• Source: PBS AI-PBS-350

The AI-pbs" target="_blank">PBS-350 is a turbojet engine jointly developed by Czech manufacturer pbs" target="_blank">PBS Velká Bíteš and the Ukrainian design bureau Ivchenko-Progress. The engine is marketed for use in missiles and large unmanned aerial systems. As of 2024, it is currently the highest thrust engine developed by pbs" target="_blank">PBS, exceeding the thrust of pbs" target="_blank">PBS's next highest engine, the pbs" target="_blank">PBS TJ150.




History


On the 19th of June, 2023, Velka Bites and Ivchenko-Progress signed a memorandum of understanding, detailing the framework from which the engine would be developed and produced.
Concerns were raised about Ivchenko-Progress' capability to produce the engine, with its headquarters in Zaporizhzhia, a city heavily affected by the Russian invasion of Ukraine. Ivor Kravchenko, the director general for Ivchenko-Progress stated that while the factory had sustained damage, it continues to operate, with strong backing from the Ukrainian government enabling it to maintain its 3000 strong workforce.
The engine was displayed at the 2024 Farnborough International Airshow, along with other products from pbs" target="_blank">PBS, such as turbine engines, Auxiliary power units and environmental control systems.




Design


The AI-pbs" target="_blank">PBS-350 is a compact turbojet engine optimized for single mission UAV systems. It features a four stage compressor, driven by a single stage turbine. It has a digital engine control unit and a fuel metering pump. Along with pyrotechnic ignition, it also utilizes windmill starting, wherein the aircraft uses its forward momentum to turn the rotor blades, reducing the weight of the system and improving performance.




Specifications


Data from



General characteristics

Type: turbojet
Length: 706 mm
Diameter: 298 mm
Dry weight: 51 kg



Components

Compressor: four-stage axial compressor
Turbine: single-stage axial turbine



Performance

Maximum thrust: 3400 N
Specific fuel consumption: 0.125 lb/(lbf⋅h) (3.5 g/(kN⋅s))
Thrust-to-weight ratio: 6.1




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