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38-442: Too large to be manportable, it was typically deployed from specialised vehicles or helicopters. The missile was intended to supplement traditional anti-tank weapons, like the 100 mm anti-tank gun whose accuracy beyond 1,500 m is poor. The missile's accuracy in contrast remained high as far as its maximum range of 2,000 m. However, the system's bulk, slow speed and poor combat accuracy drove development of later SACLOS systems, like

76-402: A number of July and August engagements in the conflict, with low effectiveness. North Korea began producing a reverse-engineered version of the missile in 1975. The missile is guided to the target by means of a joystick, which requires some skill on the part of the operator. The operator's adjustments are transmitted to the missile via a thin wire that trails behind the missile. The missile

114-402: A signal is sent from the operator's sights toward the target. The signal is generally radio or a laser . The missile has receivers for the signal on the rear of the fuselage. Some form of encoding is used in the signal so that the missile can steer itself into the center of the beam. Changing frequencies or dot patterns are also commonly used. These systems have the advantage that the link between

152-556: A single command BRDM. While a few were used by Egyptian forces during the 1967 Six-Day War and from 1969 in the War of Attrition , only one tank loss was attributed to the system. The system's hit probability is estimated to have been 25% in combat. The system was also used by the Cypriot National Guard during the 1974 Turkish invasion of Cyprus in a man-portable version. Several dozen shots were fired in action during

190-470: A smoke screen or firing on the operator. Also, the large size of the missile means that only a few rounds can be carried; the BRDM-1 vehicle can only carry three missiles. SACLOS Semi-automatic command to line of sight ( SACLOS ) is a method of missile command guidance . In SACLOS, the operator must continually point a sighting device at the target while the missile is in flight. Electronics in

228-418: A tracking station has two or more radar antennas: one dedicated to track a missile and one or more dedicated to track targets. These types of systems are most likely to be able to communicate with a missile via the same radar energy used to track it. The CLOS system uses only the angular coordinates between the missile and the target to ensure the collision. The missile is made to be in the line of sight between

266-522: Is aimed at a target and detectors on the rear of the missile keep it centered in the beam. Beam riding systems are often SACLOS , but do not need to be; in other systems the beam is part of an automated radar tracking system. An example is later versions of the RIM-8 Talos missile as used in Vietnam: the radar beam was used to take the missile on a high arcing flight and then gradually brought down in

304-461: Is automatic. Is similar to MCLOS but some automatic system positions the missile in the line of sight while the operator simply tracks the target. SACLOS has the advantage of allowing the missile to start in a position invisible to the user, and is generally far easier to operate. SACLOS is the most common form of guidance against ground targets such as tanks and bunkers. Target tracking, missile tracking and control are automatic. This guidance system

342-506: Is distance. To make it possible, both target and missile trackers have to be active. They are always automatic and the radar has been used as the only sensor in these systems. The SM-2MR Standard is inertially guided during its mid-course phase, but it is assisted by a COLOS system via radar link provided by the AN/SPY-1 radar installed in the launching platform. LOSBR uses a beam of some sort, typically radio , radar or laser , which

380-432: Is not required. MCLOS is a subtype of command guided systems. In the case of glide bombs or missiles against ships or the supersonic Wasserfall against slow-moving B-17 Flying Fortress bombers this system worked, but as speeds increased MCLOS was quickly rendered useless for most roles. Target tracking is automatic, while missile tracking and control is manual. Target tracking is manual, but missile tracking and control

418-509: Is sent to the missile, often using thin metal wires or a radio link , which causes it to steer back toward the center of the line-of-sight. Common examples of these weapons include the BGM-71 TOW wire-guided anti-tank guided missile (ATGM) and the Rapier radio-command surface-to-air missile (SAM). Another class of SACLOS weapons is based on the beam riding principle. In this case,

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456-466: Is steered by an unconventional arrangement of vibrating spoilers. As stated before, MCLOS requires considerable skill on the part of the operator. The system's effectiveness in combat drove the development of missiles based on the easier to use SACLOS system. One problem with the missile is the amount of time it takes to reach maximum range—around 20 seconds—giving the intended target time to take action, either by retreating behind an obstacle, laying down

494-423: Is that the missile sends target tracking information back to the guidance system to aid it to calculate an intercept. This negates much of the accuracy disadvantage of pure command guidance. Examples of missiles which use command guidance include: Older western missiles tend to use pure semi-active radar homing . Pure command guidance is not normally used in modern surface-to-air missile (SAM) systems since it

