov design bureau would be able to create an anti-aircraft guided missile with the required characteristics.
As in the case of the PU of the Kub complex, the development of the combat vehicle was entrusted to SKB-203 of the Sverdlovsk Economic Council under the leadership of A. Yaskin.
The definition of the concept of building an Osa anti-aircraft missile system was significantly influenced by data on the creation of the Mauler self-propelled self-propelled air defense system in the United States with the installation of all means on the M-113 tracked multipurpose armored personnel carrier chassis, widely implemented at that time. We note that the Americans, ultimately, did not succeed in creating this complex.
The brilliant successes achieved in the USSR at the end of 1950-s in the development of wheeled all-terrain vehicles (mainly under the guidance of Grachev V.A.) determined the choice of one of the models of floating armored personnel carriers that were designed for motorized rifle parts by several design teams at the end of 50's - early 60's.
In January, the design bureau of the ZIL plant refused to participate in the Osa complex, since the carrying capacity of the developed ZIL-1961 chassis (153 tons) to accommodate the systems of the complex and the missile launcher was clearly insufficient. Insufficient payload caused the rejection of the winner of the competition for armored personnel carriers - the BTR-1,8P developed by the Gorky Automobile Plant. Several subsequent years of work were carried out in relation to the 60 object wheeled chassis, created on the basis of the 1040 object armored personnel carrier developed at the design bureau of the Kutaisi Automobile Plant of the Council of Soviet Socialist Soviet Socialist Republic in cooperation with specialists of the Military Academy of Armored Forces.
In 1961, they launched the advance design of the Osa anti-aircraft missile system, which identified the main TTT solutions and missile characteristics, as well as the complex as a whole.
Already at the stage of the preliminary project, alarming signs of disconnection of indicators of elements of the complex and the rocket developed by different organizations were identified.
Initially, for a rocket, similarly to the “Kub” complex, a semi-active radar homing head was adopted. GOS and autopilot were combined into a multifunctional unit. The weight of this most important element of the onboard equipment was exceeded 1,5 times in comparison with the given weight and reached 27 kilograms. In general, according to GRAU, the use of such a homing head was not sufficiently justified compared to the option of a radio command system having an infrared homing head, was also considered in the advance project.
The large “funnel” of the dead zone, which reached 14 thousand meters in diameter at 5 thousand meters height, made the anti-aircraft complex vulnerable from aircraft attacks, which operate at medium altitudes, followed by a dive on the target.
The characteristics of the propulsion system incorporated in the design of the zenith controlled complex also turned out to be unrealistic. Designers already at an early stage abandoned the use of a ramjet engine - in relatively small rockets this engine did not provide advantages over the conventional solid-fuel engine. But even for solid-propellant jet engines, the technology of those years did not ensure the creation of fuel formulations with the necessary energy. Instead of the required specific impulse 250 kg × s / s using fuel developed by SRI-9, only 225-235 kg × s / s was provided, and the developed GIPH was provided with 235-240 kg s / s.
On the combat vehicle, it was necessary to install complex facilities with a total weight of 4,3..6 tons, which significantly exceeded the carrying capacity of an BTR-type wheeled chassis.
The main characteristics of the OSA air defense missile system according to the developer’s project materials are presented below in comparison with the customer’s requirements and the technical characteristics of the American Mauler air defense missile system declared at the beginning of the 1960s.
Comparative characteristics of the projects of anti-aircraft missile systems "Osa" and "Mauler"
Maximum range:
"Wasp" on TTT - 8-10 km;
"Wasp" on the project - 8 km;
"Mauler" - 8 km;
Minimum range:
"Wasp" on TTT - 0,8-1 km;
"Wasp" on the project - 1-1,2 km;
"Mauler" - 1-1,5 km;
Maximum height - 5000 m (for all variants);
Minimum height:
"Wasp" on TTT - 50-100 m;
"Wasp" on the project - 100 m;
"Mauler" - 100 m;
Parameter:
“Wasp” on TTT - up to 4 km;
"Wasp" on the project - up to 5 km;
"Mauler" - up to 5 km;
The probability of hitting one anti-aircraft guided missile targets such as the MiG-15:
"Wasp" on TTT - 0,5-0,7;
"Wasp" on the project - 0,3-0,5;
The probability of hitting one anti-aircraft guided missile targets such as IL-28:
"Wasp" on TTT - 0,5-0,7;
Target speed:
"Wasp" on TTT - 500 m / s;
"Wasp" on the project - 500 m / s;
"Mauler" - 660 m / s;
Mass of the complex:
"Wasp" on the project - 13,5 t;
"Mauler" - 27 t;
Chassis weight:
"Wasp" on the project - 10,0 t;
Rocket weight:
"Wasp" on TTT - 60-65 kg;
"Wasp" on the project - 65 kg;
Weight of the warhead:
"Wasp" on the project - 10,7 kg;
"Mauler" - 9,0 kg;
Rocket length:
"Wasp" on TTT - 2,25-2,65 m;
"Wasp" on the project - 2,65 m;
"Mauler" - 1,95 m;
Rocket diameter:
"Wasp" on the project - 0,18 m;
"Mauler" - 0,14 m.
In connection with the problem of the technical characteristics of the components of the complex and the missile by the decision of the MIC, they have released an addendum to the draft design. At this stage, they abandoned semi-active radar homing and switched to radio command guidance. The maximum damage range in this case was 7700 m instead of the specified 8-10 thousand meters. The required upper limit of the affected area was provided only for targets at transonic speeds.
Since, according to the project, the Kutaisi plant’s armored personnel carrier had a tonnage of 3,5 tons, it was decided to eliminate machine gun armament and use light 4,3-strong diesel engine instead of the same 180 hp used on the prototype. The MMZ-220 wheeled chassis of the Mytishchi plant was also considered, but its use was associated with an unacceptable increase in the weight of the air defense missile system to 560 tons.
In 1962, they released those. the project of the complex, however, the works were actually at the stage of experimental laboratory testing of the systems of the complex.
In 1963, the first non-standard missile mock-ups were made, but it was not possible to prepare any experimental anti-aircraft guided missile with a two-stage engine for autonomous testing. Due to the failure of the specific impulse setpoint to be reached, the weight of the fuel charge was exceeded by 2 kilograms. The launch weight of the missile with the weight of the warhead in 9,5 kg was 70 kilogram instead of 60-65 kilogram given in tactical and technical requirements. The solid propellant charge developed by the Scientific Research Institute-9 GKOT was not installed, the charge testing in the GIPH was bad. To improve performance, the replacement of a balloon-balloon with a powder pressure accumulator was worked out.
