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The power distribution unit has a critical task to ensure that the 115 VAC 400Hz power in the aircraft. 115VAC PDU has three phase inputs. There are v

The power distribution unit has a critical task to ensure that the 220VAC, 50 Hz power in the aircraft. 220VAC PDU has one phase inputs. There are vol

An Electronic Circuit Breaker Unit/Power Distribution Unit has power inputs from different sources and power outputs to feed the loads. The 28VDC Elec

Intellectual Property (IP) Core is a logic or data block used to build a Field Programmable Gate Array (FPGA) or Application-Specific Integrated Circu

Maximum takeoff(S/L static;ISA) Shaft power, hp ................................ 11, 400........................12, 200 Specific fuel consumption, kg/

AI-450-2 Takeoff(S/L static;ISA) Power, hp ........................ 630...800 Specific fuel consumption, kg/h/hp ....... 0.270...260 AI-450C-2(CP-2) T

TV3-117VMA-SBM1V series 5 Maximum emergency (S/L static;ISA) Power, hp ............... . ...... ... .3, 200 Takeoff (S/L static;ISA)

AI-322-30AI-322-40 Takeoff (S/L static;ISA) Thrust, kgf ...................3, 000............3, 755 Specific fuel consumption, kg/h/kgf ..... 0.7 ....

Check at every level: from production to testing one-stop service material selectionmanufacturingtransportationexportafter-sales ATTENTION: 1. You mus

Check at every level: from production to testing one-stop service material selectionmanufacturingtransportationexportafter-sales ATTENTION: 1. You mus

Check at every level: from production to testing one-stop service material selectionmanufacturingtransportationexportafter-sales ATTENTION: 1. You mus

Takeoff (S/L static;ISA) Thrust, kgf ..........................2, 500 Specific fuel consumption, kg/h/kg ..................0.64 Check at every level:

The 1553 test system is used to test systems using the MIL-STD-1553 communication protocol. The test system consists of a test card and a test program

Cockpit Dimmer Unit provides control of the integral lighting of Overhead, Instrument and Pedestal Panels located in the cockpit. Cockpit Dimmer Unit

The CIU analyzes the data from the peripherals and provides the data to be transmitted to peripherals to be transmitted in an appropriate format. With

Flight Control System is capable of controlling flight control software, peripheral controls, power distribution management and data recording, especi

The Ground Communication Interface (GCIU) is a flexible and reconfigurable system that, although they have the same hardware components, may differ in

The unit is used to control the camera module in the UAV. It helps the pilot in the ground station to control the camera. The Hand Control Unit is a

The Interference Blanking Unit is developed in order to ensure compatibility between the different units in aircraft for operation in various location

Linear Servo Actuator Control System is used to precisely control the linear type servo actuators such as wing flaps, nose wheels, and tail flaps whil

MFCS is a flight control computer designed for use in unmanned aerial vehicles. MFCSs architecture has been designed in line with the principle of con

The PCDU has 3 three-phase inputs, 200VAC 400Hz, 115VAC 400Hz, and 115VAC 400Hz. There is one AC output at 400Hz. AC output voltage value is selectabl

The PEPCU has 3 three-phase inputs, 440VAC 400Hz, 440VAC 60Hz, and 115VAC 60Hz. There are four AC outputs in 440VAC, two at 400Hz and two at 60Hz. The

The Rugged Data Converter (RADC) is an avionics communication translator between devices that talks different communication protocols. The RADC suppor

Rugged Ethernet Switch is a device that manages 10 Ethernet ports and 3 RS-485 ports. It has 1 Ethernet interface for accessing and managing device in

An Electronic Circuit Breaker Unit/Power Distribution Unit has power inputs from different sources and power outputs to feed the loads. The 28VDC Elec

Servo motor driver is designed to be used in aircrafts. Servo motor control system is used to precisely control the wing flaps, nose wheel and tail fl

The Strain Gage Amplifier (SGA) is a device that amplifies the signals from the strain gage sensors of the equipment Aircraft. The SGA's task is t

The Stores Remote Interface Unit (SRIU) serves as the interface between the payloads on the aircraft and the flight control computer and power distrib

UFCP is the unit on a platform where the system information and warnings on the aircraft can be seen and detailed information about the mission can be

AI-20A series 1, 2, 3, 4, AI-20K series 5, Al-20M series 6NBS Aircraft Engines Takeoff (S/L static;ISA).. Output shaft power, ehp ..................

AI-20D series 4, 5, 5E NBS Aircraft Engines Takeoff(S/L static;ISA) Output shaft power. e............................5, 180...................5, 180 E

Al-25 Takeoff(S/L static;ISA) Thrust, kgf...............................1, 500 Specific fuel consumption, kg/h...

Takeoff (S/L static;ISA) Output shaft power eh................2, 550.............2, 820............2, 820 Equivalent specific fuel consumption, kg/h/e

Maximum power takeoff(S/L static;ISA) Thrust, kgf ............. ............ 1, 720 ..........1, 720................ 1, 850 ...........1, 830 Specific

Takeoff (S/L static;ISA), uninstalled Thrust, kg ........................6, 500 ..........6, 500 Specif...

Takeoff(S/L static;ISA), uninstalled Thrust, kgf ..........................23, 430 Specific fuel consumption, kg/h/kg ...................0.345...0.362

Takeoff(S/L static;ISA) Thrust, kgf ........................2, 200 Specific fuel consumption, kg/h/kgf ............. 0.595 Check at every level: from

Takeoff(S/L static;ISA), uninstalled Thrust kg ...................7, 500 ............ 7, 500..................6, 570.................7, 000 Specific f

Takeoff(S/L static;ISA) Output shaft power, ehp ........................2, 500 Equivalent specific fuel consumption, kg/h/e......................0.206