Almaz 5V24 5V27 S-125 Neva

Last Updated: Wed Oct 13 13:02:14 UTC 2010

Almaz 5V24/5V27/S-125 Neva/Pechora

Air Defence System / SA-3 Goa Зенитный Ракетный Комплекс 5В24/5В27/С-125 Нева/Печора

Technical Report APA-TR-2009-0602

by Dr Carlo Kopp, SMAIAA, MIEEE, PEngJuly 2009

Text, Line Art © 2009 Carlo Kopp

Almaz 5V24/5V27/S-125 Neva/Pechora / SA-3 Goa / Зенитный Раке... http://www.ausairpower.net/APA-S-125-Neva.html

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The S-125 / SA-3 Goa was designed to provide low altitude coverage, supplementing the largerand longer ranging S-75 / SA-2 Guideline. This weapon played a major role during the 1970sMiddle Eastern wars. Depicted Tetraedr's upgraded UNV-2T Low Blow and a four rail 5P73launcher, upgraded to the Pechora 2T configuration (Tetraedr image).

BackgroundSNR-125/125M Low Blow Engagement Radar5V24 and 5V27 Surface to Air MissilesProduction and Exports

S-125 Technical DataS-125 Launch Footage

S-125 Battery ComponentsS-125 Battery Deployment5P71/5P73 LauncherPR-14A/AM Self Propelled Transporter/TransloaderAT-S Tow TractorAlmaz SNR-125 Low Blow Engagement RadarP-15 / P-15M / P-19 Flat Face / Squat Eye Acquisition RadarPRV-10 Konus / PRV-11 Vershina / Side Net Heightfinding Radars

S-125 / SA-3 Goa Combat ImageryReferences/Sources:

Background

The S-125 Neva/Pechora / SA-3 Goa Surface to Air Missile system was developed to supplementthe S-75 Dvina / SA-2 Guideline in Soviet and Warsaw Pact service. The S-75 Dvina / SA-2Guideline was designed to provide medium to high altitude air defence coverage, primarilyagainst bomber aircraft. As such it was not well suited to the engagement of low flying targets,especially fighter aircraft and cruise missiles.

The design aim of the S-125 Neva/Pechora / SA-3 Goa was thus to produce a system with a low


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coverage of protected airspace. Specifically, targets travelling at speeds of up to 1500 km/h(800 KTAS) and at altitudes from 100 m to 5000 m (~300 ft to 16,500 ft AGL), at ranges of upto 12 km (~6,5 NMI) were to be engaged and destroyed. Such performance is todaycharacteristic of a point defence weapon, but during the 1950s it was more typical of areadefence weapons.

The Soviets sought to build on the experience gained with the S-75 Dvina / SA-2 Guideline,using command link guidance and a proximity fused warhead, but recognised from the outsetthat a fundamentally new engagement radar design was required with much better clutterrejection performance than the RSNA/SNR-75 / Fan Song series. The requirement for narrower antenna mainlobes drove the designers into the 9 GHz frequency band, well above the ~6 GHzoperating range of the earlier RSNA/SNR-75 Fan Song series. Development was initiated in1956, aiming for an IOC after 1960.

The resulting weapon was more compact than the S-75 Dvina / SA-2 Guideline, permitting tworail launchers and two round transloaders, and used a solid propellant sustainer, the first in aPVO SAM design. Canard controls were employed. Like its predecessor, the missile used a solidrocket first stage booster. Numerous development problems were encountered throughout thesystem, but especially with the performance of the radio proximity fuse and command linkguidance at very low altitudes.

The Soviets were particularly concerned about US Air Force low altitude penetration trials flownby the B-58 Hustler, which demonstrated the ability to penetrate US SAM belts undetected, byexploiting ground clutter and elevated terrain, a factor which influenced the design of thesubsequent F-111/FB-111 series and the B-1A LRCA.

