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The Blowpipe’s guidance is initially semi-automatic with the missile gathered to the centre of the sight’s crosshairs by the infrared optic atop the aiming unit. Two to three seconds after launch, missile guidance is switched to fully MCLOS mode, and the operator regains full control of the missile. The operator has to steer the missile all the way to its target manually via a small thumb joystick. The operator can opt not to use autogathering when engaging low flying targets such as helicopters, but then has to super-elevate the launcher to ensure that the missile does not hit the ground. Four flares in the tail of the missile make it visible in flight, first to the infrared optic, then to the operator. Detonation is either by proximity or contact fuse.

In emergencies, the operator can end an engagement by shutting off the power to the transmitter with the system switch, after which the missile will immediately self-destruct. The aiming unit can then be removed from the empty missile container and fitted to a new round.

The missile’s uncooled lead sulphide passive infra-red seeker head detects infrared radiation at below 2.8 μm in wavelength. It has a 1.9 degree field of view and can track at 9 degrees per second. The seeker head tracks the target with an amplitude-modulated spinning reticle (spin-scan or AM tracking), which attempts to keep the seeker constantly pointed towards the target. The spinning reticle measures the amount of incoming infrared (IR) energy. It does this by using a circular pattern that has solid portions and slats that allow the IR energy to pass through to the seeker. As the reticle spins IR energy passes through the open portions of the reticle. Based on where the IR energy falls on the reticle the amount or amplitude of IR energy allowed through to the seeker increases the closer to the center of the reticle. Therefore, the seeker is able to identify where the center of the IR energy is. If the seeker detects a decrease in the amplitude of the IR energy it steers the missile back towards where the IR energy was the strongest. The seeker’s design creates a dead-space in the middle of the reticle. The center mounted reticle has no detection capability. This means that as the seeker tracks a target as soon as the seeker is dead center, (aimed directly at the IR source) there is a decrease in the amplitude of IR energy. The seeker interprets this decrease as being off target so it changes direction. This causes the missile to move off target until another decrease in IR energy is detected and the process repeats itself. This gives the missile a very noticeable wobble in flight as the seeker bounces in and out from the dead-space. This wobble becomes more pronounced as the missile closes on the target as the IR energy fills a greater portion of the reticle. These continuous course corrections effectively bleed energy from the missile reducing its range and velocity.

The longitudinal level serves to control and deliver the grenade launcher a given elevation angle when firing from a closed fire position. The head of the sight is used for sighting on the target (point of focusing) in it an optical system is assembled. There is an eyepiece on the head; On the left – a sight and a point for direct guidance for grenade launchers in case of damage to the optical system; On top – the base for attaching the lamp holder of the sighting grid; Front on the rim – two screws for fixing the light filter. The optical system of the sight consists of an objective, a prism, a grid, an eyepiece and protective glass. The lens is intended for obtaining images of the observed object. The prism is a wrapping system and serves to obtain a real direct image. The eyepiece serves to increase the viewing of the image of the observed object and the grid. Protective glass protects the sight from getting inside dust and dirt. Through it, the grid of the sight is illuminated. The mesh of the sight is a plate on which the scales of the angles of sight and lateral corrections are plotted.