Micro
Product Catalogue
Micro turbojet engines, 4.5 to 200 kgf
Fourteen production models across three thrust classes. All figures are measured at the design point: H = 0 km, Ma = 0, ambient temperature 15 °C, ambient pressure 101,325 Pa.
Micro
Micro
Micro
Mid
Mid
Mid
Mid / Heavy
Heavy
Heavy
Heavy
Heavy
* HK-400A / HK-800A are the standard versions; HK-400B / HK-800B are the generator-equipped versions with the same thrust output.
Comparison
Side-by-side technical comparison
Swipe horizontally on mobile. All values from the factory technical parameter list.
Micro class — HK-45A / 80A / 100A / 180A
| Parameter | HK-45A | HK-80A | HK-100A | HK-180A |
|---|---|---|---|---|
| Max thrust | 4.5 kgf | 8.0 kgf | 10.0 kgf | 18.0 kgf |
| Max RPM | 225,000 | 165,000 | 125,000 | 115,000 |
| Specific fuel consumption | 2.15 | 2.10 | 2.16 | 1.73 |
| Fuel flow at max | 161.25 g/min | 280 g/min | 432 g/min | 519 g/min |
| Airflow | 0.125 kg/s | 0.160 kg/s | 0.240 kg/s | 0.363 kg/s |
| Pressure ratio | 2.2 | 2.3 | 2.8 | 3.2 |
| Exhaust gas temperature | 800 °C | 800 °C | 800 °C | 800 °C |
| Diameter × length | 60 × 165 mm | 84 × 213 mm | 101 × 267 mm | 112 × 285 mm |
| Engine weight / system weight | 0.54 / 0.15 kg | 1.1 / 0.2 kg | 1.5 / 0.2 kg | 2.1 / 0.3 kg |
| Thrust-to-weight (core / total) | 11.54 / 8.33 | 8.88 / 7.27 | 7.69 / 6.67 | 10.00 / 8.57 |
| Idle RPM / idle thrust | 51,000 / 0.5 kgf | 50,000 / 0.5 kgf | 40,000 / 0.45 kgf | 38,000 / 0.64 kgf |
| Max flight Mach number | 0.6 | 0.6 | 0.7 | 0.7 |
| Max operating altitude | 6,000 m | 6,000 m | 6,000 m | 6,000 m |
| Max start altitude | 4,500 m | 4,500 m | 3,000 m | 4,500 m |
| Start time | < 40 s | < 40 s | < 40 s | < 40 s |
Mid class — HK-400A/B / 450A / 650A / 800A
| Parameter | HK-400A | HK-400B | HK-450A | HK-650A | HK-800A |
|---|---|---|---|---|---|
| Max thrust | 40.0 kgf | 40.0 kgf | 45 kgf | 65 kgf | 80.0 kgf |
| Max RPM | 96,500 | 96,500 | 82,000 | 71,500 | 62,000 |
| Specific fuel consumption | 1.55 | 1.55 | 1.58 | 1.55 | 1.45 |
| Fuel flow at max | 1,033 g/min | 1,033 g/min | 1,185 g/min | 1,679.2 g/min | 1,933.3 g/min |
| Airflow | 0.662 kg/s | 0.662 kg/s | 0.78 kg/s | 1.02 kg/s | 1.25 kg/s |
| Pressure ratio | 3.8 | 3.8 | 4.35 | 4.35 | 4.05 |
| Exhaust gas temperature | 780 °C | 780 °C | 780 °C | 780 °C | 780 °C |
| Diameter × length | 148 × 319 mm | 148 × 350 mm | 148 × 386 mm | 170 × 445 mm | 202 × 465 mm |
| Engine weight / system weight | 4.02 / 0.358 kg | 4.87 / 1.18 kg | 5.09 / 0.358 kg | 7.39 / 0.40 kg | 10.2 / 0.61 kg |
| Thrust-to-weight (core / total) | 10.9 / 9.95 | 10.9 / 8.21 | 11.25 | 10.32 | 8.34 / 7.84 |
| Generator output | — | DC 28 V · 650 W | — | — | — |
| Idle RPM / idle thrust | 30,000 / 1.65 kgf | 30,000 / 1.65 kgf | 26,720 / 2.20 kgf | 22,880 / 3.10 kgf | 21,000 / 4.0 kgf |
| Max flight Mach number | 0.8 | 0.8 | 0.8 | 0.8 | 0.8 |
| Max operating altitude | 8,000 m | 8,000 m | 8,000 m | 8,000 m | 10,000 m |
| Max start altitude | 4,500 m | 4,500 m | 4,500 m | 4,500 m | 4,500 m |
| Start time | < 40 s | < 40 s | < 40 s | < 50 s | < 50 s |
HK-400A is the standard version, HK-400B is the generator version. HK-800B (generator version, 1,200 W) shares the HK-800A core with a 480 mm overall length and 10.8 kg engine weight.
