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A variable shape fixed-wing micro air vehicle

A micro-aircraft, fixed-wing technology, applied in the direction of aircraft, micro-aircraft, aircraft parts, etc., can solve the problems of difficult to guarantee lift-drag ratio and stability, low Reynolds number, low speed, etc., to improve the stall angle of attack and stability. , the effect of high aerodynamic efficiency and fast flight speed

Active Publication Date: 2022-03-04
BEIJING INSTITUTE OF TECHNOLOGYGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At the same time, due to the small size and low speed of the MAV, its Reynolds number is very low during flight, and it is difficult to guarantee the lift-to-drag ratio and stability, and it is extremely susceptible to interference caused by changes in incoming flow conditions.

Method used

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  • A variable shape fixed-wing micro air vehicle
  • A variable shape fixed-wing micro air vehicle
  • A variable shape fixed-wing micro air vehicle

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Embodiment Construction

[0024] The present invention will be described in detail below with reference to the accompanying drawings and examples.

[0025] as attached figure 1 As shown, the present invention provides a variable-profile fixed-wing micro-aircraft, including rigid main body 1, forward flying power unit 2, hovering power unit 3, control rudder surface, flexible trailing edge 6 and skin 7 and other parts.

[0026] Wherein, the airfoil section of the rigid main body 1 is a low-speed airfoil with a high lift-to-drag ratio, and its plane shape is a reverse Zimmerman wing with a medium aspect ratio. The wingspan is 265 mm, the total length (excluding the front propeller) is 220 mm, and the total thickness ( folded state) is 21mm. The rigid main body 1 is provided with ducts running through the upper and lower surfaces, and the hovering power device 3 is installed in the ducts.

[0027] The forward flight power unit 2 is composed of a two-blade propeller arranged on the leading edge of the ma...

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Abstract

The invention discloses a variable-shape fixed-wing micro-aircraft, which belongs to the technical field of micro-aircraft. Including rigid main body, forward flight power unit, hovering power unit, skin and control rudder surface; the rigid main body adopts wing-body fusion structure, and forward flight power unit is installed on the leading edge of the rigid main body; the control rudder surface is installed behind the rigid main body The control rudder surface controls the attitude of the aircraft through angle changes. The rigid body is provided with ducts that run through the upper and lower surfaces. The hovering power unit is installed in the ducts. In the flying state, the skin closes the duct opening so that the rigid body maintains a complete aerodynamic shape; in the hovering state, the skin is retracted into the rigid body by the corresponding mechanism or thrown away to completely open the duct opening. The invention has the functions of hovering and vertical take-off and landing under the condition of high flight speed, and simultaneously has high reliability and aerodynamic efficiency.

Description

technical field [0001] The invention belongs to the technical field of micro-aircraft, and in particular relates to a micro-aircraft with variable shape and fixed-wing layout. Background technique [0002] Micro Air Vehicles (MAVs for short) is a new type of aircraft with small size and light weight. Due to its advantages of portability, low cost, and good concealment, it has quickly become a very popular research field. Micro air vehicles can be used in a wide range of scenarios: a single military use can be used for target detection, signal interference, etc., and a large number of use can realize distributed long-range strikes and large-scale group operations; civilian use can be used for disaster search and rescue, communication relay, resource exploration, etc. [0003] There are currently three main categories of MAVs in terms of aerodynamic layout, namely micro fixed-wing aircraft, micro flapping-wing aircraft, and micro-rotor aircraft. Among these three layouts, th...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C1/00B64C9/00B64D27/02B64C1/12B64C39/02
CPCB64C1/00B64C9/00B64D27/02B64C1/12B64C39/028B64C2001/0045
Inventor 雷娟棉郭牧天牛健平解文洋
Owner BEIJING INSTITUTE OF TECHNOLOGYGY