Flapping wing micro air vehicle based on triangular structure

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

Inactive Publication Date: 2014-10-15
SHANGHAI JIAOTONG 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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  • Flapping wing 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 drawings and embodiments, but the following content is not intended to limit the protection scope of the present invention.

[0019] Such as figure 1 As shown, the present 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 plate 6, a large Gear 7, pinion 8 and wings 9, wherein: the frame 1 provides an overall frame for the whole 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 plate 6 cooperates with the large gear 7 to convert the continuous rotation output by the motor into reciprocating rotation; the second parallel shaft 4 amplifies the amplitude of the reciprocating rotation of the f...

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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 type of aircraft with a scale no larger than 6 inches (15cm) in any direction, micro-aircraft has a very wide range of uses in military, industrial and civilian fields-it can be used to complete many 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 gradually come out. [0003] These micro-aircrafts are of a great variety, and the flight mechanisms they utilize mainly include fixed-wing flight, rotary-wing flight and flapping-wing flight. Although there are quite a few micro-aircraft using the first two flight mechanisms, it should be noted that these types of micro-aircraft have inherent limitations. For example, fixed-wing micro-aircrafts face the problem ...

Claims

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Application Information

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Patent Type & Authority Patents(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 JIAOTONG UNIV
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