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
|
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 |