368 and SRI-20, instead of 67, only seven onboard equipment were made; a prototype of a radar station at SRI-20 was not prepared for the specified period (3 of 1962).
In addition, the Kutaisi plant chassis weight exceeded by 350 a kilogram in comparison with the value presented in the technical project - 9000 kg. As a result, the transportability of the An-12 aircraft was excluded.
In KB-81, the timing of a two-stage solid-fuel jet engine was disrupted. The engine provided for the use of 31,3-kilogram combined charge, manufactured by the method of pass-through pressing. A telescopic scheme was used in the starting charge, and a simple single-channel scheme was used in the march. SRI-9 developed a TMPK formulation - a mixture of polyvinylbutadiene and ammonium perchlorate. The specific impulse was less than the specified kgf / kg for 17. To get out of the current situation, the design bureau of the plant No. 82 began developing an engine of its own design on a fuel developed by the GIPH with a mass of charge 36 kg. The charge was made by the method of free casting. The specific impulse for this more promising formulation was to reach the required level.
Although the creation of radio-electronic means for the air defense missile system was relatively successful, the development of ground equipment was lagging behind. In NII-20, they did not supply and complete the chassis for equipment saturation with electric power equipment.
As a result, neither the joint nor the factory flight tests of the 9М33 SAMs were not commenced in the given period. By the beginning of 1964, only four missile launches with the multifunctional control system MFB-K in open-loop were conducted. Only one launch was successful. 82 set 11 data for the plant, while 118 units were planned.
By the decision of the military industrial complex No. 11 from 08.01.1964, along with issuing a warning to Kosichkin, Potopalov, as well as the developer of the ship "Osa-M" Malievsky A.P. organized a commission to provide the necessary assistance headed by V. Dzhaparidze, head of the Scientific Research Institute-2 GKAT. Inclusion in the commission of the chief designer of the anti-aircraft missile system for the Air Defense Forces Raspletina A.A. and the developer of missiles for these complexes Grushin PD. identified a very unfavorable outcome for the team Potopalov and him personally.
The failure of the plant design bureau no. 82 predetermined excessive optimism in assessing the prospects for the development of Soviet solid fuels, as well as the elemental base for onboard instrumentation of control systems. In those years, the principal feasibility of a radio-controlled anti-aircraft missile with a launch weight of 65 kilogram challenged the fact that even the lightest Soviet-made air-to-air missiles weighed at least 83 kilograms. At the same time, the propulsion systems of the air-to-air missiles provided a much smaller speed increment in comparison with the required one for the missile defense system.
According to the results of the commission’s work, a Resolution of the Central Committee of the CPSU and the USSR Council of Ministers of the USSR on 07.09.1964 was prepared, which provided for the release of the Tushinsky Machine-Building Plant (plant No. 82) from work on 9М33. Instead, the OKB-2 GKAT headed by Grushin was connected to the works. The decree establishes a new start date for testing - 2 quarter 1965 of the year. Also adjusted the requirements for the rocket. The value of the starting mass was doubled and brought to a really achievable level - about 115 kilogram. It was prescribed to ensure the defeat of the target with EPR MIG-19, at a distance of 8-10 thousand m, flying at a speed of 500 m / s, at an altitude of 50-100 to 5000 m, and targets flying at subsonic speeds - at altitudes up to 6-7 thousand meters and range to 10-13 thousand meters. The chief designer of the OSA "Osa" instead of Kosichkin was appointed director of the Research Institute-20 Chudakov PM.
The characteristics and technical appearance of the new missiles, as well as the elements of the complex modified for their use, should have been presented in a draft design released in 1964.
The government has set a new deadline for submitting an anti-aircraft missile system for joint tests - 2 quarter 1967 of the year.
Already in 1965, the autonomous tests of the Grushinskaya rocket for the Osa air defense system began. The complex was presented to the Emben polygon (head Ivanov PI) in the second half of the year 1967 for joint testing. However, in July next year, the State Commission, headed by TA Mikitenko. suspended the tests, since they revealed inconsistencies of the presented anti-aircraft missile system to the requirements of the customer in terms of reliability, efficiency, operating time, and the lower boundary of the affected area. It was not possible to eliminate the burn-through of the nozzle block, when launching significant pointing errors were realized. Such shortcomings, as shown by the experience of developing other complexes, were eventually eliminated during the refinement carried out according to test results.
However, the commission found an unacceptable flaw that could not be eliminated without a fundamental reassembly of the BM. With the linear arrangement of the antenna post of radar equipment and launcher at the same level, the shelling of low-flying targets located behind the machine was completely excluded. In addition, the launcher shaded a significant sector of the radar review in front of the machine. This was evident even at the “paper” design stage, but at that time it was not criticized by the customer.
By order of the Council of Ministers of the USSR, a new deadline was set for presenting a modified anti-aircraft missile system for joint tests - the 2 quarter of the 1970 of the year. Director of NIEMI MRP (formerly SRI-20 GKRE) VP Efremov was appointed Chief Designer of "Wasps", and Drize I.M.
Developers were forced to abandon the further use of the already overloaded 1040 object chassis, which did not provide the specified power reserve and combat vehicle speed indicators. In the middle of 1960's. It was considered, however, the MT-LB tracked carrier was rejected. The Commission of the Presidium of the Council of Ministers on military-industrial issues decided to transfer the development using units and assemblies from the ZIL-135ЛМ nodes of the floating 937 wheeled chassis (later Osnova or 5937) to the Osa anti-aircraft missile system to the Bryansk Automobile Plant MAP. Structurally separate launcher and antenna post were combined into a single APU (antenna-launcher).
In March, June 1970 successfully passed factory tests of an anti-aircraft missile system at the Emben test site (head Kirichenko V.D.). In the period from July 1970 to February 1971 joint tests were conducted under the leadership of a state commission headed by M. M. Saveliev. The complex was adopted by 4 in October 1971 of the year by the Decree of the Central Committee of the CPSU and the Council of Ministers of the USSR.
At the same time, the armament of naval ships fleet entered the Osa-M air defense system.
The Osa anti-aircraft missile system (9K33) consisted of: combat vehicle (BM) 9А33B with launch, guidance and reconnaissance equipment with 4 SAM 9М33, transport-charging machine (TZM) 9Т217B with XNX sy with XNX syn XXXXXXXXXXXXXXXXX8B XNUMX XNUMXXXXNUMX XNUMXXXNUMX XNUMXKXNUMX) control mounted on cars.
