S-25 (missile)

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S-25 (missile)

S-25O missile
S-25O missile

General Information
Type Air-to-surface missile
Local name S-25, ARS-250
NATO designation S-25
Country of origin Soviet Union 1955Soviet Union Soviet Union / RussiaRussiaRussia 
Manufacturer Design office KB Totschmasch
development 1960s
Commissioning 1975
Working time in service
Technical specifications
length 3.31-3.80 m
diameter Hull: 260 mm, warhead: 300-420 mm
Combat weight 320-480 kg
drive Solid rocket engine
speed 511-530 m / s
Range 3-11 km
Furnishing
steering no
Target location no
Warhead 150-190 kg
Detonator Impact detonator or proximity detonator
Weapon platforms Planes
Lists on the subject

The S-25 is a family of unguided and guided air-to - surface missiles originally manufactured by the Soviet Union.

development

The decision to develop the weapon was issued in 1965. Based on the successfully introduced S-24 missile, a new missile with an oversized fragmentation warhead was to be developed. The development order was awarded to the KB Totschmasch design office . The tactical and technical demands made by the High Command of the Soviet Air Force could only be met with a new design. As with the 57 mm S-5 rocket , folding stabilization surfaces were used on the rear of the rocket. The first attempts at shooting were made in 1971 on the Akhtubinsk firing range . The acceptance tests took place there between July and September 1974. In 1975 the first S-25 missiles were delivered to the Russian Air Force.

In the mid-1970s, development of the S-25L variant began. This is a guided S-25 missile with a semi-active laser aiming head. For this purpose the S-25 of the 24N1 laser target seeker head of the Ch-25 was mounted. The resulting missile is called the S-25L and was incorporated into the armament of the Soviet air force in 1984. The S-25L was first presented to the public in 1993.

technology

rocket

For transport on the carrier aircraft, the S-25 is housed in the PU-O-25 launch tube (weapon carrier), which is made of wood and aluminum . The launch tube takes the entire rocket fuselage; only the over-caliber warhead protrudes from the tube. The rocket consists of a cylindrical fuselage that houses the solid fuel motor. The front part of the fuselage is enlarged in diameter and accommodates the warhead and, in the case of the guided variants, the homing head. This part is conical towards the front. The rocket has a tail unit with four guide surfaces and is spin stabilized. After leaving the launch tube, the guide surfaces fold out. In flight, the rocket rotates around its longitudinal axis at 600 revolutions per minute. A tracer set is integrated between the solid rocket nozzles for better visual tracking. The steered variants also have four delta-shaped control surfaces on the front part of the fuselage. Before firing, the weapon carrier PU-O-25 encloses the thinner part of the fuselage, the stabilizing surfaces at the rear are folded in. Together with the shape of the warhead, this reduces the drag of the attached missile. The stabilization surfaces unfold after leaving the launch tube. The range of the unguided rocket is 2–4 km with a burn time of 1.95–2.86 seconds. The scattering circle radius ( CEP ) of the unguided S-25 is around 50 m. The S-25 can be launched at an altitude of 25–3,000 m at speeds of up to 1,500 km / h.

On the guided S-25L, a module weighing 42 kg is installed at the tip of the rocket, which houses the 24N1 laser target seeker, the SUR-73 autopilot, the control surfaces and the power supply. The actual warhead, the fuselage with the rocket motor and the stabilization surfaces remained unchanged. In order for the control logic in the control module to function properly at 600 revolutions per minute, the module is pivoted and does not rotate with it. The revised weapon carrier O-25L contains the electrical connections for connection to the carrier aircraft. The maximum range is 7 km. The S-25LD version introduced in 1984 has an increased range of up to 11 km. The scattering circle radius ( CEP ) of the S-25L is given as 5–10 m, depending on the source. The laser target seeker head can optionally be replaced by a TV seeker head (S-25TV) or an infrared seeker head (S-25IRS).

Warhead

The S-25 missile was designed to combat soft, semi-hard and hard targets. The original versions are designated as S-25O and S-25F , with the letter O for Oskolochnaja ( fragmentation warhead ) and F for Fugasnaja (explosive warhead). The warhead of the S-25O has a diameter of 420 mm and a weight of 150 kg. The fragmentation warhead is the RV-25 - proximity fuze 30 meters above the ground brought to detonation and thus to achieve its optimum surface effect. During the explosion, the warhead splits into 5,500 heavy and 12,000 light fragments with an effective radius of 400–500 m. The warhead of the S-25F is significantly smaller with a diameter of 320 mm, but weighs 190 kg. This warhead has an impact fuse. When impacting loose soil, the S-25F creates a crater 3.5 m in diameter and 1 m deep. The further developed versions S-25OF and S-25OFM (for Oskolochno-fugasnaja , fragmentation warhead) have a modified warhead with an electromechanical detonator. This can be adjusted depending on the nature of the target (delay or surcharge). The weight of the warhead is 151 kg. There is also the S-25O-PU version with a shaped charge warhead for fighting bunkered targets.

The S-25L has a hardened penetration warhead with a mass of 155 kg. In addition, a 21 kg fragment warhead is installed. The S-25L can penetrate 1.5 m of reinforced concrete or 4-5 m of soil. There is also a 194 kg fragmentation warhead.

variants

  • Unguided missiles
    • S-25F: with explosive warhead, range of 2-3 km
    • S-25O: with fragmentation warhead
    • S-25O-PU: with shaped charge warhead
    • S-25OF / OFM: with fragmentation warhead
    • S-25M: modernized version of the S-25OF
    • S-25MD: modernized version with increased range of 4–5 km
  • Guided missiles
    • S-25L: with semi-active laser target seeker, range 7 km
    • S-25LD: Version of the S-25L with an increased range of 11 km
    • S-25TV: with TV seeker head, primarily intended for export
    • S-25TP: with passive infrared seeker head
    • S-25A: with active radar seeker in the K u band (18–40 GHz )
    • S-25SE: Prototype with GLONASS steering system

  • S-25F (with explosive warhead)

  • S-25O (with fragmentation warhead)

  • S-25OFM (with fragmentation warhead, modernized) in launch container O-25-L

  • S-25F, details of the rocket motor exhaust nozzles and stabilization surfaces

Carrier aircraft

Web links

Individual evidence

  1. ↑ a b c airwar.ru , accessed on February 19, 2014
  2. ↑ a b c d Jefim Gordon : Soviet / Russian Aircraft Weapons since World War Two. Midland Publishing, 2004.
  3. ↑ sistemasdearmas.com , accessed February 19, 2014
  4. ↑ a b c d Jane’s Air-Launched Weapon Systems. Edition 2002, Ducan Lennox, Jane's Information Group 2002.
  5. ^ A b Norman Friedman: The Naval Institute guide to world naval weapons systems, 1997–1998, accessed on February 19, 2014
  6. ↑ a b ausairpower.net , accessed on February 19, 2014
  7. ↑ Thomas Newdick: Postwar Air Weapons 1945 - Present . 2011. p. 173.
  8. ↑ Russian Air Force prepares to test guided rockets ( Memento from July 5, 2013 in the Internet Archive ) IHS Jane's 360, accessed February 19, 2014