ALAS ( missile ) ALAS ( Advanced Light Attack System , ) is a new Serbian long - range multipurpose guided missile system developed by the private company EdePro which will work under the direction of Yugoimport SDPR . The new system was developed for attacks on tanks , armored fighting vehicles , fortifications , command posts , low - flying helicopters , coastal ships , industrial facilities , bridges and more . It can be used by helicopters , armored vehicles , small ships and infantry . The ALAS uses a combined TV / IC guidance , which cannot be jammed . The missile is guided using a fiber - optic cable which connects the missile to the launcher . ALAS flies at very low attitude and has very small radar and IC reflexive . This missile uses a turbofan motor instead of a turbojet motor . A secondary use for this system is as an UAV . Description of system and role . The ALAS , missile system is intended for two kinds of primary mission : Tactical role . The ALAS missile system is intended for attack distant target as : Variants . There are two main types of system depending on missiles used as ALAS or LORANA system . ALAS . The ALAS missile is hot - launched from its canister by means of a solid - propellant boost motor . Alas is designation for missiles produced in Alas - A , Alas - B and Alas - C variants . For UAE it will be delivered on Nimr 6x6 chassis . Design of ALAS - C abandoned the initial design of the structure , the structure of the initial integration expand the arrow wing forward , small aerodynamic rudder control , axial turbine engine is equipped with a single nozzle . New the ALAS - C missiles actually installed the turbojet in the stretch LORANA of missile X - type wing control of the rudder head mounted at a 45 ° cross . Located in the wing front part on both sides of the elastomer is of the two intake ports of the engine , the wing rear portion on both sides of the elastomer is two flat engine nozzle , fiber spool is located in the nozzle rear . Employing an ins or optionally a gps guidance system the Alas - c will have a range of up to 25 km , using a tv / ccs / iir homing head to deliver its fragmentation warhead . Guidance . The missile is programmed to follow a preset course around or over obstructing terrain using electronic terrain maps and inertial guidance . An infrared imaging is used for the terminal guidance phase , also it is possible to transfer the thermal images back to the launching platform via a 200 MBit / s data link provided by an optical fibre , and manually select the target or avoid collateral damage by aborting mission . Missile communication is realized via optical monomode cable with two channels ( communication directions ) : Firing station comprises a high - performance compact computer for missile guidance , an operator control panel and a high - resolution display . The system uses advanced control and image processing algorithms , electro - optical converters and radio links . The firing station has an optional Global Positioning System ( GPS ) , and north - seeking device . The firing station used for mission planning before the engagement . For mission planning the firing station stores a digitized map and displays the map during missile flight . For some mission applications , a dual monitor system used . The firing unit used as a trainer and simulator without additional hardware . When attacking ships , missiles can fly at an altitude of a few meters above sea level . At this stage of the flight , the flight controls are made according to pre - programmed data , when the rocket fly to the target area , gunners seize control and joystick controls and screen . Propulsion . During launch , a solid propellant booster accelerates the missile to an initial cruising speed ( 120 – 150 m / s ) . The turbojet engine TMM - 040 ignited to take the missile to the target under control of the guidance system and the operator to control the missile speed . Main propulsion characteristics : LORANA . There is a solid propellant sustainer rocket engine and accelerated with solid propellant booster engine variant instead turbojet with range estimated to 9 km with greater speed designated LORANA ( LOng RAnge Non line of sight Attack system ) . Lorana has a 10 kg mono - HEAT or tandem warhead . LORANA is intended for use from land or helicopter platforms for launch . Lorana missile seeker was tested in mid 2012 on light aircraft SILA 450C domestic aircraft ( made in Kraljevo , Serbia by Aero - East - Europe ) in a series of 10 flights above military multibranch exercise range " Pasuljanske livade " Serbia . LORANA represents advanced remote non - line of sight attack system battery which consists of battery command post ( based on light wheeled armored SUV or semi ) and four launch vehicles , with each vehicle equipped with 4 to 6 containers with missiles . Also , there is a missile carrier , for reloading missiles or as a backup control car . Lorana missile consists of the following functional units - sub - systems : Guidance . The nose missile is mounted with TV unit , which allows the detection of target size tank at distances within 3 km . Field of view cameras used in TV display unit is 7 ° x 5 ° . Fiber optic cable can handle pulling force 52 N . Loss signal in an optical cable is 0 . 2 dB / km . Optical Cable provides direction of ground control kit on board missile data transmission rate of 128 kbit / s and direction of the missile deck to ground control station data transmission speed of 240 Mbi / s - this direction is available one video channel and two data channels . Firing station works in same principle as for ALAS rockets . According to available data Lorana can achieve accuracy of intervention chosen destination with a maximum deviation of 1 m . Operational use . Missile takes off from the shipping container - starter . Lorana can be stored in a container more than 10 years without the need preventive maintenance . After the installation on the carrier is ready for immediate use .