Transport-charging and combat vehicles were placed on the BAZ-5937 three-axle chassis, which was equipped with a powerful diesel engine, water cannon, navigation, topographic binding, communications, life support and power supply of the complex (power generator for the propulsion engine and gas turbine unit) . Aircraft IL-76 provided air transport. There was also the possibility of transportation by rail within the 02-T gauge.
The target detection radar placed on the BM 9-33B was a coherent-pulse radar station of the centimeter range of circular sight with the antenna stabilized in the horizontal plane. This made it possible to search and detect targets during the movement of the complex. The radar station performed a circular search by rotating the antenna (33 speed of revolution per minute), and by the elevation angle by moving the beam between three positions at each revolution. With a receiver sensitivity of about 10-13 W, pulsed radiation power in 250 kW, beam width in azimuth 1 degree, beam width in elevation - 4 degrees (two lower beam positions) and 19 degrees in the upper position (in elevation) 27 degrees) the station detected a fighter flying at an altitude of 5 thousand meters at a distance of 40 km (at an altitude of 50 m - 27 km). The station had good protection from passive and active interference.
Installed on BM radar tracking target centimeter range with the sensitivity of the receiver 10-13 W, pulsed radiation power in 200 kW, and the beam width 1 degree ensured the capture of the target for automatic tracking at a distance 14 kilometers at 50 meters flight altitude and 23 kilometers at flight altitude 5 thou. M. RMS of auto-tracking of a target by angular coordinates - 0,3 doo, by distance - 3 meter. The station had a system for selection of moving targets, as well as various means of protection against active interference. In the case of strong active interference, tracking was carried out using a radar detection and television optical sight.
In the system of radio command guidance of the Osa air defense system, unlike the Krug system, two sets of medium and wide beams were used to capture and further enter into the beam of the target tracking station two anti-aircraft missiles at launch with a minimum interval (from 3 to 5 seconds ). In addition to the Osa methods used in the Krug complex, when firing at low-flying targets (altitude from 50 to 100 meters), the slides method was used, which provided the guided missile to fly up to the target. This made it possible to reduce missile launch errors on the target and eliminate the triggering of the radio-fuse from the ground.
Anti-aircraft guided missile 9М33 was carried out according to the "duck" scheme. The roll stabilization is absent, therefore, the on-board equipment provides for a command distributor. To reduce the heeling moment created by the impact on the wings of the air flow disturbed by the rudders, the wing unit was performed freely rotating relative to the longitudinal axis. The main units of the rocket - a command radio unit (radio control equipment), a letter responder (radio imaging equipment), an autopilot, an on-board power supply, a radio fuse, a warhead and a safety-actuator - were located in the nose of an anti-aircraft guided missile. In the tail section were the engine, the antennas of the onboard transponder and the command radio unit, as well as the tracers used to accompany the rocket using a television-optical sighting device.
Missile mass - 128 kg, including 15-kilogram warhead. The average speed of a guided missile is 500 m / s. Rocket length - 3158 millimeters, diameter - 206 millimeters, wingspan - 650 millimeters.
The anti-aircraft guided missile did not require pre-launch preparation, with the exception of the installation of onboard radio equipment when charging the launcher.
The complex ensured the destruction of targets moving at a speed of 300 m / s at an altitude of 0,2 to 5 km in the 2,2-3,6 ... 8,5-9 km range (for targets at altitudes of 50-100 meters, the maximum range was reduced to 4-6 kilometers). For supersonic purposes, (speed up to 420 m / s, height 0,2-5 km), the boundary of the affected area is up to 7,1 km. The parameter was 2-4 kilometers.
The Phantom-2 (F-4C) probability of hitting a target calculated by the simulation results as well as combat launches of anti-aircraft guided missiles by a single missile at 50 meters was 0,35-0,4, at heights above 100 meters it increased to 0,42-0,85.
The self-propelled chassis provided the average speed of the ZRK on the dirt roads at night - 25 km / h, in the daytime - 36 km / h at maximum speed on the highway - 80 km / h. Maximum speed afloat - 10 km / h.
The rocket was delivered to the troops in combat readiness. It did not require verification and adjustment work during operation (with the exception of annual procedural checks).
Serial production of combat weapons of the Osa anti-aircraft missile system was organized in:
- Izhevsk Electromechanical Plant MRP (manufactured 9A33B combat vehicles);
- Kirov Machine Building Plant named after the XX Party Congress MAP (produced XUR 9М33).
For the creation of the Osa anti-aircraft missile system, some developers (AM Rozhnov, VV Osipov, and others) were awarded the Lenin Prize. Belokrinitsky B.Z. and others became laureates of the USSR State Prize.
Modernization of the air defense system to increase its combat effectiveness and expansion of the affected area (under the code "Osa-A") was launched in 1971 in accordance with the Resolution of the Central Committee of the CPSU and the USSR Council of Ministers. The completion date is 1974 year. Also, by the decision of the military-industrial complex No. 40 from 07.02.1973, it was entrusted to conduct development work on a variant of the air defense missile system (later called "Osa-K") with an increased number of anti-aircraft guided missiles on a combat vehicle to 6 pcs. with their placement in transport and launch containers. The development of the Osa-A air defense missile system and the Osa-K air defense missile system was completed in 1973 by conducting factory tests of prototypes. In October, the joint decision of MAP, MRP, GRAU provided for the re-equipment of the prototype BM 1973А9BM of the Osa-A anti-aircraft missile system to install a new launching device with six 33М9М33 missiles in transport-launch canisters. In the period from September 2 to February 1974 of the year at the Embeny landfill of the Main University of Ukraine (the landfill leader Vaschenko B.I.) under the leadership of the commission headed by V. Sukhotsky. joint tests of the converted BM 1975A9BM33 complex as part of the 2K9М33 (Osa-AK) complex and the 2М9М33 rocket were conducted. They were adopted in the 2 year.
Compared with the Osa anti-aircraft missile system, the Osa-AK complex had an extended destruction zone.
In BM 9А33БМ2, they changed the structure of the calculating device, improved the accuracy of the control loop, which ensured the missile's guidance on the speed target (500 meters per second instead of 420 in Osa) and maneuvering with overloads to 8 units (instead of 5). Provided the possibility of hitting the target at speeds up to 300 meters per second on catch-up courses. Improved conditions for automatic target tracking in case of passive interference due to the introduction of a mode in the target tracking station of external coherence. Improved overall noise immunity of the complex. Part of the blocks was performed on the new element base, which reduced their mass, dimensions, power consumption and increased reliability.