532-426: Is too inaccurate during the terminal phase, when a missile is about to intercept a target. This is because the ground-based radars are distant from the target and the returned signal lacks resolution. However, it is still quite practical to use it to guide a missile to a location near a target, and then use another more accurate guidance method to intercept the target. Almost any type of terminal guidance can be used, but

570-527: The 9M113 Konkurs . The 3M6 Shmel began development through Decree No. 7 on May 27, 1957. Development would be spread across several bureaus and research institutes, with the missile complex and rocket being designed by SKB-4 , led by Boris Shavyrin under the leadership of the to-be famous Sergey Nepobedimy , being based on the Nord Aviation SS.10 . Teams from TsNII-113  [ ru ] , led by Zinovy Moiseevich Persits, would handle

608-527: The US Army journal Military Review as being 'about the same size' and having 'approximately the same range' as the French SS.11 , later overestimating its range to be from 500 to 3,000 metres. There were two ground-based platforms for the missile These vehicles were deployed in anti-tank batteries attached to motor rifle regiments . Each battery has three platoons , each with three launch vehicles and

646-499: The anti-aircraft role, the target is typically already being illuminated by a radar signal. However, a beam-riding missile flies directly at the target, which is often inefficient for a high-speed target like an aircraft. For this reason, most anti-aircraft missiles follow their own route to intercept the target, and do not ride the beam. A more modern use of beam-riding uses laser signals because they are compact, less sensitive to distance, and are difficult to detect and jam. This

684-432: The beam motion into account. CLOS guidance is used mostly in shortrange air defense and antitank systems. Both target tracking and missile tracking and control are performed manually. The operator watches the missile flight, and uses a signaling system to command the missile back into the straight line between operator and target (the "line of sight"). This is typically useful only for slower targets, where significant "lead"

722-546: The center of the field of view, and the electronics automatically apply a correction instruction in the opposite direction of the change to re-center the missile. These instructions are delivered either by a radio link or a wire. Radio links have the disadvantage of being jammable , whereas wire links have the disadvantages of being limited to the length of the wire and fragile (i.e. not very good for penetrating/attacking targets in vegetated areas such as forests) and can not be fired over bodies of water due to potential shorting of

760-561: The design of the control system . Meanwhile, the charge for the solid-propellant rocket engine would be designed by NII-125 , and the HEAT warhead by NII-6 . Development of the missile proceeded rapidly, with the first unguided flights in April 1958 followed by controlled flights in June and July 1958, where testing showed the probability of a hit to be anywhere from 75—90%, depending on

798-417: The guidance system will relay commands to a missile, telling it to move the fins in a way that steers in the direction needed to maneuver to an intercept course with the target. If the target maneuvers, the guidance system can sense this and update the missiles' course continuously to counteract such maneuvering. If the missile passes close to the target, either its own proximity or contact fuze will detonate

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836-431: The inherent weakness of inaccuracy with increasing range as the beam spreads out. Laser beam riders are more accurate because beams of lasers spread less than of radars, but are all short-range, and a laser can be degraded by bad weather. In contrast, SARH becomes more accurate with decreasing distance to a target, so the two systems are complementary. Track-via-missile is a variant of command guidance. The main difference

874-414: The launcher and tell the missile where to steer to intercept its target. This control may also command the missile to detonate, even if the missile has a fuze . Typically, the system giving the guidance commands is tracking both the target and the missile or missiles via radar . It determines the positions and velocities of a target and a missile, and calculates whether their paths will intersect. If not,

912-422: The launcher and missile cannot easily be broken or jammed. But, they have a disadvantage because the guidance signal may be detected by the target. Examples include the laser-guided RBS 70 SAM and 9M120 Svir ATGM. With wire- and radio-guided SACLOS, the sighting device can calculate the angular difference in direction from the missile position to the target location. It can then give electronic instructions to

950-445: The launcher and the target (LOS), and any deviation of the missile from this line is corrected. Since so many types of missile use this guidance system, they are usually subdivided into four groups: A particular type of command guidance and navigation where the missile is always to commanded lie on the line of sight (LOS) between the tracking unit and the aircraft is known as command to line of sight (CLOS) or three-point guidance. That is,

