Design And Implementation Of Automatic Flight Control Syetem On Model Helicopter

Since unmanned helicopter has much advantage compared to unmanned fixed-wing aircraft, aswell as its huge application prospect in military and civil use, this thesis aims to discuss the designand implementation of the automatic flight control system of a model helicopter. The details are asfollows:Firstly, the hardware overall design scheme and the device selection were finished. According tothe analysis of system resource distribution, real time performance, working stability and debuggingperformance, the “DSP+dual-ported RAM+MCU” dual-core processor module of the flight controlcircuit was designed. According to the analysis of power supply of flight control system, the powersupply module design and detail circuit design were studied. According to the characteristics ofinterface communication of the information acquisition module, executive parts and datacommunication module, detail interface circuits were designed. In order to enhance the stability offlight control system, the EMC and anti-interference were designed in this paper. At last, theschematic circuits and the layout of a PCB were finished. And the hardware platform of the flightcontrol system were established.Secondly, according to the performance requirements of flight control software, the on-chipresource of DSP and MCU, the driving scheme for peripheral and the low-level driver program weredesigned. The communication modules(dual-ported RAM, PWM capture, Serial expansion, radio),PWM output module, information acquisition modules(IMU,GPS, A/D conversion and so on), PIDcontrol module were designed. The ground station was finished. At last, according to different flightmissions, above software modules were integrated and the function of the flight control software wascompleted.Finally, the control software was downloaded into the flight control circuit and the test andexperiment of each functional modules were successfully finished. And according to specific flightmission, the test and experiment of the integral flight control system were studied and some specificflight functions were achieved, which verified the validity and feasibility of the whole system.