Trials of the V-600P missile round and new radar demonstrated the capability to engage targetsat speeds of up to 2,000 km/h (~1,100 KTAS), at altitudes between 200 m and 10,000 m(~600 ft to 33 kft AGL), with the target pulling up to 4G at 5,000 m to 7,000 m (16.6 kft to 23kft) and up to 9 G below 3,300 ft AGL at transonic speeds. Estimated single shot Pk was

0.82-0.99, deteriorating to 0.49-0.88 if chaff were deployed.

While the new system met the needs of the PVO, its stow and deploy times were similar to theS-75 Dvina / SA-2 Guideline and thus too great for the Army air defence units, who rejected thedesign, resulting in the development of the high mobility 2K12 Kub / SA-6 Gainful system. TheS-125 Neva / SA-3A Goa achieved IOC in 1961, deployed as part of the Moscow region SAMbelt.

The first improved variant was the S-125M Neva M / SA-3B Goa, intended to improve themissile's kinematic engagement envelope, low altitude fusing and radar clutter rejection, andused a new four rail launcher. The new missile was designated the V-601P/5V27. IOC was notachieved until early 1964.

The weapon was not deployed to South East Asia as the Soviets feared that the US Air Forcewould quickly analyse its design and find its weaknesses, and develop effectivecountermeasures, as they had done so successfully with the S-75 Dvina / SA-2 Guideline.Instead, the Soviets exported the weapon to Egypt, to counter the innovative Israeli air force,who frustrated Soviet instructors during the war of attrition, by flying well below theengagement envelope of Egyptian S-75 Dvina / SA-2 Guideline batteries.

In Egypt, the sandy desert terrain proved problematic for wheeled vehicles, which were oftenreplaced with tracked AT-S artillery tow tractors. The Soviet instructors shot down severalIsraeli aircraft during the War of Attrition, mostly F-4E Phantoms and at least one A-4 Skyhawk.The US ALQ-101 jamming pods were effective against the S-75 Dvina / SA-2 Guideline, but notthe S-125 Neva / SA-3 Goa, possibly due to different operating bands and antenna scanfrequencies. The good low altitude capability of the weapon frustrated Israeli low altitudepenetration tactics. In the subsequent 1973 Yom Kippur war, the S-125 Neva / SA-3 Goarepeated its earlier achievement, outperforming the S-75 Dvina / SA-2 Guideline.


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upgrade package, intended to improve countermeasures resistance and performance. The9Sh33A Karat 2 television telescope was added to provide for optical angle tracking underdaylight conditions, and a new heavier and faster 5V27D missile round was designed. Theheavier missile resulted in the 5P73 launcher loadout being limited to three missiles. IOC wasachieved in 1978.

The S-125 Neva / SA-3 Goa was also used extensively by Iraq during the Iran-Iraq war, butreliable statistics do not exist, given that both sides in the conflict had a well established habit ofgrossly overstating kills in combat.

The S-125 Neva / SA-3 Goa did not perform well during the Desert Storm campaign, as it hadbeen completely compromised due to the Israeli capture of SNR-125 Low Blow radars in 1973,and good countermeasures were available. Nevertheless, the weapon is usually credited withthe handful of Iraqi SAM kills against Coalition aircraft.

The last two documented kills credited to the S-125 Neva / SA-3 Goa are the F-117A Nighthawkand an F-16 lost during Operation Allied Force in 1999.

The basic S-125 Neva / SA-3 Goa qualifies as semi-mobile, requiring several hours to set up orredeploy a battery. Typical battery composition is a single SNR-125 Low Blow seriesengagement radar, four dual rail 5P71 or four rail 5P73 launchers, and multiple PR-14 series dualround transporter/transloader trucks carrying reload rounds. Most S-125 operators deploy thesystem in fixed sites, with revetments using concreted pads and bays, and/or earthwork berms,to protect the missile system components.

SNR-125/125M Low Blow Engagement Radar

The SNR-125 Low Blow is the engagement radar for the S-125/SA-3 Goa family of commandlink guided SAM systems. While the system is regarded to be now obsolete, like the SA-2, anumber of manufacturers in former Soviet republics are offering deep technology upgrades tothe Low Blow design to improve maintainability, performance and jam resistance.