988-469: The missile is controlled to stay as close as possible on the LOS to the target. More specifically, if the beam acceleration is taken into account and added to the nominal acceleration generated by the beam-rider equations, then CLOS guidance results. Thus, the beam rider acceleration command is modified to include an extra term. The beam-riding performance described above can thus be significantly improved by taking

1026-409: The missile near the center of the gunners line of sight immediately after launch, and a narrow view lens with automatic zoom that accomplishes the fine tracking adjustments. In most configurations, the narrow field camera utilizes electronics that translate the brightest spot in the view – the flare or strobe of the missile – into an electrical impulse. This impulse changes as the missile leaves

1064-481: The missile that correct its flight path so it is flying along a straight line from the sighting device to the target. Most antitank SACLOS systems such as Milan and TOW use a strobe or flare ( visible , infrared (IR) or ultraviolet (UV) light) in the tail of the missile with an appropriate sensor on the firing post, to track the missile's flight path. The launching station incorporates a tracking camera with two lenses. A wide field of view lens that locates and "gathers"

1102-409: The opposite of manual command to line of sight (MCLOS) ones, thus allowing updated version of such anti-tank weapons (notably AT-3 Malyutka ) to still remain in service in some countries. Command guidance Command guidance is a type of missile guidance in which a ground station or aircraft relay signals to a guided missile via radio control or through a wire connecting the missile to

1140-538: The process of jet formation of high-explosive anti-tank (HEAT) charges, thus maximizing weapon's effectiveness. However, such systems don't allow for a top-attack mode, or target illumination from a different source than the launcher itself, so choice between the two operating modes may vary between operators. The main disadvantage of both SACLOS guidance systems in an anti-tank role is that working on angular differences evaluation, it does not allow any notable separation between guidance system and missile launch post

1178-423: The range. However, Soviet Army field exercises showed that hit rates could decrease to as low as 25% due to the complexity of the guidance system . The system would enter service by August 1st, 1960. Later, parade 2P27 vehicles sporting four 2K16 launchers on May 1st, 1962 were noted by Western observers in parade formation, just before the 1962 Moscow Victory Day Parade . The weapon would later be described in

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1216-411: The sighting device and/or the missile then guide it to the target. Many SACLOS weapons are based on an infrared seeker aligned with the operator's gunsight or sighting telescope . The seeker tracks the missile, either the hot exhaust from its rocket motor or flares attached to the missile airframe, and measures the angle between the missile and the centerline of the operator's sights. This signal

1254-436: The tail of the missile looks for the signal. Electronics in the missile then keep it centered in the beam. It differs from semi-active radar homing (SARH) and semi-active laser homing (SALH) in which the target is illuminated by a powerful emitter, and a sensor in the head of missile detects the reflected emissions and directs it to the target. Radar was the most common form of SACLOS signals in early systems, because, in

1292-445: The vertical plane of the target aircraft, the more accurate semi-active radar homing (SARH) being used at the last moment for the terminal homing and strike. This gave an enemy pilot the least possible warning that the aircraft was being illuminated by missile guidance radar, in contrast to search radar. This is an important distinction, as the properties of the signal differ, and are used as a cue for evasive action. LOSBR suffers from

1330-448: The warhead, or the guidance system can estimate when the missile will pass near a target and send a detonation signal. On some systems there is a dedicated radio antenna or antennas to communicate with a missile. On others, the radar can send coded pulses which a missile can sense and interpret as guidance commands. Sometimes to aid the tracking station, a missile will contain a radio transmitter, making it easier to track. Also, sometimes

1368-470: The wires. Also, wires leave a trace all the way to the target, which could help find the source of the fire. Note that almost all (unless counter counter measures are installed) wire/radio link guided ATGMs can be jammed with electro-optical interference emitters such as " Shtora-1 " on the T-90a . With beam-riding SACLOS, the sighting device emits a directional signal directed toward the target. A detector in

1406-432: Was also one of the main advantages over concurrent SALH systems regarding detection: a laser riding beam emitter is typically a low powered device and does not need to be pointed immediately to the target. Because the missile sensor looks backward to it, the whole system is also impervious to most jamming devices. Another advantage in antitank applications is that the backward-looking guidance system does not interfere with

1444-466: Was one of the first to be used and still is in service, mainly in anti-aircraft missiles. In this system, the target tracker and the missile tracker can be oriented in different directions. The guidance system ensures the interception of the target by the missile by locating both in space. This means that they will not rely on the angular coordinates like in CLOS systems. They will need another coordinate which

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