The LF125 turbojet engine identified by the military features advanced technology, high cost performance, strong carrying capacity, good reliability and it is easy to use and maintain. It can be used in mass production on unmanned aerial vehicles and missiles.
technical indicators:
| Maximum thrust | 1250N |
| Operating speed | 34000rpm～60000rpm |
| Exhaust temperature | ≤820℃ |
| Operating altitude | 0～10000m |
| Operating airspeed | 0～0.8Ma |
| Specific fuel consumption | 0.12Kg/(N·h) |
| Weight | 20.0-0.7kg |
| Jet fuel | RP-3 |
| Outside dimensions | |
| Biggest diameter | 272mm |
| Length | 636mm |
| Permitted inclination | |
| Bank angle | ±83° |
| Pitch angle | ±90° |
| Permitted flight loads | |
| Axial | ±15g |
| Normal | ±9g |
| Lateral | ±3g |
| Starting ambient temperature | -30℃～+50℃ |
| Generator power | 28V，720W |
| Cycle of the first restoration | 50h |