Like the SNR-75, the SNR-125 uses a pair of fixed scanned trough antennas to generate flappingfan shaped beams, but the design is inherently SORO (Scan On Receive Only) with a separateparabolic section antenna mounted between the characteristic chevron arrangement of troughantennas. A clutter cancelling channel is included, using the central antenna. As noted earlier,optical adjunct tracking was installed on later variants. The antenna at the top of the turret isused for the missile uplink channels.

A more detailed discussion can be found under Engagement and Fire Control Radars.

5V27 (V-601P) Goa Cutaway (via Vestnik-PVO/Aviatsiya i Kosmonavtika No12/2002)

1 Proximity fuse transmit antenna

2 5E18 radio proximity fuse

3 Canard controls


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5 Receive antenna

6 Transducer

7 Splitter/converter box

8 Battery

9 5A22/APS-600 autopilot

10 5U42/UR-20A Command link control module

11 Aileron control

12 Aileron drive

13 Sustainer powerplant with 151 kg of 301-K solid propellant providing 20 sec burn duration

14 Compressed air tank

15 Initiator for sustainer powerplant

16 Adaptor destabilising fins

17 5S45/PRD-36 boost powerplant with 2-4 sec burn duration / 14 tubes of NMF-3K propellant

18 Stabiliser pivot

Baseline S-125 / SA-3 (dark) engagement envelope, and S-125-2T Pechora 2T block upgrade(light) firing trial results. The Pechora 2T is a characteristic of contemporary digital blockupgrades to widely used Soviet era SAMs. Provisional data - Tetraedr JSC.


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Early model 5V24 SA-3A Goa missile (Almaz image via Vestnik PVO).

Late model 5V27 SA-3B Goa missile (Almaz image via Vestnik PVO).

5V24 and 5V27 Surface to Air Missiles

The basic airframe design of the 5V24/5V27 missile is similar to that of the earlier S-75 / SA-2Guideline, but with two important differences. the first is the use of a low smoke solid propellantsustainer, the second is the use of cruciform canard controls.

Like its predecessor, the 5V24/5V27 missile is a very simple design, with command linkguidance.

The nose of the missile houses the radio proximity fuse. In early variants this was the 5E15Proliv series, in later variants the 5E18. The transmit antenna is in the nose, the receiveantennas aft of the cruciform canard controls and their actuator module. The canards are usedfor pitch/yaw control inputs, with a pair of ailerons on the cruciform wing used for rollstabilisation.

The truncated conically shaped fragmentation warhead is mounted aft of the canard controls. Inearly variants this was the 5B15, with ~33 kg of high explosive and a prefragmented casingdesigned to produce 3,560-3,570 high velocity fragments. Later variants used the 72 kg 5P18 producing 4,500 fragments. A 5B72 self destruct mechanism is mounted behind the warhead.

The 5A22/APS-600 autopilot and 5U42/UR-20A Command link control module are mounted aftof the warhead in the main control section. A UR-80M turbogenerator is mounted in this section,together with the 5P54 power converter. A spherical 300 atm compressed air tank is used topower the controls.

The V-600P missile used a 5B83 solid propellant rocket sustainer, constructed with a 375 mmdia steel cylindrical casing and filled with 125 kg of NM-4Sh nitrocellulose based propellantcharge, in an annular arrangement. A 5B93 igniter was used, initiating the burn from the centralcylindrical cavity. An external cable duct routed signal cables around the engine section.

The first stage, which was used to accelerate the missile at launch, employed a PRD-36 solidrocket powerplant with 2-4 sec burn duration. This design used 14 tubes of NMF-3K solidpropellant and a variable cross section throat. The stabilisers on the booster were designed tofold out under acceleration and lock into the flight position. The adaptor sleeve between thestages acquired a pair of destabilising fins in later variants, intended to prevent post separationglide of the burned out aft section.


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The missile guidance system is relatively simple, comprising an autopilot and a command linkreceiver, with a missile beacon in the tail to facilitate tracking by the Low Blow radar.

