基于雙DSC的無人機飛控計算機核心系統(tǒng)的設計與實現(xiàn).pdf

1、南京航空航天大學碩士學位論文基于雙DSC的無人機飛控計算機核心系統(tǒng)的設計與實現(xiàn)姓名：高振申請學位級別：碩士專業(yè)：檢測技術與自動化裝置指導教師：羅秋鳳2011-01基于雙 DSC 的無人機飛控計算機核心系統(tǒng)的設計與實現(xiàn) iiABSTRACT As the core of the UAV flight control system, the fight control computer is the key issue in UAV dev

2、elopment. Presently, research in this area has not been so perfect,especially some core boards are still dependent on imports.This paper designed a UAV flight control computer core system based on dual TMS320F28335 arc

3、hitecture with full independent intellectual property rights, and explored a new implementation for the hardware design of the UAV flight control computer. Firstly, the paper analyzed the interfaces between flight contro

4、l computer and airborne equipments by studying the basic frame of the UAV flight control system, and then defined the hardware framework of flight control computer as core system and peripheral interfaces. The core syste

5、m is mainly discussed in this paper.According to the principles of small size,highly cost effective and commonality,the design requirements and design proposal are given in detail. Secondly, the core system is endowed wi

6、th powerful computing capabilities by the application of dual TMS320F28335 architecture.Through the rationally planning of the dual core on-chip peripheral resources, the core system has provided the UAV fight control sy

7、stem with most of the interface resources, including 32 analog input (A/D) channels for analog signal acquisition; 12 PWM output channels and 6 CAP channels for mini digital servo feed-back control; 40 configured GPIO ch

8、annels for airborne discrete devices; 4 UART for airborne serial devices; 8 analog output (D/A) channels and 8 UARTs are added in order to drive the traditional analog servo and interface as much as 12 serial devices. Th

9、irdly, the framework is more modifiable via the independent board function partition and the stack symbol integrated circuit board improves the space utilization and meets the requirements of miniaturization. Finally, by

10、 the debugging of single core board, the design scheme of all function modules are fully tested, and then the dual core Prototype is finished. The system integration tests have guaranteed the performance quality of the m

11、uti-interfaces; through applying this core system as the hardware platform of Micro UAV attitude determination system, which has finished the test of the practical engineering project and proved that this core system for