- Zeobercom
- China
● 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
Product Description
The device adopts a centralized architecture of three redundancy similar redundancy architecture, with ARINC659 bus as the core, and each function board is connected to the bus in the form of resources, providing basic hardware platform for the development process of flight control system such as software development, testing, comprehensive verification and digital closed-loop.
Performance Parameters
Redundancy design……………..…Triplex CPU redundant structure
Bus type……………………………..ARINC659
Serial port………………………….. Provide 2-channel 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
Power supply……………………….DC 28V input
Working Environment
Temperature ........... -45℃ ~ +70℃
Relative humidity ........... 5﹪～95﹪, no condensation
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
● 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
Product Description
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 process the signals.
We can customize redundancy flight control computers according to customers' demands.
Selection Guide for Flight Control Computer
Model No. | Description | Bus Type | Working Temperature | Embedded Controller |
ZY 8DN04-T1 | Single Redundancy Flight Control Computer | CCDL | -45℃～+70℃ | √ |
ZY 8DN01 | Dual-Redundancy Flight Control Computer | PC104 | -45℃～+70℃ | √ |
ZY 8DN02 | Triplex Flight Control Computer | ARINC659 | -45℃～+70℃ | √ |
ZY 8DN03 | Quad Flight Control Computer | LBE | -45℃～+70℃ | √ |
ZY8DN05-TN | Distributed Redundancy Flight Control Computer | CCDL | -10℃～+55℃ | √ |