Heavy class — HK-800B / 1050A / 1200A / 1600A / 2000A
| Parameter | HK-800B | HK-1050A | HK-1200A | HK-1600A | HK-2000A |
|---|---|---|---|---|---|
| Max thrust | 80.0 kgf | 105 kgf | 120 kgf | 160 kgf | 200 kgf |
| Max RPM | 62,000 | 56,500 | 50,500 | 46,000 | 41,500 |
| Specific fuel consumption | 1.45 | 1.42 | 1.35 | 1.33 | 1.30 |
| Fuel flow at max | 1,933.3 g/min | 2,485.0 g/min | 2,700 g/min | 3,546.7 g/min | 4,333.3 g/min |
| Airflow | 1.25 kg/s | 1.64 kg/s | 1.88 kg/s | 2.5 kg/s | 3.13 kg/s |
| Pressure ratio | 4.05 | 4.35 | 4.05 | 4.1 | 4.6 |
| Exhaust gas temperature | 780 °C | 780 °C | 780 °C | 780 °C | 780 °C |
| Diameter × length | 202 × 480 mm | 215 × 562 mm | 248 × 588 mm | 264 × 614 mm | 295 × 690 mm |
| Engine weight / system weight | 10.8 / 1.21 kg | 10.00 / 0.61 kg | 17.9 / 1.2 kg | 21.0 / 1.5 kg | 29.00 / 1.8 kg |
| Thrust-to-weight (core / total) | 8.34 / 7.41 | 11.18 / 10.5 | 7.2 / 6.7 | 8.20 / 7.62 | 7.35 / 6.90 |
| Generator output | DC 28 V · 1,200 W | — | — | — | — |
| Idle RPM / idle thrust | 21,000 / 4.0 kgf | 18,080 / 5.0 kgf | 18,000 / 7.5 kgf | 15,000 / 8.5 kgf | 13,280 / 10.30 kgf |
| Max flight Mach number | 0.8 | 0.9 | 0.9 | 0.95 | 0.95 |
| Max operating altitude | 10,000 m | 10,000 m | 10,000 m | 12,000 m | 16,000 m |
| Max start altitude | 4,500 m | 4,500 m | 4,500 m | 4,500 m | 4,500 m |
| Start time | < 50 s | < 50 s | < 60 s | < 60 s | < 80 s |
Specific fuel consumption in kg/(kgf·h). Accel/decel time is 6 s / 8 s on every model. Total service life 60 h, first overhaul (TBO) 25 h. Fuel: aviation kerosene or diesel blended with 5% turbine oil; lubricating oil: Mobil Jet Oil II.
Full Specifications
Model-by-model technical data
Click any model to expand its complete specification sheet.
