U23-P Turbojet 23kg Aircraft Engine
1 Idle speed RPM 31000
2 Idle thrust kg 0.85
3 Idle fuel consumption ml/min 100
4 Maximum speed RPM 117000
5 Thrust at maximum speed kg 23
6 Fuel consumption at maximum speed ml/min 780
7 Exhaust temperature ℃550-750
8 Compression ratio 3.7
9 Maximum speed SFC kg/daN.h 1.72
10 Engine weight kg 2.05
11 Diameter mm 117
12 Length mm 230
13 Maximum start altitude m 4600 (actual measurement)
14 Maximum operating altitude m 10000
15 Available fuel Mixed with 3%-5% Pegasus 2 or Mobil turbine oil
Aviation kerosene or diesel
16 Supply voltage V 3SLi-Po battery/12V
17 Working current A ＜2A
18 Power generation current A ＜5A
(All data are tested under STP±3% environment: standard temperature 15℃, pressure 1013mbar)
Product features:
This engine system is fully built-in: fuel pump, solenoid valve, engine controller, various sensors are built-in in the front casing of the engine, and there is only fuel input port, power input port, charging output port, and communication signal interface on the outside. The system is simple and convenient to install. The weight of the entire engine system is 2000 grams, the thrust-to-weight ratio is greater than 11, and the signal interface has remote control PWM input, ground service interface, CAN bus, power input, and power generation output.
l The power generation function can charge the engine battery and receiver battery during flight. It basically does not need to be charged after 10 take-offs and landings.
l This Turbine engine is a new design with high aerodynamic efficiency, wide working envelope, small power attenuation in hot weather, fast acceleration (4 seconds from idle to maximum speed),
Product storage temperature -20℃-+50℃, working and starting temperature -20℃-+40℃. Maintenance cycle, 20 hours.
U42-P Turbojet 42 kg Aircraft Engine
1 Idle speed RPM 35000
2 Idle thrust kg 3.5
3 Idle fuel consumption ml/min 240
4 Maximum speed RPM 98000
5 Maximum speed thrust kg 42
6 Maximum speed fuel consumption ml/min 1300
7 Exhaust temperature ℃ 550-850
8 Compression ratio 4
9 Maximum speed SFC kg/daN.h 1.65
10 Engine weight kg 3.95
11 Diameter mm 148
12 Length mm 390
13 Maximum starting altitude m 4000
14 Maximum operating altitude m 10000
15 Available fuels Aviation kerosene or diesel mixed with 3%-5% Pegasus 2 or Mobil turbine oil
16 Supply voltage V 12V
17 Starting current A
＜20A
18 Working current A ＜5A
(All data are tested under STP±3% environment: standard temperature 15℃, pressure 1013mbar)
Product Description:
The fuel pump, solenoid valve, engine controller and various sensors of this engine are built-in the front casing of the engine. There isonly fuel input port, power input port, communication signal interface and fuel tank boost interface on the outside. The system installation and maintenance are simple and convenient, and there is no need to consider the installation position of accessories.
The weight of the whole engine system is less than 4000 grams, the thrust-to-weight ratio is greater than 11, and the launch overload is ≥
6G. The control interface has PWM and 422 bus, 2 optional.
The telemetry data can provide throttle ratio 0%-100%, engine speed rpm, exhaust temperature ℃, oil pump speed rpm, system voltage V, system current A, engine status, fault code and other information.
The product storage temperature is -40℃-+70℃, and the working and starting temperature is -30℃-+50℃.
The working life is 7 years or 20 hours.
U55-P Turbojet 55 kg Aircraft Engine
1 Idle speed RPM 26000
2 Idle thrust kg 3.0
3 Idle fuel consumption g / min 230
4 Maximum speed RPM 83000
5 Thrust at maximum speed kg 56
6 Fuel consumption at maximum speed g / min 1300
7 Exhaust temperature ℃ 550-850
8 Compression ratio 4
9 Maximum speed SFC kg/daN.h 1.4
10 Engine weight kg 4.9
11 Diameter mm 175
12 Length mm 456
13 Maximum starting altitude m 4000
14 Maximum operating altitude m 10000
15 Available fuel Mixed with 3%-5% Pegasus 2 or Mobil turbine oil
Aviation kerosene or diesel
16 Supply voltage V 12V
17 Starting current A ＜20A
18 Working current A ＜5A
(All data are tested under STP±3% environment: temperature 15℃, pressure 1013mbar)
Product Description:
The fuel pump, solenoid valve, engine controller and various sensors of this engine are built-in
the front casing of the engine. There is only fuel input port, power input port, communication signal interface and fuel tank boost interface on the outside. The system installation and maintenance are simple and convenient, and there is no need to consider the installation position of accessories.
The weight of the whole engine system is less than 5500 grams, the thrust-to-weight ratio is greater than 11, and the launch overload is ≥
6G. The control interface has PWM throttle control and TTL bus returns engine telemetry data.
The telemetry data can provide information such as throttle ratio 0%-100%, engine speed rpm, exhaust temperature ℃, oil pump speed rpm, system voltage V, system current A, engine status, fault code, etc.
The product storage temperature is -40℃-+70℃, and the working and starting temperature is -30℃-+50℃.
Working life, 20 hours.
Packing size: length 820 width 350 height 310, packaging weight: 7.2 k
U90-P Turbojet 91 kg Aircraft Engine
1 Idle speed RPM 20000
2 Idle thrust kg 4.0
3 Idle fuel consumption g / min 450
4 Maximum speed RPM 63000
5 Thrust at maximum speed kg 91
6 Fuel consumption at maximum speed g / min 2000
7 Exhaust temperature ℃550-850
8 Compression ratio 4
9 Maximum speed SFC kg/daN.h 1.35
10 Engine total system weight kg 9.3
11 Diameter mm 205
12 Length mm 550
13 Maximum starting altitude m 4000
14 Maximum operating altitude m 10000
15 Available fuel Jet fuel or diesel mixed with 3%-5% Pegasus 2 or Mobil turbine oil
16 Supply voltage V 12V
17 Starting current A ＜30A
18 Working current A ＜6A
(All data are tested under STP±3% environment: standard temperature 15℃, pressure 1013mbar)
Product Description:
The fuel pump, solenoid valve, engine controller and various sensors of this engine are built-in
the front casing of the engine. There are only fuel input port, power input port, communication signal interface and fuel tank boost interface on the outside. The system installation and maintenance are simple and convenient, and there is no need to consider the installation position of accessories.
The weight of the whole engine system is less than 9.5kg, the thrust-to-weight ratio is greater than 9, and the launch overload is ≥
6G. The control interface has PWM throttle control and TTL bus to return engine telemetry data.
The telemetry data can provide information such as throttle ratio 0%-100%, engine speed rpm, exhaust temperature ℃, oil pump speed rpm, system voltage V, system current A, engine status, fault code, etc.
The product storage temperature is -40℃-+70℃, and the working and starting temperature is -30℃-+50℃.
Working life, 20 hour