A deflection control mechanism of a deformable head structure of a supersonic vehicle

A technology of deflection control and deformation structure, applied in aircraft control, aircraft parts, fuselage and other directions, can solve the problems of the failure of the deflection angle of the rudder surface and the reverse effect of the control, and achieve great practical value, low flight resistance, and simple principle. Effect

Active Publication Date: 2022-04-22
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
  • Description
  • Claims
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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

Method used

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  • A deflection control mechanism of a deformable head structure of a supersonic vehicle
  • A deflection control mechanism of a deformable head structure of a supersonic vehicle
  • A deflection control mechanism of a deformable head structure of a supersonic vehicle

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Embodiment Construction

[0030] In order to make the object, technical solution and effect of the present invention clearer and clearer, the following examples are given to further describe the present invention in detail. It should be pointed out that the specific implementations described here are only used to explain the present invention, not to limit the present invention.

[0031] like Figure 1~2As shown, the deflection control mechanism of the present invention includes a nose 1 and a body 3, and a deflection control mechanism 2 is arranged between the nose 1 and the body 3; the deflection control mechanism 2 is a symmetrical structure, including left and right symmetrical Double ball hinge connection structure 5; the two ends of the double ball hinge connection structure 5 are respectively connected to the head connection ring 4 and the fuselage connection ring 7; the double ball hinge connection structure 5, the head connection ring 4, and the fuselage are connected The rings 7 together for...

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Abstract

The invention discloses a deflection control mechanism of a deformable head of a supersonic aircraft, which belongs to the field of aircraft design. The invention proposes a structural concept of a deflectable deformation of the head of an aircraft, and provides a corresponding deflection control mechanism scheme. At the bending, deflection, and position of the aircraft head, a double ball joint structure is adopted, and four distance adjustment devices are evenly distributed in the circumferential direction. The rotation of the hinge structure is used to adjust the deflection direction of the aircraft head. Under the coordinated action of the distance adjustment device, the aircraft head can be deflected at any angle in the heading, and a bias moment is generated under the action of the airflow to change the flight direction. Direction, thereby improving the heading maneuvering efficiency of the aircraft when flying at high speed.

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...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C1/06B64C9/00
CPCB64C1/0683B64C1/069B64C9/00
Inventor 周丽陈鸣峰邱涛
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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