In operation, the Low Blow radar tracks the target and continuously computes an optimalmissile trajectory for intercept, while tracking the 5B24/5V27 missile via its transponder beacon.The uplink is then used to continuously drive the missile flightpath as close as possible to theintended trajectory, in a closed loop scheme.

The Low Blow provides manual tracking, automatic tracking and television angle trackingmodes. The system provides five missile guidance control laws, TT (CLOS), PS, MV (LoAlt), K(surface target attack) and DKM (ballistic). Three missile uplink signals are employed, K1 andK2 for pitch/yaw steering, and K3 for fuse control. The most often used control law was the“Polavinoye Spravleniye (PS - half correction)” technique, which is a range known mode. In PSmode the proximity fuse is activated 60 m before the missile reaches the target, whereas inbasic range unknown TT/CLOS mode the fuse is activated immediately after launch.

The command link guidance scheme, and the need to carefully select control laws and radarmodes, results in a need for high levels of operator skill and a good understanding ofengagement geometries.

Production and Exports

The S-125 Neva / SA-3 Goa was manufactured by the Soviets from the mid-1960s through tothe 1980s, with spare part manufacture to support exported installations continuing since then.The Soviets exported the weapon globally, and it would appear at this time that it is the mostlywidely used of the legacy SAM systems. As the S-125 Neva / SA-3 Goa does not require thestockpiling and handling of problematic hypergolic liquid fuels, and is much simpler to operateand maintain than its PVO-SV contemporary, the 2K12 Kvadrat / SA-6 Gainful, it has been avery popular weapon in the developing world.

Surveying the exact status of current global deployments of this system is problematic, sincemany operators do not disclose the state of their air defence systems. Russia retired the systemduring the 1990s, but it remains in use with many former Soviet Republics, some formerWarsaw Pact nations, and many former Soviet client nations in the developing world, especiallyAfrica.

A number of electronics and mobility upgrades have been developed, a more detailed discussioncan be found under Legacy Air Defence System Upgrades.

S-125 Technical Data

Characteristics "Pechora" ADMS

1. Channels capacity, target 1

2. Channels capacity, SAM 2

3. Maximum target detection range, km 80

4. Maximum speed of targets engaged, head-on/receding, m/s 700 / 300

5. Minimal altitude of target engaged, km 0.02

6. Maximum altitude of target engaged, km 18

7. Range to near boundary of engagement zone, km 3.5

8. Range to remote boundary of engagement zone, km 17

9. Maximum slant range of engagement zone, km 24.8

10. Maximum course parameter of the target engaged, km 16.5

11. SAM guidance methods HL , TP

12. Jamming protection of SAM System:

spectrum density of the jamming (W/MHz),

equivalent distance 100 km

24


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13. Kill probability of target by one SAM:

а) tactical fighter

б) helicopter

в) cruise missile

г) maneuvering target

0.45 - 0.87

0.17 - 0.67

0.04 - 0.48

0.20 - 0.50

Source: Tetraedr

S-125 Launch Footage

SAM System Mobility - Air Defence System Vehicles [Click for more ...]SAM System Integration - Air Defence Command Posts [Click for more ...]SAM System Passive Targeting - Emitter Locating Systems [Click for more ...]SAM System Counter VLO Capabilities [Click for more ...]SAM System Multimedia - Rosoboronexport Footage [Click for more ...]

