ZB 8DN02 Triplex Redundant Flight Control Computer

Vue d'ensemble

1 Triplex redundancy CPU structure 2 Bus function module realized by external interface integrated board 3 Discrete function module realized by discrete emulator 4 Analog function module realized by analog simulation card 5 Power module realized by power board 6 External power supply of the chassis is powered by AC 220V 7 Centralized architecture design 8 ARINC659 serial back board bus as the core among channels The device adopts a centralized architecture with a triplex similar redundancy structure, and its interchannel takes ARINC659 serial backplane bus as the core. Every function board hooked up to the bus in the form of resources, the device provides basic hardware platform for the software development, testing,comprehensive verification and digital closed-loop of the development course of the flight control system. Redundancy design........... Triplex CPU redundant structure Bustype........... ARINC659 bus interface Serialport........... Provide 2-way of RS422 serial port interfaces per redundancy Watchdog...........Every redundancy of flight control computer owns watchdog function Discrete ...........64-channel discrete input and 64-channel discrete output Analog...........16-channel analog input and 16-channel analog output Powersupply........... DC 28V input Temperature range........... -10℃～65℃ Relative humidity........... 5﹪～95﹪, nocondensation Shock vibration........... 5g External dimensions (L W H) (without ear)........... 600 320 350 mm Chassis material........... Aviation aluminum alloy Construction of automatic test system Laboratory automation, research and design verification 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 controlcomputer 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.

Spécifications techniques

Caractéristiques principales : Model No. Description / Bus Type / Working Temperature / Portable / Embedded Controller / Max Output Power, ZY 8DN04-T1 Flight Control Computer / CCDL / -10℃～+65℃ / - / / -, ZY 8DN01 Flight Control Computer / CCDL / -10℃～+65℃ / - / / -, ZY 8DN02 Flight Control Computer / 659 / -10℃～+65℃ / - / / -, ZY 8DN03 Flight Control Computer / LBE / -10℃～+65℃ / - / / -, ZY12204 PC104 Framework Ruggedized Computer / PC104 / -40℃～+60℃ / / / 200W.

Spécifications techniques

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