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Pneumatic composite control tailless flying wing layout unmanned aerial vehicle and control method thereof

A composite control, UAV technology, applied in non-electric variable control, aircraft control, attitude control and other directions, can solve the problems of destroying stealth performance, insufficient maneuverability, slow response speed, etc., to achieve fast response speed and reduce interference , the effect of simple structure

Active Publication Date: 2020-07-31
CHINA ACAD OF AEROSPACE AERODYNAMICS
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0014] The technical problem solved by the present invention is: to overcome the deficiencies in the prior art, to propose a tailless flying-wing unmanned aerial vehicle with aerodynamic compound control and its control method, to solve the problem of complex structure of traditional mechanical deflection rudder surface, damage to stealth performance and maneuverability Insufficient and slow response problems

Method used

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  • Pneumatic composite control tailless flying wing layout unmanned aerial vehicle and control method thereof
  • Pneumatic composite control tailless flying wing layout unmanned aerial vehicle and control method thereof
  • Pneumatic composite control tailless flying wing layout unmanned aerial vehicle and control method thereof

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Embodiment

[0052] A specific embodiment of the present invention designs an aerodynamic compound control scheme for attitude and overload of a tailless flying wing layout with small aspect ratio. The total length of the flying wing is 20m, the wingspan is 15.3m, the empty weight is 12t, the longitudinal distance between the center of mass and the head is 9m, the sweep angle of the leading edge is 65°, and the trailing edge of the tail is W-shaped. At a distance of 0.1m from the trailing edge of the airfoil, six jet slits are arranged on the upper and lower airfoils parallel to the trailing edge, and the width of the slit is 1mm. 1.5, the total jet pressure is adjusted in the range of 0.1MPa~1MPa according to the flight attitude. The center of the track control nozzle on the lower surface is at the center of mass, the longitudinal position is 9.2m, and the nozzle outlet is circular in shape with a diameter of 0.433m. The engine grain adopts HTPB / AP type propellant, and the specific heat ...

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Abstract

The invention relates to a pneumatic composite control tailless flying wing layout unmanned aerial vehicle and a control method thereof. A plurality of air injection slits with continuously adjustablepressure are arranged on the upper surface and the lower surface of the unmanned aerial vehicle parallel to the rear edge, and jet flow counteraction thrust is used for replacing a pneumatic controlsurface to perform aircraft three-channel attitude control; and meanwhile, a solid pulse engine is downwards arranged at the mass center of the unmanned aerial vehicle and is used for improving the instantaneous overload of the aircraft during high-maneuverability flight. The defects that a traditional pneumatic control surface is low in response speed, complex in structure, large in weight, low in tailless flying wing layout overload capacity and the like are overcome, and the attitude control and maneuvering capacity of the flying wing unmanned aerial vehicle can be remarkably improved.

Description

technical field [0001] The invention relates to a tailless flying-wing unmanned aerial vehicle controlled by aerodynamic compound control and a control method thereof, belonging to the field of unmanned aerial vehicle control. Background technique [0002] At present, the traditional control surfaces of aircraft are connected by hinges and driven by mechanical devices. The disadvantages include: [0003] (1) Complex structure and heavy weight; [0004] (2) The deflection of the rudder surface caused partial damage to the stealth shape of the aircraft, which reduced the survivability; [0005] (3) The response time of the actuating mechanism of the wing rudder is long, and the delayed response leads to a decrease in control accuracy; [0006] (4) The control ability of the control surface is seriously insufficient at low speed and high angle of attack. [0007] In order to meet the performance requirements of high maneuverability and strong stealth, the future development ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C15/14B64C21/02B64C19/00B64C39/02G05D1/08G05D1/10
CPCB64C15/14B64C21/02B64C19/00B64C39/02G05D1/0808G05D1/101B64U10/00
Inventor 陈培刘松罗世杰马继魁李康康
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS
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