Stability Control And Design Of Four-wing Aircraft

For present society four rotorhelicopter has multiple advantages because of the degree of social concern and use levels are increasing,such as the production cost is relatively low,while the rapid development of science and technology content factors.Although for now,the aircraft function has been more and more rich,but the research in the field of aircraft,its stability or attitude the key research contents,but also determines the quality of aircraft.The author of the study is based on the existing theory,analyzes the stability of aircraft,and its optimal,and then through the experimental test,the author carried out the work including:Filter out the noise filtering algorithm: complementary attitude angle is in accordance with the strapdown inertial navigation system for aircraft attitude mechanism,attitude,attitude matrix and related angle,lay the foundation.The attitude calculation through the complementary filter algorithm can remove the sensor output numerical noise,to achieve the purpose of noise reduction,to ensure the accuracy of the numerical output is higher,but also to ensure the attitude calculation more accurately.The fuzzy control algorithm of attitude angle: the original PID control algorithm,in the calculation of vehicle attitude angle stability,there are many deficiencies,the crash probability is relatively large,so the author is through fuzzy PID control(fuzzy PID)method is actually a simulation of PID,fuzzy control,and then analyze the results,you can through the fuzzy PID control algorithm to calculate the stability of waves,and the results compared with the traditional PID control algorithm the calculation results more accurate,more reliable.Aircraft test: the author constructs the experimental platform,the test based on this test,the above 2 algorithms control effect on the attitude stability.The experimental platform is introduced and related to the hardware,and the application software,which provide the data acquisition sensor device,driving flight control system,the flow chart of control the flight.