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Aerodynamic Calculation And Key Experiment Technology Investigation Of A Hovering Insect-like Micro Air Vehicle

Posted on:2016-02-03Degree:MasterType:Thesis
Country:ChinaCandidate:T WangFull Text:PDF
GTID:2272330470469609Subject:Measuring and Testing Technology and Instruments
Abstract/Summary:PDF Full Text Request
With the developing demand in civil and military, the study about insert-like micro air vehicle has caused the research boom internationally. At present,due to the lack of the mature aerodynamic system and the flight control experiment of insect model, the research content of this paper is presented. This paper includes two parts. In the first part, the forces and moments of the 3D flapping wing in hovering condition were calculated and analyzed. And in the second part, the experiment platform used for controlling the attitude of insect model was designed.In this paper, the 3D flapping wing with different kinematic parameters was simulated by the commercial CFD(Computational Fluid Dynamic) software Fluent.The result showed that the lift force of flapping wing was influenced by the flapping motion mainly. In the hovering condition,when angle of attack was symmetrical, the lift force Fl and the turning moment Mz influenced by the change of the angle of attack. The lift force Fl enhanced when the angle of attack increasing, and reached the peak when the angle of attack increased to about 35°to 55°. And then it decreased with the increasing of incidence angle. When flapping amplitude Φ increasing, the lift force increased simultaneously. Moreover, the lift force also increased with the frequency increasing. And following, the aerodynamic force of flapping wing in flight was also showed.The experiment platform based on a water channel, the attitude parameters real-time acquisition of insect model could be achieved in this platform. With these attitude parameters, the next attitude parameter and target velocity of insect model could be calculated. Through these work, the attitude controlling of insect model could be realized. The force data acquisition and the data communication between PC and master controller were achieved based on Labview. As shown in this paper,the force acquisition was based on UDP protocol, and the data communication via a serial port. The results show that these programs are useful to the data acquisition and communication, the function of communication between PC and master controller has been achieved.
Keywords/Search Tags:micro air vehicle, numerical simulation, flapping wing, Labview platform
PDF Full Text Request
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