ZY 8DN03 Quad Redundant Flight Control Computer

Vue d'ensemble

1 Quad redundancy CPU structure 2 Provide 2-channel of RS422 serial interface for each redundancy 3 Provide watchdog for each redundancy 4 Bus function module realized by external interface integrated board 5 Discrete function module realized by using discrete simulation board 6 Analog function module realized by analog emulator 7 Power module realized by power board 8 The external power supply of the chassis powered by AC 220V The device adopts a centralized architecture with quad similar redundancy structure. The channels are based on LBE serial bus and CCDL. Every functionboard is connected with 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 ........... Quad redundant CPU structure Bust ype ........... LBE serial bus and CCDL Serial port ........... Provide 2-way of RS422 serial port interfaces per redundancy Watchdog........... Every redundancy of flight control computer owns watchdog function Discrete........... 64-way discrete input and 64-way discrete output Analog quantity ........... 48-channel analog input and 48-channel analog output Power supply ........... DC 28V input Temperature range ........... -10℃～65℃ Relative humidity ........... 5﹪～95﹪, no condensation Shock vibration ........... 5g External dimensions (L W H) (without ear) ........... 700 320 350 mm Case material ........... Aviation aluminum alloy Construction of automatic test systems 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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