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

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...

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 rudders and embedded resistance rudders. Increment to generate yaw moment, but it will couple roll and pitch, and reduce lift force, need other rudder surface to decouple and compensate

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