Minisize aircraft

A micro-aircraft, integrated technology, applied in the field of aircraft, can solve the problems of insufficient lift area, small rudder surface area, insufficient fuselage capacity, etc., and achieve the effect of reducing external dimensions, reducing induced resistance, and large volume and volume

Inactive Publication Date: 2007-06-20
TSINGHUA UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

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

Method used

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Embodiment Construction

[0032] The present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0033] Shown in conjunction with Fig. 2 (a) ~ Fig. 2 (d), micro air vehicle of the present invention comprises airframe 20, two elevons 31 and 32, two vertical empennages 41 and 42 and a ventral fin 50, and propeller 60.

[0034] In the present invention, the concept of wing-body fusion is adopted in the aerodynamic design of the aircraft. Compared with FIG. 1 , the aircraft in FIG. 2( a ) does not have the traditional slender wings and fuselage in appearance, but the wings and fuselage are integrally formed into a flat body 20 . The body 10 is an axisymmetric shape, which can be seen more clearly in FIG. The body 20 is divided into two parts, a left half body 21 and a right half body 22 . Although there is no difference between the traditional wing and the fuselage in the present invention, it can be seen from Fig. 2 (a) ~ Fig. 2 (...

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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...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C39/10
Inventor 周兆英王晓浩王劲东熊沈蜀朱荣宋宇宁魏强
Owner TSINGHUA UNIV
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