Shenzhen Nuobashi Trading Co.,Ltd

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

Product Description

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.

Performance Parameters

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

Working Environment

Temperature range ........... -10℃～65℃

Relative humidity ........... 5﹪～95﹪, no condensation

Shock vibration ........... 5g

General Specifications

External dimensions (L×W×H) (without ear) ........... 700×320×350 mm

Case material ........... Aviation aluminum alloy

Typical Applications

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.

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