Cruise missile DAC-5 (complex K-26)




    management system:

    Radar GOS


    spetsboepripasov, high-explosive


    anti, anti-radar, air-to-ground




    300 km.

    year development:


    cruise missile DAC-5 (set to-26) Cruise missile DAC-5 (D-5) as part of K-26 is designed to destroy radar-contrast sea (surface ships) or terrestrial (bridges, dams, power plants) purposes.

    USSR CM Resolution on the establishment of missile DAC-5 with a control system "Rise", was released on August 24, 1962 They wondered launch range of 180-240 km and a flight speed of 3200 km / h at an altitude of 22,500 m

    complex K-26 was developed in the "Raduga", using the experience of creating the Kh-22. Flight tests of K-26 began on two planes in October 1964. On Tupolev pilot plant number 156 under it converted serial production machines Kazan aviation plant - Tu-16K-11-16KS number 8204022 and Tu-16KSR-2A number 5202010, released almost 10 years ago. Factory tests were delayed for almost two years, and together with the client state tests complex was launched only in January 1967. Results of the first test phase starts with the marine and land-based targets were deemed unsatisfactory due to the low accuracy for the ships dictated management system deficiencies.

    After completions

    complex K-26 re-presented on the state tests, during which they performed 87 flights. To test also attracted Tu-16K-26 number 4200703, and with the end of 1968 - was transformed from a marine bombers Tu-16K-10-26 number 1793014. During the tests, completed by November 30, 1968, at sea and ground targets fired 13 rockets DAC-5. Launches were made at airspeeds carrier 400-850 km / h and altitudes from 500 to 11,000 m This launch range significantly depended on flight mode under the terms of target acquisition radar and missile seeker capture. Thus, at high altitude flight at 11,000 m sector radio survey was significantly higher, and target acquisition occurred at a distance of 300 km, at an altitude of 500 m launch range does not exceed 40 km. Tests marine Tu-16K-10-26 continued until the spring of next year, followed by 12 November 1969 Aviation and Missile Systems K-26 and K-10-26 were adopted by the DA and AVMF.

    Based on DAC-5 were also created a modernized version of the DAC-5M of K-26M to combat small-sized complex targets exhibit increased accuracy characteristics and low-altitude complex K-26H with rockets DAC-5H. Due to the limited visibility when working with low altitude and low resolution, reduces the possibility of complex modernization required search and sighting system. On 14 aircraft radar system installed panoramic "Berkut" IL-38 increased under the fairing. These machines came in aviation of the Baltic Fleet. A more radical solution is the use of a new radar "Rubin-1M", created in 1973 on the basis of "Rubin-1KB» and has an increased detection range and improved resolution. Its antenna system had significant dimensions, differing high gain and reduced by half beamwidth. Detection range maritime targets reached 450 km, but most aerial and need for the equipment layout volumes demanded carry radar with regular place in gruzootsekah under which was mounted teardrop voluminous cowl. Another distinctive feature of these machines has become smooth nose portion, devoid of the former radar. To save weight lifted nose cannon installation, fuel system and tank number was reduced to three, which are located on-site equipment units.

    necessity in today's anti-radar missiles reflected in the Resolution CM from February 7, 1964, to ask the creation of K-26P missiles with KSR-5P, equipped with passive homing. Search the radiating purposes was carried out using airborne radar station reconnaissance and targeting "Ritz" (formally known as passive radar) and conjugated with her intelligence apparatus working radar. The system of control and guidance equipment also included passive homing missiles and autopilot. Antenna unit "Ritsa" placed on the frame glazing mate cabin in which LEDs were assembled, with the help of which displays information about the position and characteristics of Processed radar, and the system is ready to launch missiles.

    Senior Tu-16K-26P entered the factory tests in the summer of 1967, after a series of improvements in April 1972 he was presented to the state tests. CM Resolution of 4 September 1973 the complex K-26P adopted the naval aviation, and in 1975 began to Remzavod refitting aircraft modeled on the Tu-16K-26P. Complex K-26P allowed to hit the radio-emitting target single and salvo launch both missiles in one go, as well as carry out an attack on two different purposes - one lying on the flight path, and the other located in the alignment of 7,5 ° from the axis of the aircraft. Missiles after launch were directed entirely autonomously, without limiting plane in the maneuver.