HK-45A
Micro class · 4.5 kgf thrust · Ø60 × 165 mm · 0.54 kg
Max thrust4.5 kgf
Max RPM225,000 rpm
Engine / system weight0.54 kg / 0.15 kg
Thrust-to-weight (core/total)11.54 / 8.33
SFC at max2.15 kg/(kgf·h)
Fuel flow at max161.25 g/min
Inlet airflow0.125 kg/s
Pressure ratio2.2
Max exhaust temperature800 °C
Idle RPM51,000 rpm
Idle thrust0.5 kgf
Idle SFC6.0 kg/(kgf·h)
Idle fuel flow50 g/min
Start methodElectric starter / fuel start
Start time< 40 s
Max start altitude4,500 m
Max operating altitude6,000 m
Max flight Mach number0.6
Accel / decel time< 6 s / < 8 s
Diameter × length60 × 165 mm
Total life / first overhaul (TBO)60 h / 25 h
FuelAviation kerosene / diesel blended with 5% turbine oil
Lubricating oilMobil Jet Oil II
Design pointH = 0 km, Ma = 0, ambient 15 °C, 101,325 Pa
HK-80A
Micro class · 8 kgf thrust · Ø84 × 213 mm · 1.1 kg
Max thrust8 kgf
Max RPM165,000 rpm
Engine / system weight1.1 kg / 0.2 kg
Thrust-to-weight (core/total)8.88 / 7.27
SFC at max2.1 kg/(kgf·h)
Fuel flow at max280 g/min
Inlet airflow0.160 kg/s
Pressure ratio2.3
Max exhaust temperature800 °C
Idle RPM50,000 rpm
Idle thrust0.5 kgf
Idle SFC6.0 kg/(kgf·h)
Idle fuel flow50 g/min
Start methodElectric starter / fuel start
Start time< 40 s
Max start altitude4,500 m
Max operating altitude6,000 m
Max flight Mach number0.6
Accel / decel time< 6 s / < 8 s
Diameter × length84 × 213 mm
Total life / first overhaul (TBO)60 h / 25 h
FuelAviation kerosene / diesel blended with 5% turbine oil
Lubricating oilMobil Jet Oil II
Design pointH = 0 km, Ma = 0, ambient 15 °C, 101,325 Pa
HK-100A
Micro class · 10 kgf thrust · Ø101 × 267 mm · 1.5 kg
Max thrust10 kgf
Max RPM125,000 rpm
Engine / system weight1.5 kg / 0.2 kg
Thrust-to-weight (core/total)7.69 / 6.67
SFC at max2.16 kg/(kgf·h)
Fuel flow at max432 g/min
Inlet airflow0.240 kg/s
Pressure ratio2.8
Max exhaust temperature800 °C
Idle RPM40,000 rpm
Idle thrust0.45 kgf
Idle SFC8.7 kg/(kgf·h)
Idle fuel flow65.25 g/min
Start methodElectric starter / fuel start
Start time< 40 s
Max start altitude3,000 m
Max operating altitude6,000 m
Max flight Mach number0.7
Accel / decel time< 6 s / < 8 s
Diameter × length101 × 267 mm
Total life / first overhaul (TBO)60 h / 25 h
FuelAviation kerosene / diesel blended with 5% turbine oil
Lubricating oilMobil Jet Oil II
Design pointH = 0 km, Ma = 0, ambient 15 °C, 101,325 Pa
HK-180A
Micro class · 18 kgf thrust · Ø112 × 285 mm · 2.1 kg
Max thrust18 kgf
Max RPM115,000 rpm
Engine / system weight2.1 kg / 0.3 kg
Thrust-to-weight (core/total)10.00 / 8.57
SFC at max1.73 kg/(kgf·h)
Fuel flow at max519 g/min
Inlet airflow0.363 kg/s
Pressure ratio3.2
Max exhaust temperature800 °C
Idle RPM38,000 rpm
Idle thrust0.64 kgf
Idle SFC8.91 kg/(kgf·h)
Idle fuel flow95 g/min
Start methodElectric starter / fuel start
Start time< 40 s
Max start altitude4,500 m
Max operating altitude6,000 m
Max flight Mach number0.7
Accel / decel time< 6 s / < 8 s
Diameter × length112 × 285 mm
Total life / first overhaul (TBO)60 h / 25 h
FuelAviation kerosene / diesel blended with 5% turbine oil
Lubricating oilMobil Jet Oil II
Design pointH = 0 km, Ma = 0, ambient 15 °C, 101,325 Pa
HK-400A / HK-400B
Mid class · 40 kgf thrust · Ø148 × 319/350 mm · 4.02 kg (A)
Max thrust40 kgf
Max RPM96,500 rpm
Engine weight (A / B)4.02 kg / 4.87 kg