S-125 Battery Components

S-125M Battery Components

System Qty Function/Composition Vehicle

SNR-125 UNV Cabin / Low Blow 1 Radar head van Towed

SNR-125 UNK Cabin 1 Radar operator van (OdAZ-828 semitrailer) Towed

5E96 Cabin 1 Power generator van Towed

5P71 / 5P73 4 Launcher, Two/Four Rail Towed

PR-14A/AM 8 Transporter/transloader ZIL-131

AKKORD 1 Training Emulator (OdAZ-828 semitrailer) Towed

P-15M Squat Eye 1 UHF-Band Low Level Acquisition Radar Ural-375

P-15/19 Flat Face 1 UHF-Band Acquisition Radar Ural-375

1L22 Parol 4 / 75E6 Parol 3 1 IFF Interrogator KrAZ-255

PRV-10 Konus / PRV-11 Vershina / Side Net 1 Heightfinding Radars Towed

5F20/5Ya61/62/63 Tsikloida 1 Radio relay van (OdAZ-828 semitrailer) Towed

S-125 Optional Battery Components

RD-75 Amazonka 1 Rangefinding radar Towed

P-12M/P-18 Spoon Rest 1 VHF-Band Acquisition Radar Ural-375

AT-S N Tow Tractor -

S-125 Battery Deployment


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Aerial reconnaissance image of a Middle Eastern S-125 / SA-3 Goa site (via http://peters-ada.de/).


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US DoD rendering of fixed revetted S-125 / SA-3 Goa site. Site design followed a similarpractice to that followed in the construction of S-75 / SA-2 Guideline sites.


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NVA drawing of an S-125 / SA-3 Goa site (via http://peters-ada.de/).

5P71/5P73 Launcher


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Reloading a 5P71 launcher from the PR-14A transloader vehicle.

PR-14A/AM Self Propelled Transporter/Transloader


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Early model PR-14A transloader/transporter (US DoD).

AT-S Tow Tractor


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The AT-S tracked tow tractor was often used as a substitute for wheeled tractors in MiddleEastern deployments, due to soft surface conditions (Russian internet image).

Almaz SNR-125 Low Blow Engagement Radar

SNR-125M Low Blow B deployed, with UNV and UNK vans, and generator van (via VestnikPVO).


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Detail of Slovakian Air Force SNR-125M1 Low Blow in a hardened emplacement, the system hassince been retired from service (image © Miroslav Győrösi).

P-15 / P-15M / P-19 Flat Face / Squat Eye Acquisition Radar


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Late model P-19 Flat Face D acquisition radar.


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PR-14A , P-15 Flat Face and P-15M Squat Eye. Note the antenna mast tether on the P-15M(Soviet MoD).

PRV-10 Konus / PRV-11 Vershina / Side Net Heightfinding Radars


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Early model PRV-10 heightfinder (Vestnik PVO image).

S-125 / SA-3 Goa Combat Imagery

The SNR-125M Low Blow operated at the core of the most successful S-125M battery ever usedin combat is depicted here. This system, formerly of the 3rd battery of the 250th Missile Brigadeof the Yugoslav Federal Air Force (3. raketni divizion 250. raketne brigade PVO (Protivvazdusneotbrane)), is credited with two confirmed kills during the Allied Force air campaign of 1999,while under the command of then LtCol and later Col Zoltán Dani. The first claimed kill was Vega31, F-117A AF 82-0806, lost on the 27th March, 1999. The second claimed kill was F-16CG AF88-0550, lost on 2nd May, 1999. The Serbians are also claiming a B-2A Spirit bomber, on 20thMay 1999, but no physical evidence exists to support the latter claim. The SNR-125M Low Blowin question has since 1999 been upgraded to the SNR-125M1T configuration, with a thermalimager and laser rangefinder, and some electronics upgrades like the TVK (televisioncoordinator equipment), and was recently photographed at Jakovo, near Belgrade InternationalAirport. It currently belongs to the 2nd Missile Battalion of the Serbian Air Force. All images ©


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SNR-125M1T Low Blow UNV radar head and UNK operator van.


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SNR-125M1T Low Blow UNV radar head, above and below.


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SNR-125M1T Low Blow UNK operator van, above, and stencils denoting claimed kills, below.


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5P73 launcher with four 5V27D Goa rounds loaded.

References/Sources:

Said Aminov, Vestnik PVO, URL: http://pvo.guns.ru1.Peter Skarus, Peter's ADA - Theorie und Grundlagen der Fla, URL: http://peters-ada.de/2.

Technical Report APA-TR-2009-0602

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Almaz 5V24 5V27 S-125 Neva