Flight control system of wing-layout-hidden unmanned aerial vehicle and control method of flight control system

A flight control system and a technology for unmanned aerial vehicles, which are applied to the flight control system and the control field of the flying wing layout stealth unmanned aerial vehicle, can solve the problems of poor flight stability and low operation efficiency, and achieve the reduction of the moment of inertia and the operation efficiency. High, weight saving effect

Active Publication Date: 2017-11-03
西安天拓航空科技有限公司
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  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The present invention provides a flight control system and control method for a stealth drone with a flying wing layout, the purpose of which is to solve the problem of the flight control of an existing stealth drone with a flying wing layout. Problems of poor stability and low operating efficiency

Method used

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  • Flight control system of wing-layout-hidden unmanned aerial vehicle and control method of flight control system
  • Flight control system of wing-layout-hidden unmanned aerial vehicle and control method of flight control system
  • Flight control system of wing-layout-hidden unmanned aerial vehicle and control method of flight control system

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Embodiment Construction

[0019] The present invention is described in detail below in conjunction with accompanying drawing and specific embodiment:

[0020] Such as figure 1 As shown, the aerodynamic shape of the flying wing includes a left wing section and a right wing arranged symmetrically with the left wing section; section, the left three wing sections; the right wing section includes the first right wing section 11, the second right wing section 12, and the third right wing section 13 arranged sequentially from inside to outside; the wing of the first right wing section 11 The negative camber airfoil closest to the root transitions to the S-shaped airfoil at the tip; the root airfoil of the second right wing section 12 is the same as the tip airfoil of the right wing section 11, and the tip is a large camber wing type; the right three wing section 13 is the wingtip section, and the root airfoil is the same as the tip airfoil of the right second wing section 12, and the tip converges into one p...

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Abstract

The invention relates to the field of unmanned aerial vehicles, in particular to a flight control system of a wing-layout-hidden unmanned aerial vehicle and a control method of the flight control system, aiming to solve the problems of poor flight stability and low operation efficiency of an existing wing-layout-hidden unmanned aerial vehicle. First control surfaces respectively arranged at rear edges of a left first wing section and a right first wing section, a second control surface and a third control surface respectively arranged at rear edges of a left second wing section and a right second wing section, and fourth control surfaces respectively arranged on upper surfaces of the left second wing section and the right second wing section cooperatively act, so control on various flight attitudes of the unmanned aerial vehicle is realized, the flight stability is good, and the operation efficiency is high.

Description

technical field [0001] The invention relates to the field of unmanned aerial vehicles, in particular to a flight control system and a control method for a stealth unmanned aerial vehicle with flying wing layout. Background technique [0002] In order to complete the control tasks of various modes of the UAV, it is necessary to use the flight control system to achieve accurate control of the attitude and flight trajectory. The flight control system is the core of the UAV. Various performance indicators and flight safety of the flight control system are directly affected by the quality of the flight control system. The wing-body fusion flying wing layout simply means that there is only the aerodynamic layout of the aircraft's wings, and the fuselage and wings are integrated without obvious boundaries. Undoubtedly, this layout is the most aerodynamically efficient layout, because all body structures are lifting bodies that can generate lift, and the wing-body fusion design min...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C9/06B64C9/12
CPCB64C9/06B64C9/12B64U10/25B64U2201/10B64U20/10Y02T50/40
Inventor 不公告发明人
Owner 西安天拓航空科技有限公司
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