    In addition to anti-radar missiles

    DAC-5P, the complex provides the use of the DAC-11 and similar purpose remains fully strike capabilities using missiles DAC-5, DAC-2 and bomb armament. With the advent of the upgraded DAC-5M complex opportunities were expanded, and he received the name of K-26PM, differing install improved equipment targeting missile heads.

    low-altitude rocket KSR-5H became the basis for the development of cruise missiles target DAC-5 nm (D-5 nm) and CEB-5mV (D-5 mV) in the low - and high-rise options. Target simulated flight missiles of various types of class "air-surface", a top speed of M = 4.2 at altitudes up to 40 km. Served for testing the latest SAM target launched from carriers Tu-16KRM converted from conventional machines with increased hid modeled missile and installation of holders of DB-352-11-5. To start the target could also be used missile Tu-16K-26.

    For creating

    missile complex K-26 staff team led by A. Ya Bereznyak was awarded the State Prize for 1970 Development of K-26P was awarded the State award for 1977. Serial production of the DAC-5 and its variants has been launched at the Smolensk aircraft plant.


    carriers DAC-5 missiles altered Tu-16A and Tu-16K-16. The latter could use and KSR-2 missiles. Range missiles DAC-5 was significantly higher capacity media radar and did not allow the full potential of new missiles. Therefore, in the area of the cargo hold of the aircraft radar set "Ruby" with antenna from search and sighting station "Berkut" , with a range of up to 400km detection purposes. Under the new radar was converted twelve carriers.

    cruise missile DAC-5 (set to-26) In the future, a new complex for the Navy re-equipped Tu-16K-10 (Tu-16K10-26), and for the Navy and Air Force - Tu-16K11-16 (Tu-16KSR2-5). Tu-16K10-26 in addition to the regular rocket K-10S/SNB under the wing of the carrier beam holders to put two DAC-5. In the 1970s it was the most powerful anti-ship aircraft complex. The simultaneous use of K-10 low-altitude and high-altitude DAC-5 significantly increased the probability of target destruction.

    For product development

    D-5 large group of MKB "Raduga", headed by A. Ya Bereznyak was awarded the State Prize for 1970


    mostly supplied as an option rocket KSR-5H, which had the same ARGSN as the base, but differs in a number of systems, including on-board power supply. In 1972, anti-radiation was created DAC SD-5P. Her carrier Tu-16K-26P received station targeting "Riza", which was placed on the Tu-16KSR2-5. For the creation of rocket KSR-5P MKB "Raduga" received the State Award for 1977

    In 1967

    . on EMRs began work on equipping the complex K-26 bombers 3M. Production aircraft 0305 received 2 DB-487 radar "Rubin 1ME" targeting equipment for DAC-5P and ATP "Azalea." Test aircraft called the ZM-5, were successful, however, was not resolved the question of extending aircraft life and work stopped.

    In the early seventies

    similar revision was one Tu-95M (Tu-95M-5 complex K95-26).

    complex K-26 had significant capabilities and combat effectiveness, allowing you to hit both marine and ground targets (such as factory buildings, bridges, dams, depots and warehouses), General condition is sufficient radar visibility of objects, which is also responsible airfields port facilities and railway station. At the time of adopting its missiles were almost nesbivaemy not only available anywhere, but also promising means of enemy air defenses, and this situation continued until the beginning of the 1980s.

    Complex application

    missiles with antiradar DAC-5P made themselves vulnerable and antiaircraft weapons - after hacking defense aviation strike group benefits become even more pronounced.

    the west DAC-5 rocket was designated AS-6 "Kingfish".


    cruise missile DAC-5 (set to-26) According to the aerodynamic configuration DAC-5 - mid-wing monoplane and feathers (see layout scheme).

