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ZofiTech s.r.o.

ZofiTech ZT J160 turbojet engine intake view showing the compressor inlet, nose cone, and strut layout on a dark background.
ZofiTech ZT J160 high-thrust turbojet engine front view with compact cylindrical housing, exhaust cone, and connector lead on a dark background.
Close-up of the ZofiTech ZT J160 turbojet intake showing the compressor inlet, nose cone, support struts, and side-mounted ports for integration.
Side profile of the ZofiTech ZT J160 high-thrust turbojet engine on a dark background, showing the exhaust cone and compact housing.
ZofiTech ZT J160 turbojet engine shown upright with intake and nose cone visible, designed for high-thrust UAV propulsion.
Front intake view of the ZofiTech ZT J160 high-thrust turbojet engine showing the compressor inlet and hub, with side-mounted interface block.
ZofiTech ZT J160 high-thrust turbojet exhaust nozzle close-up, showing the circular outlet and internal support struts for UAV propulsion.
Close-up of a ZofiTech ZT J Series turbojet engine in a workshop, highlighting the stainless housing and compact intake assembly for UAV and target drone propulsion.
ZofiTech ZT J Series turbojet engines on a workshop bench, with the largest unit in the foreground and smaller models behind for UAV and target drone propulsion.
ZofiTech

ZT J160

Thrust 1569 N 352 Lbf
Engine diameter 261,4 mm 10.3 Inch
Engine length 700 mm 27.6 Inch
Engine weight 21 450 g 47.2 Lbs
The ZT J160 is a high-thrust, next-generation turbojet engine developed by ZofiTech for UAVs, target drones, and advanced aerospace platforms. Combining robust design, precision engineering, and exceptional efficiency, it delivers powerful performance in a compact, lightweight form. The ZT J160 ensures rapid, reliable starts and precise control under all conditions. Manufactured under the highest quality standards, each unit is fully tested and ready for deployment.
  • High thrust-to-weight ratio with exceptional efficiency
  • Compact, modular design for scalable integration
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Technical description

All data at STP ± 2%
Engine diameter 261.4 mm 10.3 in
Engine length 700 mm 27.6 in
Engine weight 21 450 g 47.2 lb
System airborne weight * 25 650 g 56.55 lb
Thrust at design RPM of 46 000 >1 569 N >352 lbf
Maximum allowed RPM 46 000 46 000
Thrust at idle RPM 75 N 16.9 lbf
Pressure ratio 4:1 4:1
Mass flow at design RPM 2 500 g/s 5.51 lb/s
Normal EGT (avg of 2 internal EGT probes) 800 °C 1 472 °F
Max EGT (avg of 2 internal EGT probes) 850 °C 1 562 °F
Fuel consumption 3 600 g/min 127 oz/min
Specific fuel consumption 38.24 g/(kN · s) 1.35 lb/(lbf · h)
Starting method: Direct kerosene starting system (<45 seconds starting time).
* Total weight of: Engine, EPV, Fuel filter, 6 cell LiPo battery, battery connector, 3 mounting straps.
Min operation temperature * -35 °C -31 °F
Max operating temperature +50 °C +122 °F
Max operating altitude 8 000 m 26 250 ft
Max operating speed 1 000 km/h 620 mph
* With the use of LiPo batteries the minimum operation temperature is limited to -10 °C (battery temperature).
1 × RS-232 or RS-485 ** Throttle and switch settings including special functions *
2 × PWM between 1–2 ms ** Throttle and switch settings (special functions * with push button)
2 × Analog inputs 0–5 V DC ** Throttle and switch settings (special functions * with push button)
* Activation of prime function, igniter function, starter function, speed cool.
** Specify EPV at ordering with PWM inputs or analog inputs / serial input RS-232 or RS-485.
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