In the rocket, the radio fuse was finalized by introducing into it a two-channel receiver with an autonomous height analysis scheme at the moment of arming. This ensured a failure of the radio fuse from the ground at altitudes up to 27 meters. Since the missile defense system was located in a container, it was equipped with a wing having a disclosure mechanism after the start. The upper and lower console in the transport position evolved towards. Before the start, the rear and front covers of the container opened and, rotating about the attachment axes, rose.
The warranty period was increased from 1 to 5 years. The radiation resistance of the rocket increased.
The combat effectiveness of the Osa-AK air defense missile system, depending on the position of the missile attack site and the target in the affected area, was 0,5-0,85.
However, the Osa-AK anti-aircraft missile system could not effectively combat fire support helicopters - the main modern means of destruction tanks. The elimination of this significant drawback was carried out during the execution of the Mara experimental design work, which was started in November 1975 in accordance with the Resolution of the Central Committee of the CPSU and the Council of Ministers of the USSR. Factory tests of the upgraded BM 9A33BM2 equipped with 9M33M2 missiles were carried out in 1977. According to the results of these tests, the rocket was finalized in terms of the electrical circuit and radio fuse. The new anti-aircraft guided missile tribute name 9M33MZ. State tests of the modernized version of the Osa-AKM complex (9K33MZ) were carried out at the Embensky training ground in September-December 1979 (the training ground manager VV Zubarev) under the leadership of a commission headed by A. Zubenko In 1980, the Osa-AKM air defense system was adopted.
When firing at helicopters at an altitude of less than 25 meters, the complex used a special method of guiding an anti-aircraft guided missile with semi-automatic tracking of targets at angular coordinates using a television-optical reticle.
The 9A33BM3 combat vehicle implemented the following activities:
- due to the introduction of an additional scale, they improved the resolution of the indicator of a circular view of the target detection station in azimuth and range;
- due to the refinement of the computational instrument, they implemented a method for guiding an anti-aircraft guided missile with a large angular advance of the target at the vertical plane to the rocket. This reduced the likelihood of a radio-fuse triggering from hitting the ground and reducing the effect of signal fluctuations along the channel on the pointing accuracy;
- increased the flux density of the fragments towards the target. This was achieved by issuing a command to forcibly undermine a warhead when an anti-aircraft guided missile approaches the target;
- ensured the issuance on the rocket of the correction team of the trigger area of the radio-fuse according to the area of the fragmentation of the warhead during fire.
The 9М33М3 rocket differed from a serial anti-aircraft guided missile by a modified radio fuse.
The modified anti-aircraft missile system compared with a serial sample had the ability to destroy helicopters hovering at almost zero altitude and flying at speeds up to 80 m / s at distances from 2000 to 6500 m with course heading to 6000 m.
The probability of a Hugh-Cobra-type helicopter being on the ground was 0,07-0,12 flying at an altitude of 10 meters - 0,12-0,55, hovering at an altitude of 10 meters - 0,12-0,38.
The Osa complex, as well as all its modifications, were in service with motorized rifle divisions as part of anti-aircraft missile regiments. Each regiment "Wasp", as a rule, consisted of five batteries and a regiment command post with a control battery. The battery consisted of four Osa complexes (combat vehicles) and a battery commander station equipped with a PU-12 control center. The regiment control battery included the control point PU-12 (M) and the detection radar P-15 (-19).
The operation of the combat equipment of the complex was provided by the use of TZM 9Т217, 9ВХNUMX adjustment machines, machines of those. maintenance of 914В9, group spare parts 210Ф9, automated control and test testing stations 372В9, as well as ground equipment complex 242Ф9.
Through external economic channels, the Osa anti-aircraft missile system was shipped to the Warsaw Pact member countries, India, Iraq and other states of the Middle East, Asia and Africa. In total, the OSA was adopted for use in 25 countries.
At relatively short ranges in anti-aircraft missile systems, a high energy ratio of the signal reflected from the target to the interference was ensured, which made it possible even with intense interference to use radar channels to detect and track targets, and to suppress the television-optical sight. SAM "Osa" in terms of noise immunity surpassed any military anti-aircraft complex of the first generation. In this regard, when using the Osa complexes during the fighting in southern Lebanon in the early 1980s, the enemy widely used various tactical methods, which reduced the combat effectiveness of the complex, in addition to electronic countermeasures. For example, a mass launch of unmanned aerial vehicles simulating combat aircraft was used, followed by an attack aviation at the position of the air defense systems that have spent their ammunition.
Before the “Storm in the Desert” the special forces of the multinational forces, using helicopters, penetrated into Kuwait, captured and took out the Osa anti-aircraft missile system with all the technical documentation. In addition, the crew was captured, which consisted of the Iraqi military.
According to media reports, at the beginning of 1991, during the hostilities, the Iraqi Osa anti-aircraft missile system shot down an American cruise missile.
On the basis of the Osa missiles, the Saman target has recently been developed for use on highways up to 16 kilometers, which simulates a target with 0,08-1,6 2 ESR.
The main characteristics of the Osa anti-aircraft missile systems:
The name - "Osa" / "Osa-AK" / "Osa-AKM";
Range of damage - 2..9 / 1,5..10 / 1,5..10 km;
Height affected area - 0,05..5 / 0,025..5 / 0,025..5 km;
The affected area by parameter is 2-6 / 2-6 / 2-6 km;
The probability of hitting a fighter with one anti-aircraft guided missile 0,35..0,85 / 0,5..0,85 / 0,5..0,85;
The maximum speed of the targeted targets is up to 420 / up to 500 / up to 500 m / s;
Reaction time - 26..34 / 27..39 / 27..39 with
The speed of the anti-aircraft guided missile - 500 m / s;
Missile mass - 128 kg;
The mass of the warhead - 15 kg;
Deployment / collapse time - 3..5 min .;
The number of target channels - 1;
The number of anti-aircraft missiles on a combat vehicle - 4 / 6 / 6;
Year of adoption - 1972 / 1975 / 1980.
The mass of the anti-aircraft guided missile is no more than 60-65 kilogram, which allowed the launcher to be manually charged by two military personnel.
The main purpose of the complex is to cover the means and forces of motorized rifle divisions from low-flying targets.
The same Decree asked the development of the Osa-M shipborne anti-aircraft missile system using part of the radio-electronic means and the Osa missile system.
Work on the complex "Wasp" was not easy. If the failures during the development of the Kub anti-aircraft missile system cost the two chief designers of the positions they occupied, then when designing the Wasps, they changed not only the chief designers, but also the organizations that developed the chassis of the self-propelled unit and the rocket.
The lead developer of the anti-aircraft missile system as a whole and the 9А33 combat vehicle have determined the NERC-NNXX. The chief designer of the machine and the complex is Kosichkin MM.
