ZB8DN01 Double Redundant Flight Control Computer

Overview

1 ZY 8DN01 Double Redundant Flight Control Computer 2 Provide Micro SD,USB memory interface 4 Embedded inertial navigation unit, differential GPS unit 5 Data link transmitting unit 6 Provide DC 24Voltage output and motor driving module 7 Aluminum alloy profile frame structure 8 The base with a JPMZ-0.5 shock absorber 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. Temperature range -10℃～65℃ Relative humidity 5﹪～95﹪, no condensation External dimensions (L W H) (without ear) 125 150 88 mm Case material aviation aluminum alloy 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.

Technical specification

Key specifications: 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.

Technical specifications

Compatible aircraft

This part fits the following platforms.

Fitment data pending — contact us with your aircraft model.

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