A compact 160 kgf (1,569 N) micro turbojet engine purpose-built for UAVs and target drones. It combines a 20 kg dry weight with 46,000 rpm maximum speed and reliable performance up to 8 km altitude and Mach 0.8. One-button electronic starting makes ground and airborne integration simple.
The 160 kgf micro turbojet engine is designed primarily as a powerplant for unmanned aerial vehicles (UAVs) and target drones. With a diameter of just 260 mm, a length of 690 mm and a weight of 20 kg, it delivers a maximum thrust of 1,569 N (160 kgf) at a maximum rotational speed of 46,000 rpm. All data are measured at standard temperature and pressure (STP). The engine idles at 15,000 rpm with only 70 N of idle thrust, enabling smooth throttle modulation for target-drone flight profiles. Fuel flow at design speed is 216 kg/h, and exhaust gas temperature is 800 °C at maximum speed. Rated for operation up to 8 km altitude and a maximum Mach number of 0.8, it suits high-speed jet target drones and reconnaissance UAVs. The starting power supply is a compact 22.2 V, 4,500 mAh pack, simplifying ground support equipment and airborne starting systems.
Key specifications: Maximum Thrust: 1,569 N (160 kgf) at maximum speed; Diameter: 260 mm; Length: 690 mm; Weight: 20 kg; Maximum Rotational Speed: 46,000 rpm; Idle Speed: 15,000 rpm.
Specifications
| Parameter | Value | Unit |
|---|---|---|
| Maximum Thrust | 1,569 N (160 kgf) at maximum speed | |
| Diameter | 260 mm | |
| Length | 690 mm | |
| Weight | 20 kg | |
| Maximum Rotational Speed | 46,000 rpm | |
| Idle Speed | 15,000 rpm | |
| Idle Thrust | 70 N | |
| Mass Flow at Design Speed | 2,500 g/s | |
| Fuel Flow at Design Speed | 216 kg/h | |
| Exhaust Gas Temperature | 800 °C | |
| Maximum Operating Altitude | 8 km | |
| Maximum Mach Number | 0.8 | |
| Starting Power Supply | 22.2 V, 4,500 mAh | |
| Measurement Conditions | Standard temperature and pressure (STP) |
All specifications are taken from the manufacturer’s current datasheet.
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