The development of the rocket was entrusted to the design bureau of the plant No. 82 of the Moscow City Narkhoz (head Potopalov AV). At the beginning of the 1950's This plant was the first in the USSR to master the mass production of anti-aircraft missiles, developed by the Lavochkin team, for the first-born of the country's anti-aircraft missile forces, Sistema-25. It was assumed that, like other design bureaus previously created at the factories and at the end of the 1950s that switched to independent design, the Potopalov design bureau would be able to create an anti-aircraft guided missile with the required characteristics.
As in the case of the PU of the Kub complex, the development of the combat vehicle was entrusted to SKB-203 of the Sverdlovsk Economic Council under the leadership of A. Yaskin.
The definition of the concept of building an Osa anti-aircraft missile system was significantly influenced by data on the creation of the Mauler self-propelled self-propelled air defense system in the United States with the installation of all means on the M-113 tracked multipurpose armored personnel carrier chassis, widely implemented at that time. We note that the Americans, ultimately, did not succeed in creating this complex.
The brilliant successes achieved in the USSR at the end of 1950-s in the development of wheeled all-terrain vehicles (mainly under the guidance of Grachev V.A.) determined the choice of one of the models of floating armored personnel carriers that were designed for motorized rifle parts by several design teams at the end of 50's - early 60's.
In January, the design bureau of the ZIL plant refused to participate in the Osa complex, since the carrying capacity of the developed ZIL-1961 chassis (153 tons) to accommodate the systems of the complex and the missile launcher was clearly insufficient. Insufficient payload caused the rejection of the winner of the competition for armored personnel carriers - the BTR-1,8P developed by the Gorky Automobile Plant. Several subsequent years of work were carried out in relation to the 60 object wheeled chassis, created on the basis of the 1040 object armored personnel carrier developed at the design bureau of the Kutaisi Automobile Plant of the Council of Soviet Socialist Soviet Socialist Republic in cooperation with specialists of the Military Academy of Armored Forces.
In 1961, they launched the advance design of the Osa anti-aircraft missile system, which identified the main TTT solutions and missile characteristics, as well as the complex as a whole.
Already at the stage of the preliminary project, alarming signs of disconnection of indicators of elements of the complex and the rocket developed by different organizations were identified.
Initially, for a rocket, similarly to the “Kub” complex, a semi-active radar homing head was adopted. GOS and autopilot were combined into a multifunctional unit. The weight of this most important element of the onboard equipment was exceeded 1,5 times in comparison with the given weight and reached 27 kilograms. In general, according to GRAU, the use of such a homing head was not sufficiently justified compared to the option of a radio command system having an infrared homing head, was also considered in the advance project.
The large “funnel” of the dead zone, which reached 14 thousand meters in diameter at 5 thousand meters height, made the anti-aircraft complex vulnerable from aircraft attacks, which operate at medium altitudes, followed by a dive on the target.
The characteristics of the propulsion system incorporated in the design of the zenith controlled complex also turned out to be unrealistic. Designers already at an early stage abandoned the use of a ramjet engine - in relatively small rockets this engine did not provide advantages over the conventional solid-fuel engine. But even for solid-propellant jet engines, the technology of those years did not ensure the creation of fuel formulations with the necessary energy. Instead of the required specific impulse 250 kg × s / s using fuel developed by SRI-9, only 225-235 kg × s / s was provided, and the developed GIPH was provided with 235-240 kg s / s.
On the combat vehicle, it was necessary to install complex facilities with a total weight of 4,3..6 tons, which significantly exceeded the carrying capacity of an BTR-type wheeled chassis.
The main characteristics of the OSA air defense missile system according to the developer’s project materials are presented below in comparison with the customer’s requirements and the technical characteristics of the American Mauler air defense missile system declared at the beginning of the 1960s.
Comparative characteristics of the projects of anti-aircraft missile systems "Osa" and "Mauler"
Maximum range:
"Wasp" on TTT - 8-10 km;
"Wasp" on the project - 8 km;
"Mauler" - 8 km;
Minimum range:
"Wasp" on TTT - 0,8-1 km;
"Wasp" on the project - 1-1,2 km;
"Mauler" - 1-1,5 km;
Maximum height - 5000 m (for all variants);
Minimum height:
"Wasp" on TTT - 50-100 m;
"Wasp" on the project - 100 m;
"Mauler" - 100 m;
Parameter:
“Wasp” on TTT - up to 4 km;
"Wasp" on the project - up to 5 km;
"Mauler" - up to 5 km;
The probability of hitting one anti-aircraft guided missile targets such as the MiG-15:
"Wasp" on TTT - 0,5-0,7;
"Wasp" on the project - 0,3-0,5;
The probability of hitting one anti-aircraft guided missile targets such as IL-28:
"Wasp" on TTT - 0,5-0,7;
Target speed:
"Wasp" on TTT - 500 m / s;
"Wasp" on the project - 500 m / s;
"Mauler" - 660 m / s;
Mass of the complex:
"Wasp" on the project - 13,5 t;
"Mauler" - 27 t;
Chassis weight:
"Wasp" on the project - 10,0 t;
Rocket weight:
"Wasp" on TTT - 60-65 kg;
"Wasp" on the project - 65 kg;
Weight of the warhead:
"Wasp" on the project - 10,7 kg;
"Mauler" - 9,0 kg;
Rocket length:
"Wasp" on TTT - 2,25-2,65 m;
"Wasp" on the project - 2,65 m;
"Mauler" - 1,95 m;
Rocket diameter:
"Wasp" on the project - 0,18 m;
"Mauler" - 0,14 m.
In connection with the problem of the technical characteristics of the components of the complex and the missile by the decision of the MIC, they have released an addendum to the draft design. At this stage, they abandoned semi-active radar homing and switched to radio command guidance. The maximum damage range in this case was 7700 m instead of the specified 8-10 thousand meters. The required upper limit of the affected area was provided only for targets at transonic speeds.
Since, according to the project, the Kutaisi plant’s armored personnel carrier had a tonnage of 3,5 tons, it was decided to eliminate machine gun armament and use light 4,3-strong diesel engine instead of the same 180 hp used on the prototype. The MMZ-220 wheeled chassis of the Mytishchi plant was also considered, but its use was associated with an unacceptable increase in the weight of the air defense missile system to 560 tons.
In 1962, they released those. the project of the complex, however, the works were actually at the stage of experimental laboratory testing of the systems of the complex.
