M-13 MSRA
| M-13 MSRA | |
|---|---|
 | |
| Type | Active radar guided air-to-air missile and surface-to-air missile |
| Place of origin |  Acrea |
| Service history | |
| In service | 2008-Present |
| Used by | Acrea |
| Wars | Zemplen War |
| Production history | |
| Designer | Kobalt-Zeiss AG NordEX Försvarssystemet AB |
| Manufacturer | NordEX Försvarssystemet AB |
| Specifications | |
| Weight | 160 kg (350 lb) |
| Length | 3.1 m (10 ft 2 in) |
| Diameter | 160 mm (6.3 in) |
| Effective firing range |
|
| Warhead | High explosive blast-fragmentation |
Detonation mechanism | Proximity or direct impact fuse |
| Engine | Solid-propellant rocket motor |
| Speed | Mach 4 |
Guidance system |
|
The M-13 MSRA (Missil, strids, radar-activ), often called the "Misrah", is an active radar guided air-to-air missile and surface-to-air missile designed and manufactured by Kobalt-Zeiss AG and NordEX Försvarssystemet AB. The missile was designed to achieve the long range, multi-target capability of the previous M-10C DRAAM missiles, while utilising a smaller missile with very high kinematic performance. It was designed in tandem with the M-9 IRSS infrared missile for use with the EF-633 Mako and EF-662 Vampyr fighters, as well as to equip the EF-135 Draken with more capable armament. The missile has an operational range exceeding 100 km. To achieve its maneuvering performance, the MSRA
Design
Propulsion
The DAAMR is propelled by a throttleable ducted rocket with an integrated nozzleless booster, which provides the missile with a long range, a high average speed, a wide operational envelope, a flexible mission envelope, relatively simple design, and ease of logistics. The propulsion system consists of four main components: a ramcombustor with integrated nozzleless booster, two air intakes, the interstage, and the sustain gas generator.
The solid propellant nozzleless booster is integrated within the ramcombustor and accelerates the missile to a velocity where the ramjet can ignite. The air intakes and the port covers which seal the intake diffusors from the ramcombustor remain closed during the boost phase. The interstage is mounted between the gas-generator and the ramcombustor and contains the ignition unit, the booster igniter, and the gas generator control valve. The gas generator is ignited by the hot gases from the booster combustion which flow through the open control valve. The gas generator contains an oxygen deficient composite solid propellant which produces a hot, fuel-rich gas which auto-ignites in the air which has been decelerated and compressed by the intakes. The high energy boron-loaded propellant provides a roughly threefold increase in specific impulse compared to conventional solid rocket motors.
Thrust is controlled by a valve which varies the throat area of the gas generator nozzle. Reducing the throat area increases the pressure in the gas generator which increases the propellant burn rate, increasing the fuel mass flow into the ramcombustor. The mass flow can be varied continuously over a ratio greater than 10:1.
Control
A two-way datalink between the missile and the launch aircraft allows the weapon to receive mid-course target updates and even be re-targeted mid-flight. The missile is also capable of being handed off to third-party command, such as from an airborne early warning and control aircraft, allowing the launching aircraft to move to other tasks. The missile is also capable of reporting its status, including its functionality and target information, back to the weapon controller via the datalink.
Warhead
Terminal guidance for the DAAMR is provided by an active-radar seeker head. The active-radar proximity fuze uses information provided by four antennae symmetrically-mounted around the missile body behind the seeker head to calculate the optimum time and range to detonate the blast-fragmentation warhead in order to achieve the maximum lethal effect against the target.
