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| Place of Origin | China |
ProductDescription
ZY8DN04-T1Single Redundant Flight Control Computer is based on the analysis of similar products at home and abroad, and combined with the latest technical development trend as well as the latest needs of users. ZY8DN04-T1 takes NXP's high-performance low-power processor P1010 as its core, supports VxWorks real-time operating system, and provides rich peripheral interfaces, flight parameter recording and other flight control computer proprietary functions. ZY8DN04-T1 is suitable for airborne, shipborne and vehicle-mounted applications in harsh working environments.
WorkingEnvironment
Temperature range........... -10℃～65℃
Relative humidity............. 5﹪～95﹪, nocondensation
Shock vibration................ 5g
General Specification
Case material........... Aviation aluminum alloy
TypicalApplications
Construction of automatic testing 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 |
