Qiam-1 SRBM Short-Range Ballistic Missile.

Technical Data

• Design

  The Qiam-1 ballistic missile follows a single-stage cylindrical airframe architecture derived from the Scud missile family, consisting of an elongated fuselage housing the oxidizer tank, fuel tank, propulsion unit, guidance module, and payload section. The missile body is constructed using a lightweight aluminium structural airframe, reducing overall launch mass while maintaining structural strength required to withstand internal propellant pressure and aerodynamic stresses during boost and re-entry.

  A defining structural characteristic of the Qiam-1 is its finless aerodynamic configuration, eliminating the four stabilizing fins typically found on Scud-class missiles. Instead, the missile relies on thrust-vector control (TVC) within the rocket engine to maintain directional stability during the boost phase. Removing these external fins reduces aerodynamic drag and slightly decreases structural weight, improving ballistic efficiency and contributing to the missile’s extended operational range.

  The missile measures approximately 11.5 m in length, with a body diameter of about 0.88 m, and has a launch weight of roughly 6,000–6,200 kg.

  The missile is deployed on a road-mobile transporter-erector-launcher (TEL) consisting of a heavy tractor truck coupled to a multi-axle semi-trailer launch platform. The missile is transported horizontally on the trailer within a reinforced launch cradle equipped with a hydraulic erection system that raises the missile to the vertical launch position before firing.

  The launcher platform visible in the image uses a multi-axle semi-trailer chassis with four rear axles, designed to distribute the missile’s weight and support the launch structure. The trailer incorporates integrated equipment compartments along the chassis, likely containing electrical systems, launch control equipment, and hydraulic power units.

  Before launch, the TEL deploys hydraulic stabilizers and support outriggers to secure the platform to the ground and maintain stability during missile erection. A hydraulic erector arm located beneath the missile body lifts the missile from the transport position to the vertical firing position. This road-mobile configuration allows rapid relocation and enhances survivability by enabling missile units to launch from dispersed and concealed positions.

• Missile Propulsion

  The Qiam-1 is powered by a single liquid-fuel rocket engine derived from earlier Scud propulsion technology but adapted to support the missile’s finless configuration and improved flight control characteristics.

  The propulsion system uses a bipropellant mixture consisting of kerosene-based hydrocarbon fuel and inhibited red fuming nitric acid (IRFNA) oxidizer. These hypergolic propellants ignite spontaneously when combined, enabling a relatively simple ignition system and reliable engine start during launch.

  The rocket engine incorporates a gimbaled nozzle thrust-vector control system, allowing the engine nozzle to pivot during the boost phase. This mechanism provides steering control and stabilizes the missile during ascent, compensating for the absence of aerodynamic control fins.

  During the boost phase, the propulsion system accelerates the missile to hypersonic velocity, enabling it to follow a ballistic trajectory with an operational range of up to approximately 800 km. During the terminal phase of flight, the warhead descends at speeds estimated between Mach 5 and Mach 7.

  Because the missile uses liquid propellants, pre-launch fueling procedures are required, although the road-mobile TEL configuration allows launch operations from dispersed positions.

• Guidance Systems

  The Qiam-1 relies primarily on a strap-down inertial navigation system (INS) controlled by an onboard digital flight computer that calculates the missile’s trajectory during powered flight and ballistic ascent.

  The navigation system uses gyroscopes and accelerometers to measure orientation and velocity, enabling the flight computer to maintain the programmed trajectory. Corrections during the boost phase are performed through thrust-vector steering of the rocket engine.

  Some analyses indicate that the missile may also benefit from ground-based radar support during the early boost phase, allowing external tracking systems to transmit trajectory corrections shortly after launch.

  In upgraded variants equipped with maneuverable re-entry vehicles, small control surfaces on the warhead may allow limited trajectory adjustments during the terminal phase.

• Warhead

  The Qiam-1 can carry several types of conventional warheads depending on mission requirements. The standard payload is believed to consist of a high-explosive fragmentation warhead weighing approximately 650–750 kg, intended for strikes against military infrastructure and hardened targets.

  Alternative payload options may include cluster or submunition warheads, designed to disperse bomblets over a wide target area and increase effectiveness against dispersed targets such as airfields, troop concentrations, or logistical installations.

  The missile employs a separable re-entry vehicle, which detaches from the missile body during the terminal phase of flight. This design improves aerodynamic stability and reduces radar visibility, complicating interception by missile defense systems.

• Combat Use

  Within Iranian military doctrine, the Qiam-1 functions as a theater-level strike weapon capable of engaging strategic and operational targets throughout the Middle East. With an operational range approaching 800 km, the missile enables Iranian forces to strike airbases, command centers, radar installations, logistics depots, and critical infrastructure across regional theaters.

  The missile’s road-mobile TEL launch system allows missile units to operate from dispersed launch sites, increasing survivability against pre-emptive strikes and enabling rapid repositioning after launch.

  Operational doctrine suggests that Qiam missiles may be employed in coordinated missile salvos, intended to saturate enemy missile defense systems. The combination of hypersonic terminal velocity, separable warheads, and potential maneuverable re-entry vehicles increases the difficulty of interception by defensive systems.