System weight (A / B)0.358 kg / 1.18 kg
Thrust-to-weight (core/total)10.9 / 9.95
SFC at max1.55 kg/(kgf·h)
Fuel flow at max1,033 g/min
Inlet airflow0.662 kg/s
Pressure ratio3.8
Max exhaust temperature780 °C
Idle RPM30,000 rpm
Idle thrust1.65 kgf
Idle SFC5.45 kg/(kgf·h)
Idle fuel flow150 g/min
Start methodElectric starter / fuel start
Start time< 40 s
Max start altitude4,500 m
Max operating altitude8,000 m
Max flight Mach number0.8
Accel / decel time< 6 s / < 8 s
Diameter × length148 × 319 mm (A) / 148 × 350 mm (B)
Generator output (version B)DC 28 V ±1.2 V, max output 650 W
Total life / first overhaul (TBO)60 h / 25 h
FuelAviation kerosene / diesel blended with 5% turbine oil
Lubricating oilMobil Jet Oil II
Design pointH = 0 km, Ma = 0, ambient 15 °C, 101,325 Pa
HK-450A
Mid class · 45 kgf thrust · Ø148 × 386 mm · 5.09 kg
Max thrust45 kgf
Max RPM82,000 rpm
Engine / system weight5.09 kg / 0.358 kg
Thrust-to-weight (core/total)12.36 / 11.25
SFC at max1.58 kg/(kgf·h)
Fuel flow at max1,185 g/min
Inlet airflow0.78 kg/s
Pressure ratio4.35
Max exhaust temperature780 °C
Idle RPM26,720 rpm
Idle thrust2.20 kgf
Idle SFC5.18 kg/(kgf·h)
Idle fuel flow189.9 g/min
Start methodElectric starter / fuel start
Start time< 40 s
Max start altitude4,500 m
Max operating altitude8,000 m
Max flight Mach number0.8
Accel / decel time< 6 s / < 8 s
Diameter × length148 × 386 mm
Total life / first overhaul (TBO)60 h / 25 h
FuelAviation kerosene / diesel blended with 5% turbine oil
Lubricating oilMobil Jet Oil II
Design pointH = 0 km, Ma = 0, ambient 15 °C, 101,325 Pa
HK-650A
Mid class · 65 kgf thrust · Ø170 × 445 mm · 7.39 kg
Max thrust65 kgf
Max RPM71,500 rpm
Engine / system weight6.30 kg / 0.40 kg
Thrust-to-weight (core/total)11.02 / 10.32
SFC at max1.55 kg/(kgf·h)
Fuel flow at max1,679.2 g/min
Inlet airflow1.02 kg/s
Pressure ratio4.35
Max exhaust temperature780 °C
Idle RPM22,880 rpm
Idle thrust3.10 kgf
Idle SFC5.21 kg/(kgf·h)
Idle fuel flow269.2 g/min
Start methodElectric starter / fuel start
Start time< 50 s
Max start altitude4,500 m
Max operating altitude8,000 m
Max flight Mach number0.8
Accel / decel time< 6 s / < 8 s
Diameter × length170 × 445 mm
Total life / first overhaul (TBO)60 h / 25 h
FuelAviation kerosene / diesel blended with 5% turbine oil
Lubricating oilMobil Jet Oil II
Design pointH = 0 km, Ma = 0, ambient 15 °C, 101,325 Pa
HK-800A / HK-800B
Mid / heavy class · 80 kgf thrust · Ø202 × 465/480 mm · 10.2 kg (A)
Max thrust80 kgf
Max RPM62,000 rpm
Engine weight (A / B)10.2 kg / 10.8 kg
System weight (A / B)0.61 kg / 1.21 kg
Thrust-to-weight (core/total)8.34 / 7.84
SFC at max1.45 kg/(kgf·h)
Fuel flow at max1,933 g/min
Inlet airflow1.25 kg/s
Pressure ratio4.05
Max exhaust temperature780 °C
Idle RPM21,000 rpm
Idle thrust4 kgf
Idle SFC5.64 kg/(kgf·h)
Idle fuel flow376 g/min
Start methodElectric starter / fuel start
Start time< 50 s
Max start altitude4,500 m
Max operating altitude10,000 m
Max flight Mach number0.8
Accel / decel time< 6 s / < 8 s
Diameter × length202 × 465 mm (A) / 202 × 480 mm (B)
Generator output (version B)DC 28 V ±1.2 V, max output 1,200 W
Total life / first overhaul (TBO)60 h / 25 h
FuelAviation kerosene / diesel blended with 5% turbine oil
Lubricating oilMobil Jet Oil II
