Device for eliminating side force of slender body at large incidence angle

Abstract

The invention discloses a device for eliminating side force for a slender body at a large incidence angle, comprising a film support frame and a retractable mechanism. A cover just above the front part of the head of the flying vehicle is provided with a retractable slit, the front end of the head of the flying vehicle is provided with a small bracket (8) and a large bracket (17). An electric telescopic rod (7) is located between the two brackets; the axis line of the electric telescopic rod (7) overlaps the central connection line of the two brackets. A guide rail (6) is located under the axis line of the flying vehicle and is parallel to the axis line. A connecting tube (18) is sleeved on a sleeve (2) of the film support frame, and is fixedly connected with two connecting sheets at one side of the connecting tube (18) through a connecting plate of a sliding block (12). The invention realizes the unfolding and the folding of a film (5) through the stretching and contracting movement of the electric telescopic rod at the axis line direction of the airplane; under the role of the airflow, the film generates self-excited vibration and non-steady streaming around, realizes the control of the asymmetric vortex, and eliminates the side force; the structure is simple, the performance is reliable, therefore, the invention is suitable for a fighter or a tactical missile and other flying vehicles.

Description

Technical field [0001] The invention relates to the aviation, aerospace and weapon industries, and is a device for eliminating the lateral force of a slender body at a high angle of attack. Background technique [0002] When aircraft such as fighter jets or tactical missiles are flying at a high angle of attack, the flow in the leeward zone of the aircraft is composed of vortices with asymmetric strength and position. The lateral forces generated by these asymmetric vortices bring about the flight and control of the aircraft. Many disadvantages. How to eliminate these lateral forces by adjusting the precursor asymmetric vortex is a technical difficulty that aerodynamicists and scientific research institutions have been working hard to study. [0003] In the range of low angle of attack (0°≤α<10°), the flow around the model is an adherent and stable flow, and the lateral force is zero; in the range of small angle of attack (10°<α≤20°), the model flows Separation occurs, a pa...

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Problems solved by technology

[0004] At present, there are mainly the following measures to control the asymmetric vortex at high angle of attack: 1) Holes are drilled in the head of the model, and the lateral force is controlled by the control method of pulsating air blowing through small holes. The main disadvantage is the control of the asymmetric vortex. The required blowing volume is closely related to the incoming flow velocity, that is to say, as the flight speed increases, the blowing volume also increases accordingly, so the required energy also increases, and the weight cost of additional equipment is relatively high; 2) Put the model head It is transformed into a movable nose cone, which is controlled by the left and right deflection or rotation of the nose cone. Obviously, the mechanism of this method is complicated, and the changes to the model are relatively large; The forced vibration of the vibration mechanism realizes the control of the asymmetric vortex with a small energy consumption. According to the results of the literature, this control method is very effective, but the small disturbance vibration mechanism is still very complicated, and requires the power supply and control mechanism. The weight cost is also high, and sometimes it is not convenient to place in the limited space on the head of the model

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