In 1963, the first non-standard missile mock-ups were made, but it was not possible to prepare any experimental anti-aircraft guided missile with a two-stage engine for autonomous testing. Due to the failure of the specific impulse setpoint to be reached, the weight of the fuel charge was exceeded by 2 kilograms. The launch weight of the missile with the weight of the warhead in 9,5 kg was 70 kilogram instead of 60-65 kilogram given in tactical and technical requirements. The solid propellant charge developed by the Scientific Research Institute-9 GKOT was not installed, the charge testing in the GIPH was bad. To improve performance, the replacement of a balloon-balloon with a powder pressure accumulator was worked out.
368 and SRI-20, instead of 67, only seven onboard equipment were made; a prototype of a radar station at SRI-20 was not prepared for the specified period (3 of 1962).
In addition, the Kutaisi plant chassis weight exceeded by 350 a kilogram in comparison with the value presented in the technical project - 9000 kg. As a result, the transportability of the An-12 aircraft was excluded.
In KB-81, the timing of a two-stage solid-fuel jet engine was disrupted. The engine provided for the use of 31,3-kilogram combined charge, manufactured by the method of pass-through pressing. A telescopic scheme was used in the starting charge, and a simple single-channel scheme was used in the march. SRI-9 developed a TMPK formulation - a mixture of polyvinylbutadiene and ammonium perchlorate. The specific impulse was less than the specified kgf / kg for 17. To get out of the current situation, the design bureau of the plant No. 82 began developing an engine of its own design on a fuel developed by the GIPH with a mass of charge 36 kg. The charge was made by the method of free casting. The specific impulse for this more promising formulation was to reach the required level.
Although the creation of radio-electronic means for the air defense missile system was relatively successful, the development of ground equipment was lagging behind. In NII-20, they did not supply and complete the chassis for equipment saturation with electric power equipment.
As a result, neither the joint nor the factory flight tests of the 9М33 SAMs were not commenced in the given period. By the beginning of 1964, only four missile launches with the multifunctional control system MFB-K in open-loop were conducted. Only one launch was successful. 82 set 11 data for the plant, while 118 units were planned.
The layout of the 9M33 SAM "Osa". 1. 2 radio fuse transmitter. Steering machine 3. 4 power supply. Air pressure accumulator 5. 6 radio fuse receiver. 7 radio control equipment. Autopilot 8. Warhead 9. RDTT 10. Stabilizer hinge
By the decision of the military industrial complex No. 11 from 08.01.1964, along with issuing a warning to Kosichkin, Potopalov, as well as the developer of the ship "Osa-M" Malievsky A.P. organized a commission to provide the necessary assistance headed by V. Dzhaparidze, head of the Scientific Research Institute-2 GKAT. Inclusion in the commission of the chief designer of the anti-aircraft missile system for the Air Defense Forces Raspletina A.A. and the developer of missiles for these complexes Grushin PD. identified a very unfavorable outcome for the team Potopalov and him personally.
The failure of the plant design bureau no. 82 predetermined excessive optimism in assessing the prospects for the development of Soviet solid fuels, as well as the elemental base for onboard instrumentation of control systems. In those years, the principal feasibility of a radio-controlled anti-aircraft missile with a launch weight of 65 kilogram challenged the fact that even the lightest Soviet-made air-to-air missiles weighed at least 83 kilograms. At the same time, the propulsion systems of the air-to-air missiles provided a much smaller speed increment in comparison with the required one for the missile defense system.
According to the results of the commission’s work, a Resolution of the Central Committee of the CPSU and the USSR Council of Ministers of the USSR on 07.09.1964 was prepared, which provided for the release of the Tushinsky Machine-Building Plant (plant No. 82) from work on 9М33. Instead, the OKB-2 GKAT headed by Grushin was connected to the works. The decree establishes a new start date for testing - 2 quarter 1965 of the year. Also adjusted the requirements for the rocket. The value of the starting mass was doubled and brought to a really achievable level - about 115 kilogram. It was prescribed to ensure the defeat of the target with EPR MIG-19, at a distance of 8-10 thousand m, flying at a speed of 500 m / s, at an altitude of 50-100 to 5000 m, and targets flying at subsonic speeds - at altitudes up to 6-7 thousand meters and range to 10-13 thousand meters. The chief designer of the OSA "Osa" instead of Kosichkin was appointed director of the Research Institute-20 Chudakov PM.
The characteristics and technical appearance of the new missiles, as well as the elements of the complex modified for their use, should have been presented in a draft design released in 1964.
The government has set a new deadline for submitting an anti-aircraft missile system for joint tests - 2 quarter 1967 of the year.
Already in 1965, the autonomous tests of the Grushinskaya rocket for the Osa air defense system began. The complex was presented to the Emben polygon (head Ivanov PI) in the second half of the year 1967 for joint testing. However, in July next year, the State Commission, headed by TA Mikitenko. suspended the tests, since they revealed inconsistencies of the presented anti-aircraft missile system to the requirements of the customer in terms of reliability, efficiency, operating time, and the lower boundary of the affected area. It was not possible to eliminate the burn-through of the nozzle block, when launching significant pointing errors were realized. Such shortcomings, as shown by the experience of developing other complexes, were eventually eliminated during the refinement carried out according to test results.
However, the commission found an unacceptable flaw that could not be eliminated without a fundamental reassembly of the BM. With the linear arrangement of the antenna post of radar equipment and launcher at the same level, the shelling of low-flying targets located behind the machine was completely excluded. In addition, the launcher shaded a significant sector of the radar review in front of the machine. This was evident even at the “paper” design stage, but at that time it was not criticized by the customer.
By order of the Council of Ministers of the USSR, a new deadline was set for presenting a modified anti-aircraft missile system for joint tests - the 2 quarter of the 1970 of the year. Director of NIEMI MRP (formerly SRI-20 GKRE) VP Efremov was appointed Chief Designer of "Wasps", and Drize I.M.
Developers were forced to abandon the further use of the already overloaded 1040 object chassis, which did not provide the specified power reserve and combat vehicle speed indicators. In the middle of 1960's. It was considered, however, the MT-LB tracked carrier was rejected. The Commission of the Presidium of the Council of Ministers on military-industrial issues decided to transfer the development using units and assemblies from the ZIL-135ЛМ nodes of the floating 937 wheeled chassis (later Osnova or 5937) to the Osa anti-aircraft missile system to the Bryansk Automobile Plant MAP. Structurally separate launcher and antenna post were combined into a single APU (antenna-launcher).
In March, June 1970 successfully passed factory tests of an anti-aircraft missile system at the Emben test site (head Kirichenko V.D.). In the period from July 1970 to February 1971 joint tests were conducted under the leadership of a state commission headed by M. M. Saveliev. The complex was adopted by 4 in October 1971 of the year by the Decree of the Central Committee of the CPSU and the Council of Ministers of the USSR.
