Minisize aircraft

Abstract

This invention relates to a micro aviator, which comprises machine body, aviator wings, vertical fixing plane, helm plane and screw oar. The machine body and wings are formed into one flat machine with machine part symmetric with the middle axis line of the flying direction. The plane edge of machine is symmetric to the middle axis with two plane shapes of echelon. The helm plane comprises two symmetric located elevator side wings on the back of the machine part, wherein the elevator wing rotate along machine back edge. The aviator is integrated with traditional plane to form one machine to provide elevation force and task load space.

Description

technical field [0001] The invention relates to the field of aircraft, and more specifically, the invention relates to a micro air vehicle. Background technique [0002] Since the United States proposed the concept of "micro-aircraft" in 1992, micro-aircraft have attracted much attention because of their special purposes. Some countries have invested special funds to develop aircraft with a wingspan of less than one meter or even less than 150 mm, and have achieved considerable results. The characteristics of the micro-aircraft are: the size of the aircraft is 6-100 centimeters, the weight is 10-500 grams, the cruising speed is 30-70 kilometers per hour, the endurance time is 20-100 minutes, and the activity radius is 1-10 kilometers. The tasks performed by the aircraft include: air reconnaissance, target indication, communication relay, etc. MAVs have the following main characteristics: [0003] 1. Small size and low flying Reynolds number. The wingspan of the MAV is le...

AI Technical Summary

Problems solved by technology

[0006] 1) Insufficient lift area. If a conventional aircraft is scaled down, under strict size restrictions (wingspan less than 40 cm), the wing area in this way will be difficult to provide the necessary lift;

[0007] 2) Insufficient fuselage capacity. As mentioned above, conventional aircraft mostly adopt a slender fuselage design. When the size is reduced, its capacity decreases according to the cube of the length, making it difficult to install various types of control and mission equipment;

[0008] 3) Insufficient steering torque of the rudder surface

The stability of MAV itself is poor, and the requirements for maneuverability are higher than those of ordinary aircraft

The area of ​​the rudder surface in the traditional design is very small, which cannot generate enough steering torque and cannot meet the maneuverability requirements of the micro air vehicle

Furthermore, traditional aircraft use three sets of rudder surfaces: elevator, rudder, and aileron to control the pitch, yaw, and lateral three-axis movement of the aircraft, but this method is too complicated for micro air vehicles

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