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Method for designing UAV (unmanned aerial vehicle) provided with deflectable winglet

A design method, UAV technology, applied in computing, aircraft parts, special data processing applications, etc., can solve problems such as poor stall characteristics, low recovery dive height loss, inability to take into account high dive maneuverability, etc., to achieve enhanced The effect of heading stability, avoiding propeller slipstream, and improving pitch stability

Active Publication Date: 2019-05-28
NORTHWESTERN POLYTECHNICAL UNIV
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  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In order to avoid the deficiencies of the prior art, the present invention proposes a design method for an unmanned aerial vehicle with deflectable winglets, which solves the problem that most unmanned aerial vehicles cannot take into account both high dive maneuverability and low recovery dive altitude loss, and has problems with poor stall characteristics

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  • Method for designing UAV (unmanned aerial vehicle) provided with deflectable winglet
  • Method for designing UAV (unmanned aerial vehicle) provided with deflectable winglet
  • Method for designing UAV (unmanned aerial vehicle) provided with deflectable winglet

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Embodiment Construction

[0049] The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention.

[0050] In describing the present invention, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", " Orientation indicated by rear, left, right, vertical, horizontal, top, bottom, inside, outside, clockwise, counterclockwise, etc. The positional relationship is based on the orientation or positional relationship shown in the drawings, which is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, Therefore, it should not be construed as limiting the invention.

[0051] In this embodiment, a kind of unmanne...

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Abstract

The invention provides a method for designing a UAV (unmanned aerial vehicle) provided with a deflectable winglet. The problems that most UAVs nowadays have big height loss when performing dive and climb maneuvers, cannot guarantee cruising property and has poor stalling characteristics are solved by respective design of a main wing, inverted V empennages and the deflectable winglet of the UAV. The inverted V empennage layout and a rear propeller power mode are adopted. According to the layout, interference drag between the empennages as well as between the empennages and the fuselage can be reduced with fewer parts, and downwash of the empennages can be weakened to enhance course stability. Meanwhile, propeller slipstream can be avoided by the layout, so that pitching stability is improved.

Description

technical field [0001] The invention belongs to the design field of unmanned aerial vehicles, and in particular relates to a design method for an unmanned aerial vehicle with deflectable winglets. Background technique [0002] In the development of modern military power, people pay more and more attention to informatization and automation, and the increasingly complex battlefield environment also requires the improvement of the comprehensive combat capability of the troops. With the rapid development of artificial intelligence, sensor technology, and automatic control technology, more and more attention has been paid to the multi-task performance and combat capabilities of UAVs. Although the number, types, and frequency of UAVs are rapidly increasing, multifunctional and highly mobile military UAVs have not yet been deeply researched and developed. In terms of civilian use, it can be loaded with infrared, digital cameras or weather sensors and other equipment. The aircraft ...

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Application Information

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IPC IPC(8): B64F5/00G06F17/50
Inventor 郭正涛楚武利张莎
Owner NORTHWESTERN POLYTECHNICAL UNIV
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