Two-wing differential flapping micro flapping rotor aircraft

Abstract

The invention discloses a two-wing differential flapping micro flapping rotor aircraft, and relates to the field of micro aircrafts. The two-wing differential flapping micro flapping rotor aircraft comprises wings, a transmission mechanism, a power device and a base. The power device and the transmission mechanism are fixed on the base. The two wings are fixed to the two ends of the transmission mechanism correspondingly. During working, a micro motor in the power device supplies power to drive an inner rod of the transmission mechanism to ascend and descend, so that two wing connecting rods simultaneously move in the opposite directions, the pair of wings arranged symmetrically is driven to move downward and upward alternately, and differential flapping is achieved. According to the two-wing differential flapping micro flapping rotor aircraft, it is ensured that the average lift force in the flapping process with the same frequency of the wings is unchanged, wing transient lift force fluctuations are reduced significantly, the lift force is more even within the whole flapping cycle, requirements for output power of the motor are reduced effectively, and the energy utilizing efficiency is improved significantly.

Description

technical field [0001] The invention relates to the field of micro-aircraft, in particular to a micro-flapping-rotor aircraft with differential flapping of two wings. Background technique [0002] Since the 1990s, with the continuous improvement of traditional aircraft design technology, people have been exploring the mechanism of animal flight and swimming more and more deeply, and the rapid development of microelectronics technology has led to the rapid development of the field of micro air vehicle design. , has broad application prospects in national security and national economic construction, and is applied to tasks such as reconnaissance, communication, exploration and assistance in rescue under complex environmental conditions. [0003] The patent application whose publication number is CN 101492093: "Design Method of Flapping Rotor and Miniature Flapping Rotor Aircraft Designed by Using the Method" discloses a miniature flapping rotor aircraft. supply. MAVs are lig...

AI Technical Summary

Problems solved by technology

[0005] The present invention aims at flapping both wings in the same direction for the existing miniature flapping rotor aircraft, resulting in extremely large wing lift and transient energy consumption during down-shooting, and very little lift and transient energy consumption during up-shooting. Due to the huge difference in transient energy consumption, large fluctuations in system lift, and low overall energy utilization, a miniature flapping rotor aircraft with differential flapping wings was proposed.

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