Design pointH = 0 km, Ma = 0, ambient 15 °C, 101,325 Pa
HK-1050A
Heavy class · 105 kgf thrust · Ø215 × 562 mm · 10.0 kg
Max thrust105 kgf
Max RPM56,500 rpm
Engine / system weight10.00 kg / 0.61 kg
Thrust-to-weight (core/total)11.18 / 10.50
SFC at max1.42 kg/(kgf·h)
Fuel flow at max2,485.0 g/min
Inlet airflow1.64 kg/s
Pressure ratio4.35
Max exhaust temperature780 °C
Idle RPM18,080 rpm
Idle thrust5.0 kgf
Idle SFC4.77 kg/(kgf·h)
Idle fuel flow397.5 g/min
Start methodElectric starter / fuel start
Start time< 50 s
Max start altitude4,500 m
Max operating altitude10,000 m
Max flight Mach number0.9
Accel / decel time< 6 s / < 8 s
Diameter × length215 × 562 mm
Total life / first overhaul (TBO)60 h / 25 h
FuelAviation kerosene / diesel blended with 5% turbine oil
Lubricating oilMobil Jet Oil II
Design pointH = 0 km, Ma = 0, ambient 15 °C, 101,325 Pa
HK-1200A
Heavy class · 120 kgf thrust · Ø248 × 588 mm · 17.9 kg
Max thrust120 kgf
Max RPM50,500 rpm
Engine / system weight17.9 kg / 1.2 kg
Thrust-to-weight (core/total)7.2 / 6.7
SFC at max1.35 kg/(kgf·h)
Fuel flow at max2,700 g/min
Inlet airflow1.875 kg/s
Pressure ratio4.05
Max exhaust temperature780 °C
Idle RPM18,000 rpm
Idle thrust7.5 kgf
Idle SFC4.0 kg/(kgf·h)
Idle fuel flow525 g/min
Start methodElectric starter / fuel start
Start time< 60 s
Max start altitude4,500 m
Max operating altitude10,000 m
Max flight Mach number0.9
Accel / decel time< 6 s / < 8 s
Diameter × length248 × 588 mm
Total life / first overhaul (TBO)60 h / 25 h
FuelAviation kerosene / diesel blended with 5% turbine oil
Lubricating oilMobil Jet Oil II
Design pointH = 0 km, Ma = 0, ambient 15 °C, 101,325 Pa
HK-1600A
Heavy class · 160 kgf thrust · Ø264 × 614 mm · 21.0 kg
Max thrust160 kgf
Max RPM46,000 rpm
Engine / system weight21 kg / 1.5 kg
Thrust-to-weight (core/total)8.20 / 7.62
SFC at max1.33 kg/(kgf·h)
Fuel flow at max3,546 g/min
Inlet airflow2.5 kg/s
Pressure ratio4.1
Max exhaust temperature780 °C
Idle RPM15,000 rpm
Idle thrust8.5 kgf
Idle SFC4.00 kg/(kgf·h)
Idle fuel flow570 g/min
Start methodElectric starter / fuel start
Start time< 60 s
Max start altitude4,500 m
Max operating altitude12,000 m
Max flight Mach number0.95
Accel / decel time< 6 s / < 8 s
Diameter × length264 × 614 mm
Total life / first overhaul (TBO)60 h / 25 h
FuelAviation kerosene / diesel blended with 5% turbine oil
Lubricating oilMobil Jet Oil II
Design pointH = 0 km, Ma = 0, ambient 15 °C, 101,325 Pa
HK-2000A
Heavy class · 200 kgf thrust · Ø295 × 690 mm · 29.0 kg
Max thrust200 kgf
Max RPM41,500 rpm
Engine / system weight29.00 kg / 1.8 kg
Thrust-to-weight (core/total)7.35 / 6.90
SFC at max1.30 kg/(kgf·h)
Fuel flow at max4,333.3 g/min
Inlet airflow3.13 kg/s
Pressure ratio4.6
Max exhaust temperature780 °C
Idle RPM13,280 rpm
Idle thrust10.30 kgf
Idle SFC4.36 kg/(kgf·h)
Idle fuel flow748.5 g/min
Start methodElectric starter / fuel start
Start time< 80 s
Max start altitude4,500 m
Max operating altitude16,000 m
Max flight Mach number0.95
Accel / decel time< 6 s / < 8 s
Diameter × length295 × 690 mm
Total life / first overhaul (TBO)60 h / 25 h
FuelAviation kerosene / diesel blended with 5% turbine oil
Lubricating oilMobil Jet Oil II
Design pointH = 0 km, Ma = 0, ambient 15 °C, 101,325 Pa
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