ZB8DN01 Double Redundant Flight Control Computer

Product Description

The device is a flight control computer platform applied to UAV with laminated structure of four layers inside, including functions as data processing, data acquisition, communication, long-distance data transmission, direction inertial navigation and so on. It adopts PC104 stack, peripheral module construction realized by external extend device's local bus of embedded processer. This device contains one port of RS232 and one port of RS422, debug interface for JTAG and UART, built-in inertial navigation, barometer, GPS module and a base with JPMZ-0.5 shock absorber. The whole machine frame structure is designed by aviation aluminum alloy-alloy so it has obvious characters of firm construction and light body. It is a flight control computer which integrates aviation control with task to meet the autonomous flight control and mission of the multi-rotatable wings/fixed-wings airplane and helicopter.

Working Environment

Temperature range ……………… -10℃～65℃

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

Shock vibration ……………… 5g

General Specifications

External dimensions (L×W×H) (without ear) ……………… 125×150×88 mm

Case material ……………… aviation aluminum alloy

Typical Applications

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