Mechanism and experiments of asymmetrical pitch system for MAV
In view of problem for miniaturizing Micro Air Vehicles (MAV), a novel asymmetrical pitch system faced to rotary wing MAV is introduced. The pitch mechanism and control characteristics are studied and analyzed. Because the deformation of elasticity link is key to generate the blade pitch, it is analyzed and calculated by elasticity finite element method. And the results illustrate the linear relationship between blade pitch angles and the output torque of the motor. Based on control system of asymmetrical pitch, mechanism experiments based on strain gauge are done, and the factors that affect the deformation of the elastic linkage is analyzed. Results indicate that mechanism of asymmetrical pitch is effective.
A control system for experimental platform of micro aerial vehicle based on C8051F020
A new measuring way different from the traditional deducting method for the angle of blade pitch was proposed based on high-speed camera and image processing. According to the experiment requirement,an experimental platform mainly based on the device of Micro Aerial Vehicle(MAV) and a new control system found on C8051F020 SCM were designed.In the platform,C8051F020 SCM was the MCU;the phase information of the propeller's main-shaft was tested with the micro position sensor and the PCA capture function of C8051F020 SCM.The four phase information of a propeller's main-shaft was gained by collecting the output signal of a position sensor;the motor speed was controlled by the output signal of PWM generated by C8051F020 SCM for controlling the motor speed up;a high-speed camera was touched off by the interrupt signal from the PCA capture in order to realize the synchronization between the speeding up of the motor and the taking pictures of the camera.This control system has compacted configuration and high reliability.Finally,using this system to control the MAV for simulating the forward flying,the electronic collector curve of MAV was obtained.It is proved that the proposed method and the experiment platform based this method can be used to measure the blade pitch and have met the design requirement completely.
The micro aerial vehicle (MAV) with flapping wings
The research of micro aerial vehicles (MAVs) is a new field of low-Reynolds-number flow, which attracts much attention in the advanced aeronautical area. The flapping wing, proved by many natural flyers, is the most appropriate way of flying objects which sizes are less than 6 inches. However, there is still plenty of room for studying on the unsteady aerodynamic characteristics of flapping wings. The flapping wing, which is light weighted and high strengthened, is originally composed of the titanium-alloy frame and the parylene skin. Such an integration of fabrication needs the help of MEMS processing. Additionally, the flapping test after the wing fabrication and the corresponding signal analysis from the smart wing skin concluded this project and set the bases for the wind-tunnel verification/correction in the very near future.