ZB 8DN02 Triplex Redundant Flight Control Computer

Features as follows

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
 

Product Description

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.

Performance Parameters

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

Working Environment

Temperature range……….. -10℃～65℃

Relative humidity……….. 5﹪～95﹪, nocondensation

Shock vibration……….. 5g

General Specifications

External dimensions (L×W×H) (without ear)……….. 600×320×350 mm

Chassis material……….. Aviation aluminum alloy

Typical Applications

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.

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

Selection Guide for Flight Control Computer