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Flight control computer, the core of the UAV flight control system, is the solution device of control system to realize the control law calculation function of flight control system and output control command to servo system. Flight control computer is also the management part of all the system, which is responsible for redundancy management calculation, logical judgment, working mode conversion, and achieves the declaration of system state, fault alarm and BIT function of the whole flight control system. It provides signal interfaces from other parts of the system and from the system to the on-board cross-link equipment on the machine and processes the signals.
We can customize redundancy flight control computers according to customers demands.
● Achieving redundancy management and self-test function through hardware and software to meet the reliability requirements of flight computer and flight control system reliable.
● According to the information of command sensor and flight movement sensor, it performs control law calculation and the result is input to servo system to control motion of rudder actuator.
● Self-test capability to meet the system testability requirements and providing test circuits for other parts
● Providing power supply for some other external parts

Distributed Redundancy Flight Control Computer

1.CPU is powered by NXP POWERPC P2020
2.DDR3 has a capacity of 1GB, ROM 1GB, NVSRAM 256KB and FLAHS 16Gb*8bit
3.CCDL function is supported, S400B communication mode defined by IEEE1394B protocol is adopted, including 1 sending bus and 3 receiving buses, each of which supports the rate of 400Mbps
4.Single node MIL-1394B system bus (Nodes are optional, supports up to three nodes), conform to AS5643 protocol
5.16-channel discrete input interface, 16-channel discrete output interface (discrete type configurable)
6.8-channel analog input/output interface
7.1-channel 100M/1000M Ethernet
8.4-channel RS422 interface, 2-channel RS232 interface
9.3-channel synchronous input and 1-channel synchronous output interface
10.Support VxWorks and other dedicated flight control real-time operating systems

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Quad Redundant Flight Control Computer

● Quad redundancy CPU structure
● Bus function module realized by external interface integrated board
● Discrete function module realized by using discrete simulation board
● Analog function module realized by analog emulator
● Power module realized by power board
● The external power supply of the chassis powered by AC 220V
● Centralized structure design
● LEB Bus
● Suitable for simulation system

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Single Redundant Flight Control Computer

● CPU is powered by NXP POWERPC P1010, with a maximum main frequency of 800MHz
● DDR3 has a capacity of 1GB, ROM 1GB, NVSRAM 256KB and FLAHS 16Gb*8bit
● 5-channel RS422 interface, 2-channel RS232 interface
● 16-channel discrete input interface, 16-channel discrete output interface (discrete type configurable)
● 8-channel analog input interface, 8-channel analog output interface
● 5-channel PWM output interface
● 1 channel 100M/1000M Ethernet
● 1 channel CAN communication interface (reserved)
● 1 channel synchronous input and 1 channel synchronous output interface (reserved)
● 1 channel CCDL input 1 channel CCDL output (reserved)
● A set of DIF interfaces
● Flight parameter record
● Support for BIT testing
● Support VxWorks real-time operating system
● Suitable for small and medium sized drones

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Double Redundant Flight Control Computer

1.Dual redundancy CPU synchronization, monitoring and channel switching
2.Cross-channel data transfer
3.RS485, RS422, RS232 communication
4.Self-test, external power supply interface
5.Power supply design meets GJB181A-2003 Aircraft Power Supply Characteristics
6.Monitor all external input and internal secondary supply voltages
7.Development/debugging, ground maintenance and testing functions
8. Suitable for medium and large drones and helicopters

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Triplex Redundant Flight Control Computer

● Triplex redundancy CPU structure
● Bus function module realized by external interface integrated board
● Discrete function module realized by discrete emulator
● Analog function module realized by analog simulation card
● Power module realized by power board
● External power supply of the chassis is powered by AC 220V
● Centralized architecture design
● Suitable for simulation system

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