1. Dual CPU redundant structure
2. Provide Micro SD, USB memory interface
3. RS232/422, AD/DA.PWM
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
9. PC104 stack structure with ATAG & UART test interfaces

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 devices 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: 595, no condensation
Shock vibration: 5g

General Specifications
External dimensions (LH) (without ear): 12515088 mm
Case material: aviation aluminum alloy

Typical Applications
Construction of automatic testing system
Laboratory automation, research and design verification