    DAC-5 rocket has a metal structure with stressed skin, sredneplana location delta wing span and a small Phillips plumage. Control roll and pitch carried integrally turning stabilizer worked in elevon mode Exchange - tselnopovorotnym upper keel. To increase stability in flight missile had lower ventral fin, down to the right on the flight during storage, transport and suspension. Layout at startup ensured pneumatic cylinder with unlocking rudders shoot the clamps.

    main structural materials airframe missiles were stainless steel EI-654 (oxidizer tank compartment), and 30KhGSA 12H2NVFA (power nodes butt feathers and elements) alloys AMG-6T (fuel tank) and D16T (part coverings and panels). 1 of heat-resistant steel toe 2HNVFA also produces rocket fairing, heated in-flight up to 420 °. Large housing units were welded together, wing and tail were made with extensive use of honeycomb panels of thin aluminum foil to ensure that the strength and stiffness poured molten xylitol, and then processed by the theoretical contour on a vertical milling machine using a copier. Large, widely used non-ferrous castings, which went on production load frames and beams mounting hardware.

    Some of the problems caused

    manufacturing radiotransparent fairings - bulky items that should have been at high supersonic aerodynamic and thermal loads, the required mechanical strength, heat - and moisture resistance, high surface smoothness, low weight and, more importantly, due radioprozrachny, which makes special stringent requirements. Last directly affect the characteristics of the GOS, which required to provide radio transmission coefficient within 70-75%. Required experiments and searches fabrication technologies most "light" in the desired radio band fairings implemented leading engineers of the plant number 256 VN Lezhenina, LE Kuznetsova, A. Kazakov and specialist VIAM KT Shcherbakova.

    Practice making

    whole fairings for the X-22 of fiberglass showed that they have too much weight. Fairing almost two-meter size at the required strength and stiffness had to have a small mass, but precisely defined contours. By radiotransparency requirements, limited thickness 4-7 mm. Cone had a honeycomb structure with a grid filler, and the thickness varied from greater in the tip to the base fine. For the manufacture of the outer and inner steel plunger-shirts used in which a vacuum molded fiberglass sheathing. At the same punch on the inner jacket Jell molded contour mesh cell aggregate, then was put on the outer shirt and belt force at the base. Final polymerization curing package of the binder resin to enhance the strength was carried out in compliance with the furnace temperature stepwise.

    challenging task became construction balloons balloons that fed control actuators and missile system pressurization. Cylinders made of two thin hromansilevyh hemispheres 5 mm thick, welded joins. Cylinders were withstanding the operating pressure of 350 atm, however, the products do not always work strong. In the operation had been a number of cases, their explosion destroys the structure, and was near the engine and tanks, which resulted in a fatal outcome for the whole product and was extremely dangerous for the staff. Cylinders - "bomb" does not enjoy the trust as long as they have not been introduced to strengthen wound fiberglass body harnesses on the binder composition. Such a construction withstanding pressures up to 700 atm, allowing to reduce the wall thickness of 4 mm, and does not break when yielded fragments, breaking down to half.

    the bow missile homing equipment held Sun-WH with active radar seeker. Using airborne equipment targeting GOS lock target for suspension, tracking its position in azimuth. Control System - "Rise" provided by homing rate and pitch and height control software, providing output rockets into the stratosphere, followed by a dive to the target. , In the future, the control system has been improved and provide the ability to perform evasive maneuver in the event of radiation missiles enemy radar.

    In the next compartment

    placed high explosive warhead-type cumulative weight of 700 kg or a nuclear warhead in a special container with all necessary equipment, including a detonation device, providing a specified ground or air blasting, system protection and charging sensor undock from the carrier and by tracking sensors temperature control system, supporting the compartment required temperature and humidity.

    central part of the rocket fuel compartment occupied with fuel and oxidizer tanks. Fuel tank contained 660 l, steel tank-oxidant compartment - 1010 l. Tank pressurization system provides air that is also used first stage delivery system, it can help boost also produced waveguides layout and ventral fin. Pipelines pressurization system, supply of electrical fittings and wiring were laid in the ventral fairing under the removable panels for access. "Dry" ampoule battery with converter equipment compartment Energy systems provide for 480 seconds. Low-altitude DAC-5H had a number of differences in the energy system and the battery.

