Eddy current generating device for controlling lateral force of large-incidence-angle slender body

Abstract

The invention relates to an eddy current generating device for controlling a lateral force of a large-incidence-angle slender body. A rotating mechanism is installed inside a conical head part of an aircraft, and the axis of the rotating mechanism is overlapped with that of the aircraft; a retraction jack is installed inside the conical head part of the aircraft and positioned between the rotating mechanism and the top end of the conical head part of the aircraft; a micro triangular wing in the retraction jack is arranged on the top end outside the conical head part of the aircraft. The micro triangular wing is driven by an electric telescoping rod to do telescoping movement along the axis direction of the aircraft. Unsteady weak turbulent flow generated by the micro triangular wing under the effect of airflow is used for performing the proportional control on the lateral force within the range of an angle of attack being 25 to 60 degree, and the control range of the lateral force coefficient is -3 to 3. The micro triangular wing can be withdrawn into the conical head part of the aircraft under the situations of zero lateral force and small lateral force, no additional resistance is produced, and the eddy current generating device is applicable to the aircraft with a taper angle being more than 30 degrees. The eddy current generating device has the characteristics of simplicity in structure, reliability in performance and the like.

Description

technical field [0001] The invention relates to the field of aircraft aerodynamic design, in particular to a vortex generator for controlling the lateral force of a slender body with a large angle of attack. Background technique [0002] When modern fighter jets and missiles maneuver at high angles of attack, there will be a sudden and uncertain side-slip movement of the head. This phenomenon is called "phantom yaw". This phenomenon is because when the slender spiral body is at a large angle of attack, even if there is no sideslip angle, a complex multi-vortex flow will be generated in the leeward region, which will bring a lateral force of almost the same magnitude as the lift force. force, which induces a large yaw and roll moment; and the direction of the lateral force is uncertain. [0003] In the range of small attack angles (0°≤α<10°), the flow around the model is a stable flow with no lateral force; in the range of small and medium attack angles (10°<α≤20°), th...

AI Technical Summary

Problems solved by technology

[0009] In the invention with the patent number 201120218920.2, an asymmetric vortex control device for the aircraft precursor is disclosed. Air blowing ports and oscillating jet devices are arranged on both sides of the leeward area of ​​the aircraft precursor. By changing the direction of the jet, the asymmetric vortex can be achieved. control, this device is complex and requires continuous energy input

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