Deflection control mechanism of head deformable structure of supersonic aircraft

Abstract

The invention discloses a deflection control mechanism for a head deformable structure of a supersonic aircraft, belongs to the field of aircraft design, provides a structural concept that the head of the aircraft can deflect and deform, and provides a corresponding deflection control mechanism scheme. Double-ball-joint structures are adopted at bending and deflection positions of the head of the aircraft. Four distance adjusting devices are evenly distributed in the annular direction, each distance adjusting device can conduct telescopic adjustment, rotation of the double-spherical-hinge structure is controlled through stretching and retracting of the four distance adjusting devices, and therefore the deflection direction of the head of the aircraft is adjusted, and under the coordination effect of the distance adjusting devices, the head of the aircraft can deflect at any angle in the course, bias torque is generated under the action of airflow, the flight direction is changed, and therefore the course maneuvering efficiency of the aircraft in the high-speed flight process is improved.

Description

technical field [0001] The invention belongs to the field of aircraft design, and in particular relates to a deflection control mechanism of a deformable head structure that can be used to improve the maneuverability of a supersonic aircraft. Background technique [0002] The control efficiency of a supersonic vehicle is an important index to measure its performance, and the high-efficiency control method has great research value. [0003] However, in the existing control methods, the control surface is mostly located at the rear of the aircraft. As the flight speed increases, the structural elastic deformation of the lifting surface will have a greater impact on the efficiency of the rudder surface. In general, with the deflection of the control surface, the change of the camber of the airfoil will produce an additional lift force opposite to the direction of the lift force; as the flight speed increases, the value of the additional lift force will continue to increase, and...

AI Technical Summary

Problems solved by technology

When the flight speed increases to a certain value, the deflection angle of the rudder surface completely loses its effect, and the control efficiency becomes zero; if the dynamic pressure is increased, the opposite effect will even occur, that is, the control reverse effect

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