At the same time, the armament of naval ships fleet entered the Osa-M air defense system.
The Osa anti-aircraft missile system (9K33) consisted of: combat vehicle (BM) 9А33B with launch, guidance and reconnaissance equipment with 4 SAM 9М33, transport-charging machine (TZM) 9Т217B with XNX sy with XNX syn XXXXXXXXXXXXXXXXX8B XNUMX XNUMXXXXNUMX XNUMXXXNUMX XNUMXKXNUMX) control mounted on cars.
Transport-charging and combat vehicles were placed on the BAZ-5937 three-axle chassis, which was equipped with a powerful diesel engine, water cannon, navigation, topographic binding, communications, life support and power supply of the complex (power generator for the propulsion engine and gas turbine unit) . Aircraft IL-76 provided air transport. There was also the possibility of transportation by rail within the 02-T gauge.
The target detection radar placed on the BM 9-33B was a coherent-pulse radar station of the centimeter range of circular sight with the antenna stabilized in the horizontal plane. This made it possible to search and detect targets during the movement of the complex. The radar station performed a circular search by rotating the antenna (33 speed of revolution per minute), and by the elevation angle by moving the beam between three positions at each revolution. With a receiver sensitivity of about 10-13 W, pulsed radiation power in 250 kW, beam width in azimuth 1 degree, beam width in elevation - 4 degrees (two lower beam positions) and 19 degrees in the upper position (in elevation) 27 degrees) the station detected a fighter flying at an altitude of 5 thousand meters at a distance of 40 km (at an altitude of 50 m - 27 km). The station had good protection from passive and active interference.
Installed on BM radar tracking target centimeter range with the sensitivity of the receiver 10-13 W, pulsed radiation power in 200 kW, and the beam width 1 degree ensured the capture of the target for automatic tracking at a distance 14 kilometers at 50 meters flight altitude and 23 kilometers at flight altitude 5 thou. M. RMS of auto-tracking of a target by angular coordinates - 0,3 doo, by distance - 3 meter. The station had a system for selection of moving targets, as well as various means of protection against active interference. In the case of strong active interference, tracking was carried out using a radar detection and television optical sight.
In the system of radio command guidance of the Osa air defense system, unlike the Krug system, two sets of medium and wide beams were used to capture and further enter into the beam of the target tracking station two anti-aircraft missiles at launch with a minimum interval (from 3 to 5 seconds ). In addition to the Osa methods used in the Krug complex, when firing at low-flying targets (altitude from 50 to 100 meters), the slides method was used, which provided the guided missile to fly up to the target. This made it possible to reduce missile launch errors on the target and eliminate the triggering of the radio-fuse from the ground.
Anti-aircraft guided missile 9М33 was carried out according to the "duck" scheme. The roll stabilization is absent, therefore, the on-board equipment provides for a command distributor. To reduce the heeling moment created by the impact on the wings of the air flow disturbed by the rudders, the wing unit was performed freely rotating relative to the longitudinal axis. The main units of the rocket - a command radio unit (radio control equipment), a letter responder (radio imaging equipment), an autopilot, an on-board power supply, a radio fuse, a warhead and a safety-actuator - were located in the nose of an anti-aircraft guided missile. In the tail section were the engine, the antennas of the onboard transponder and the command radio unit, as well as the tracers used to accompany the rocket using a television-optical sighting device.
Missile mass - 128 kg, including 15-kilogram warhead. The average speed of a guided missile is 500 m / s. Rocket length - 3158 millimeters, diameter - 206 millimeters, wingspan - 650 millimeters.
The anti-aircraft guided missile did not require pre-launch preparation, with the exception of the installation of onboard radio equipment when charging the launcher.
The complex ensured the destruction of targets moving at a speed of 300 m / s at an altitude of 0,2 to 5 km in the 2,2-3,6 ... 8,5-9 km range (for targets at altitudes of 50-100 meters, the maximum range was reduced to 4-6 kilometers). For supersonic purposes, (speed up to 420 m / s, height 0,2-5 km), the boundary of the affected area is up to 7,1 km. The parameter was 2-4 kilometers.
The Phantom-2 (F-4C) probability of hitting a target calculated by the simulation results as well as combat launches of anti-aircraft guided missiles by a single missile at 50 meters was 0,35-0,4, at heights above 100 meters it increased to 0,42-0,85.
The self-propelled chassis provided the average speed of the ZRK on the dirt roads at night - 25 km / h, in the daytime - 36 km / h at maximum speed on the highway - 80 km / h. Maximum speed afloat - 10 km / h.
The rocket was delivered to the troops in combat readiness. It did not require verification and adjustment work during operation (with the exception of annual procedural checks).
Serial production of combat weapons of the Osa anti-aircraft missile system was organized in:
- Izhevsk Electromechanical Plant MRP (manufactured 9A33B combat vehicles);
- Kirov Machine Building Plant named after the XX Party Congress MAP (produced XUR 9М33).
For the creation of the Osa anti-aircraft missile system, some developers (AM Rozhnov, VV Osipov, and others) were awarded the Lenin Prize. Belokrinitsky B.Z. and others became laureates of the USSR State Prize.
Modernization of the air defense system to increase its combat effectiveness and expansion of the affected area (under the code "Osa-A") was launched in 1971 in accordance with the Resolution of the Central Committee of the CPSU and the USSR Council of Ministers. The completion date is 1974 year. Also, by the decision of the military-industrial complex No. 40 from 07.02.1973, it was entrusted to conduct development work on a variant of the air defense missile system (later called "Osa-K") with an increased number of anti-aircraft guided missiles on a combat vehicle to 6 pcs. with their placement in transport and launch containers. The development of the Osa-A air defense missile system and the Osa-K air defense missile system was completed in 1973 by conducting factory tests of prototypes. In October, the joint decision of MAP, MRP, GRAU provided for the re-equipment of the prototype BM 1973А9BM of the Osa-A anti-aircraft missile system to install a new launching device with six 33М9М33 missiles in transport-launch canisters. In the period from September 2 to February 1974 of the year at the Embeny landfill of the Main University of Ukraine (the landfill leader Vaschenko B.I.) under the leadership of the commission headed by V. Sukhotsky. joint tests of the converted BM 1975A9BM33 complex as part of the 2K9М33 (Osa-AK) complex and the 2М9М33 rocket were conducted. They were adopted in the 2 year.
Compared with the Osa anti-aircraft missile system, the Osa-AK complex had an extended destruction zone.
