Control surface suitable for course autostability and control of high-aspect-ratio flying wing arranging airplane

A technology of aircraft heading and large aspect ratio, applied in the field of flying wing layout aircraft heading control, can solve the problems of lift reduction and other problems, achieve the effect of small drag increment, small channel coupling, and meet the requirements of heading control

Inactive Publication Date: 2016-08-17
CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] At present, the research on the course control rudder surface of aircraft with large-aspect-ratio flying wing layout mainly focuses on resistance rudder surfaces such as cracked

Method used

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  • Control surface suitable for course autostability and control of high-aspect-ratio flying wing arranging airplane
  • Control surface suitable for course autostability and control of high-aspect-ratio flying wing arranging airplane
  • Control surface suitable for course autostability and control of high-aspect-ratio flying wing arranging airplane

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Example Embodiment

[0022] Such as figure 1 As shown, the control surface of the present invention suitable for the flight stabilization and control of a large aspect ratio flying wing layout aircraft is located at the rear of the aircraft fuselage 1, and is composed of a left control surface 2 and a right control surface 3. Plane symmetrical placement, where the left control surface is connected to the fuselage 1 through the left rotation axis 4, and the right control surface is connected to the fuselage 1 through the right rotation axis 5. The directions of the left rotation axis 4 and the right rotation axis 5 of the control surface are both in the direction of the axis of the fuselage 1. Consistent, the left shaft 4 and the right shaft 5 are fixedly connected to the fuselage 1, and the control steering gear is installed inside the fuselage 1.

[0023] The left control surface 2 and the right control surface 3 are respectively controlled by different servos. The left control surface 4 drives the l...

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Abstract

The invention discloses a control surface suitable for course autostability and control of a high-aspect-ratio flying wing arranging airplane. The control surface is composed of two control planes symmetrically arranged at the rear portion of an airplane body. Each control plane is controlled by a single steering engine. The rotation axis is identical to the axis of the airplane body in direction. The deflection angle range of the control surface ranges from -90 degrees to 90 degrees. The control surface and the airplane body are combined into a whole after the control surface is closed. Through cracking rotation of the left side and the right side of the control surface, the course stability of the flying wing arranging airplane is effectively improved, and the course operation stability characteristic of the flying wing arranging airplane is improved. Compared with an existing resistance type rudder used for the high-aspect-ratio flying wing arranging airplane, the control surface for course control has the beneficial effects of being simple in mechanical structure, high in operation efficiency, small in channel coupling and small in augmented resistance, the control planes can be freely collected and released according to the airplane hiding characteristic, and the control surface can be used as a course-control control plane of the flying wing arranging airplane.

Description

technical field [0001] The invention belongs to the technical field of heading control of flying-wing layout aircraft, and in particular relates to a control surface suitable for heading stabilization and control of flying-wing layout aircraft with large aspect ratio. Background technique [0002] The flying wing layout aircraft adopts the wing-body fusion design, cancels the vertical tail and the flat tail, which can greatly enhance the stealth performance, increase the lift-to-drag ratio, reduce the structural weight and wing load, and improve the aircraft's range and flight time. However, after canceling the vertical tail of the aircraft, the basic directional stability and yaw control ability of the aircraft will be lost. Therefore, how to solve the problems of heading stability and heading control caused by canceling the vertical tail has become one of the key technologies in the design of flying-wing layout aircraft. [0003] At present, the research on the directiona...

Claims

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Application Information

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IPC IPC(8): B64C9/00B64C9/06B64C3/10
CPCB64C9/00B64C3/10B64C9/06
Inventor 贾洪印邓有奇周桂宇唐静马明生周乃春张培红郑鸣龚小权李彬
Owner CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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