    rocket equipped with LRE type design S.5.33 KB AM Isaev having two combustion chambers with separate exhaust nozzles. Supersonic nozzle unregulated, and each of them has been optimized to create a specific thrust. Food engine provides a common turbopump unit (TPU) with automatic adjustment modes, performing two programs with different thrust. High TNA gave the necessary level of fuel consumption is 80 kg / s, and the required pressure at the inlet to the engine (thrust rocket engine increases significantly with increasing the operating pressure in the combustion chamber, and the pressure must exceed its supply to fuel could enter the engine). The two-chamber design ZhRD at low weight and compactness provide the required range of rods needed for different flight conditions. When starting the rocket started working afterburner combustion thrust which in 7100 reported kgf thrust rocket 1.8 and provide rapid acceleration and climb. To maintain speed at the height of the work included marching combustion chamber with an economical 600 kgf thrust or 1120 kg, depending on the desired flight mode. Fuel - two-component: fuel TG-02 (660 hp) and an oxidant AK-27P (1010 L). Air missile system provided a boost waveguides, oxidizer and fuel tanks, layout ventral fin and other operations.


    DAC-5 (see projection) - basic version of the missile

    DAC-5H (see projection) - low-altitude version of the missile DAC-5, with the same ARGSN as the base, but differs in a number of systems, in particular on-board power supplies

    DAC-5P - version DAC-5 equipped with passive radar homing and designed to defeat radar (range goal to capture the 400-450km).

    DAC-5M - rocket to fight with complex small-sized targets with high accuracy.

    DAC-5nm - low-altitude missile target

    DAC-5mV - altitude missile target

    By airplane equipment

    missile was compatible with older complexes K-10 and K-11-16 based on the Tu-16, but for the suspension demanded reinforced holders DB-487.

    cruise missile DAC-5 (set to-26)

    Technique of use of K-26 (see diagram) was largely similar to the K-16. After target detection radar carrier carried her capture and tracking of homing missiles in flight at an altitude of 10-11 km is normally applied by removal of 300 km. With regard to control operations and the time for decision-making milestone start DAC-5 from these heights was a distance of about 280 km. Team-missile equipment with power supply switched "on board" on the media ampoule own battery, and after 12-14 seconds of all missiles left on standby to start. Descended from suspension rocket went down, away from the aircraft to a safe distance while undocking served as a signal for fuse arming warheads. Speed at start should withstand the range 400-850 km / h on the second second flight was launched rocket engine and began to pick up speed, the 15th sec. after the dissolution of moving into the climb team software autopilot mechanism. Then there is a connection via GOS course, but with acceleration up to Mach 3 disconnected afterburner mode. At an altitude of 18,000 meters rocket began stabilization height with the inclusion of LRE and sustainer mode transition to horizontal flight, operated at an altitude of 22,500 m As rapprochement with the aim of up to 60 km missile was converted into a dive with an angle of 30 °, (dive team elaborated on autopilot when deviation antenna radar coordinator GOS 30 °, that corresponds to the slant range to the object about 60 km and the distance measuring device with access to the GOS distance duplicated team in case of failure auto-tracking).

    When distance to the target was reduced to 400-500 m, autopilot switches to stabilize the flight, keeping the direction of homing to avoid disruption due to interference or "blinding" the reflected signal. GOS itself under the influence of interference in order to avoid failure, the previous settings memorized target. Guidance system DAC-5 provides a sufficiently high accuracy, characterized by the probable circular deviation of 10-20 m (the same quantity measured and precision DAC-5P). However, guidance for operational use was noted that the error may increase significantly in a well-organized electronic countermeasures by the enemy, and for anti-radar missiles - as a result of jamming or termination of radar.





    Length, m




    Diameter, m




    span, m




    Starting weight, t




    guidance system

    ARLGSN Inertial +

    PRLGSN Inertial +

    ARLGSN Inertial +


    OF thermonuclear 350-500 kt or

    OF thermonuclear 350-500 kt or


    warhead weight, kg

    700 (900-1000)



    firing range, km

    240-300 (400)



    flight speed, km / h

    3200 (3M)

    3200 (3M)


    height, km




    Altitude, km












    preparation unit missiles




    radar targeting




    aircraft carrier

    Tu-16K-26, Tu-16K10-26, Tu-95K-26, Tu-95M5


    Tu-16K-26, Tu-16K-10-26


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