In BM 9А33БМ2, they changed the structure of the calculating device, improved the accuracy of the control loop, which ensured the missile's guidance on the speed target (500 meters per second instead of 420 in Osa) and maneuvering with overloads to 8 units (instead of 5). Provided the possibility of hitting the target at speeds up to 300 meters per second on catch-up courses. Improved conditions for automatic target tracking in case of passive interference due to the introduction of a mode in the target tracking station of external coherence. Improved overall noise immunity of the complex. Part of the blocks was performed on the new element base, which reduced their mass, dimensions, power consumption and increased reliability.
In the rocket, the radio fuse was finalized by introducing into it a two-channel receiver with an autonomous height analysis scheme at the moment of arming. This ensured a failure of the radio fuse from the ground at altitudes up to 27 meters. Since the missile defense system was located in a container, it was equipped with a wing having a disclosure mechanism after the start. The upper and lower console in the transport position evolved towards. Before the start, the rear and front covers of the container opened and, rotating about the attachment axes, rose.
The warranty period was increased from 1 to 5 years. The radiation resistance of the rocket increased.
The combat effectiveness of the Osa-AK air defense missile system, depending on the position of the missile attack site and the target in the affected area, was 0,5-0,85.
However, the Osa-AK anti-aircraft missile system could not effectively combat fire support helicopters - the main modern means of destruction tanks. The elimination of this significant drawback was carried out during the execution of the Mara experimental design work, which was started in November 1975 in accordance with the Resolution of the Central Committee of the CPSU and the Council of Ministers of the USSR. Factory tests of the upgraded BM 9A33BM2 equipped with 9M33M2 missiles were carried out in 1977. According to the results of these tests, the rocket was finalized in terms of the electrical circuit and radio fuse. The new anti-aircraft guided missile tribute name 9M33MZ. State tests of the modernized version of the Osa-AKM complex (9K33MZ) were carried out at the Embensky training ground in September-December 1979 (the training ground manager VV Zubarev) under the leadership of a commission headed by A. Zubenko In 1980, the Osa-AKM air defense system was adopted.
When firing at helicopters at an altitude of less than 25 meters, the complex used a special method of guiding an anti-aircraft guided missile with semi-automatic tracking of targets at angular coordinates using a television-optical reticle.
The 9A33BM3 combat vehicle implemented the following activities:
- due to the introduction of an additional scale, they improved the resolution of the indicator of a circular view of the target detection station in azimuth and range;
- due to the refinement of the computational instrument, they implemented a method for guiding an anti-aircraft guided missile with a large angular advance of the target at the vertical plane to the rocket. This reduced the likelihood of a radio-fuse triggering from hitting the ground and reducing the effect of signal fluctuations along the channel on the pointing accuracy;
- increased the flux density of the fragments towards the target. This was achieved by issuing a command to forcibly undermine a warhead when an anti-aircraft guided missile approaches the target;
- ensured the issuance on the rocket of the correction team of the trigger area of the radio-fuse according to the area of the fragmentation of the warhead during fire.
The 9М33М3 rocket differed from a serial anti-aircraft guided missile by a modified radio fuse.
The modified anti-aircraft missile system compared with a serial sample had the ability to destroy helicopters hovering at almost zero altitude and flying at speeds up to 80 m / s at distances from 2000 to 6500 m with course heading to 6000 m.
The probability of a Hugh-Cobra-type helicopter being on the ground was 0,07-0,12 flying at an altitude of 10 meters - 0,12-0,55, hovering at an altitude of 10 meters - 0,12-0,38.
The Osa complex, as well as all its modifications, were in service with motorized rifle divisions as part of anti-aircraft missile regiments. Each regiment "Wasp", as a rule, consisted of five batteries and a regiment command post with a control battery. The battery consisted of four Osa complexes (combat vehicles) and a battery commander station equipped with a PU-12 control center. The regiment control battery included the control point PU-12 (M) and the detection radar P-15 (-19).
The operation of the combat equipment of the complex was provided by the use of TZM 9Т217, 9ВХNUMX adjustment machines, machines of those. maintenance of 914В9, group spare parts 210Ф9, automated control and test testing stations 372В9, as well as ground equipment complex 242Ф9.
Through external economic channels, the Osa anti-aircraft missile system was shipped to the Warsaw Pact member countries, India, Iraq and other states of the Middle East, Asia and Africa. In total, the OSA was adopted for use in 25 countries.
At relatively short ranges in anti-aircraft missile systems, a high energy ratio of the signal reflected from the target to the interference was ensured, which made it possible even with intense interference to use radar channels to detect and track targets, and to suppress the television-optical sight. SAM "Osa" in terms of noise immunity surpassed any military anti-aircraft complex of the first generation. In this regard, when using the Osa complexes during the fighting in southern Lebanon in the early 1980s, the enemy widely used various tactical methods, which reduced the combat effectiveness of the complex, in addition to electronic countermeasures. For example, a mass launch of unmanned aerial vehicles simulating combat aircraft was used, followed by an attack aviation at the position of the air defense systems that have spent their ammunition.
Before the “Storm in the Desert” the special forces of the multinational forces, using helicopters, penetrated into Kuwait, captured and took out the Osa anti-aircraft missile system with all the technical documentation. In addition, the crew was captured, which consisted of the Iraqi military.
According to media reports, at the beginning of 1991, during the hostilities, the Iraqi Osa anti-aircraft missile system shot down an American cruise missile.
On the basis of the Osa missiles, the Saman target has recently been developed for use on highways up to 16 kilometers, which simulates a target with 0,08-1,6 2 ESR.
The main characteristics of the Osa anti-aircraft missile systems:
The name - "Osa" / "Osa-AK" / "Osa-AKM";
Range of damage - 2..9 / 1,5..10 / 1,5..10 km;
Height affected area - 0,05..5 / 0,025..5 / 0,025..5 km;
The affected area by parameter is 2-6 / 2-6 / 2-6 km;
The probability of hitting a fighter with one anti-aircraft guided missile 0,35..0,85 / 0,5..0,85 / 0,5..0,85;
The maximum speed of the targeted targets is up to 420 / up to 500 / up to 500 m / s;
Reaction time - 26..34 / 27..39 / 27..39 with
The speed of the anti-aircraft guided missile - 500 m / s;
Missile mass - 128 kg;
The mass of the warhead - 15 kg;
Deployment / collapse time - 3..5 min .;
The number of target channels - 1;
The number of anti-aircraft missiles on a combat vehicle - 4 / 6 / 6;
Year of adoption - 1972 / 1975 / 1980.
Information