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Wing-flapping micro air vehicle based on triangular structure

A triangular structure and aircraft technology, which is applied in the field of micro-aircraft, can solve problems such as asymmetry in flapping motion, difficulty in size optimization control, and influence on the overall performance of micro-aircraft, achieving strong differentiability, easy assembly and maintenance, and convenient mass production Effect

Inactive Publication Date: 2012-12-12
SHANGHAI JIAO TONG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the flapping motion of the two wings of the micro-aircraft is not symmetrical, which makes the size optimization and subsequent control very difficult, and seriously affects the overall performance of the micro-aircraft

Method used

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  • Wing-flapping micro air vehicle based on triangular structure

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Embodiment Construction

[0018] The technical solutions of the present invention will be further explained below in conjunction with the accompanying drawings and embodiments, but the following contents are not intended to limit the protection scope of the present invention.

[0019] like figure 1 As shown, this embodiment provides a novel flapping-wing micro-aircraft based on a triangular structure, including a frame 1, a motor output shaft 2, a first parallel shaft 3, a second parallel shaft 4, a triangular structure 5, a baffle 6, a large Gear 7, pinion 8 and wings 9, wherein: the frame 1 provides an integral frame for the entire micro-aircraft; the motor output shaft 2 transmits the motion of the motor to other parts; the first parallel shaft 3 and the triangular structure 5, The baffle 6 cooperates with the large gear 7 to convert the continuous rotation output by the motor into reciprocating rotation; the second parallel shaft 4 cooperates with the large gear 7 and the pinion 8 to amplify the re...

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Abstract

The invention discloses a wing-flapping micro air vehicle (MAV) based on a triangular structure, which belongs to the field of MAV. The MAV comprises a frame, a parallel shaft structure, a movement output structure, a movement amplification structure, and a pair of wings. The parallel shaft structure and the movement output structure are directly arranged on the frame. With the parallel shaft structure, the movement output structure, the movement amplification structure and the pair of wings are connected into a whole. The movement output structure is connected to one end of the parallel shaft structure. The movement amplification structure is arranged in the middle of the parallel shaft structure. The pair of wings is arranged on the other end of the parallel shaft structure. The flapping of the two wings is completely symmetric, such that imbalance factors during flying are substantially eliminated. Therefore, the comprehensive performance of the MAV is improved, and the MAV is easy to control. Also, the MAV provided by the invention is advantaged in simple and reasonable structure, workability, and differentiability. The MAV is suitable for batch productions employing numerical control micro-machining.

Description

technical field [0001] The invention relates to the technical field of micro-aircraft, in particular to a novel flapping-wing micro-aircraft based on a triangular structure. Background technique [0002] As a class of aircraft with dimensions no larger than 6 inches (15cm) in any direction, MAVs have a very wide range of uses in military, industrial and civilian fields—it can be used to accomplish numerous tasks such as reconnaissance, surveillance, and search and rescue. Since the concept of micro-aircraft was proposed in 1992, various forms of micro-aircraft have been gradually introduced. [0003] There are many kinds of these micro-aircraft, and the flight mechanisms used by them mainly include fixed-wing flight, rotary-wing flight and flapping-wing flight. Although there are many MAVs utilizing the first two flight mechanisms, it should also be noted that these types of MAVs have inherent limitations. For example, fixed-wing MAVs face the problem of aerodynamic instab...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C33/00
Inventor 张卫平杨宋渊柯希俊谭小波陈文元刘武崔峰吴校生
Owner SHANGHAI JIAO TONG UNIV
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