Long range aircraft missile Meteor

The rocket (see the scheme) is made according to the normal aerodynamic scheme and has a high value of transverse V-wing (45°). For aerodynamic control and stabilization, a cruciform tail fin is used.

The propulsion system combined with an integrated layout consists of a direct-flow air jet engine (DAS) with a modulo-adjustable thrust and a starting accelerator, which are placed in a single housing. The launch accelerator is equipped with a low-smoke blended fuel charge and, after separation of the rocket from the launch vehicle, ensures its acceleration to the launch speed of the SARD march.

The gas generator charge of the marching SARD is based on heavy boron containing fuel with the volume heat of combustion more than 5x104MJ/m3. The consumption and composition of the generated gas can be changed in a sufficiently wide range in accordance with the flight conditions and the direct-flow circuit operation mode for all conditions of the missile's combat application. The depth of control of the generated gas flow of the SARD is more than 10:1 and is provided by a special valve in the nozzle of the gas generator.

The combustion chamber and the engine gas generator are made of heat-resistant steel. Air intakes located on the outer side of the rocket body are made of titanium. The engine is designed by Bayern-Chemie Protac.

The use of the RVD provides an increase in the average rocket speed and range. According to advertising materials, the maximum range of the missile reaches 150 km.

The combat unit is a shrapnel and blast furnace with a weight of 25 kg, equipped with radar non-contact and contact fuses. The fuse has four antennas located in the nose section, and when a target is detected, it ensures that the BC is detonated at a distance optimal for causing maximum damage. The fuse is designed by Saab Bofors Dynamics, a Swedish company.

A combined control system is used to control the missile: a command-inertial system at the starting point of the trajectory and a homing system at the final point.

The missile is equipped with a two-way asynchronous data line channel and is capable of receiving control commands from the carrier aircraft and interacting aircraft, including AWACS system aircraft. The transmission of these commands corrects the missile by updating target position information, compensating for aiming errors, and the drift of the inertial control system, which increases over time. Telemetry information from the missile's on-board systems is transmitted to the carrier in real time via a return data channel.

The Meteor rocket is equipped with an active homing radar head, which is based on technologies used on Aster and MICA missiles. In addition to the standard high repetition rate mode, the medium-range repetition rate mode has been introduced in the missile's ARGS to meet the requirements for all-round application and engagement of low-flying targets. By using sophisticated signal processing algorithms, Meteor is able to track and engage targets in the group, as well as under conditions of strong interference and countermeasures.  The modified proportional guidance method is used to solve the task of launching the missile into the target area and pointing at the final trajectory section.

In accordance with the Integrated Logistics Support concept, Meteor is delivered to the customer in a special container equipped with a diagnose system and does not require special verification equipment during storage. If a malfunction is detected, the rocket in the container is returned to the manufacturer.