An aircraft adopting the aerodynamic layout of the double-pointed fishtail leading edge

Abstract

The invention provides an air vehicle adopting a double-pointed-cone fish tail type front edge aerodynamic layout. The air vehicle comprises a vehicle body and an engine. The vehicle body comprises head pointed cones, a transition section, air inlet channel pointed cones and a blended wing body. The two head pointed cones are adopted and symmetrically arranged on the two sides, so that the low-pressure area of the head of the air vehicle is effectively enlarged, the trim capability of the whole vehicle is improved while the lift force is increased, and the trim resistance of the whole vehicle is reduced; by designing the transition section in the gap between the head pointed cones and the blended wing body, the vortex core central position on the inner sides of the head pointed cones is controlled, unfavorable interference between vortexes is reduced, the air flow energy of the upper surface is supplemented at the same time, and the lift force is increased; the air inlet channel pointed cones are arranged in the middle of the transition section, and then the vortex lift force of the upper surface of the air vehicle and high-angle-of-attack air inlet efficiency are improved; besides, the shielding effect on an air inlet channel is achieved through the head pointed cones and the transition section, and the hidden performance is improved; by means of the design of a plane groove surface between an air inlet channel lip and a tail jet nozzle on the lower surface of the air vehicle, the purpose of increasing the lift force is achieved. By means of the aerodynamic layout scheme, the hidden performance, taking-off and landing performance, subsonic speed and transonic speed maneuvering characteristics, the supersonic cruise performance, the poststall maneuver performance and other indexes can be well considered.

Description

technical field [0001] The invention relates to the technical field of aerospace, in particular to an aircraft adopting the aerodynamic layout of the double pointed cone fishtail leading edge. Background technique [0002] Aircraft is the backbone of modern national defense, and it is also a symbol of the comprehensive strength of a major country such as economic strength, scientific and technological strength, and basic industry. In the complex system engineering of aircraft design, aerodynamic layout design is the forerunner and the most important thing. It is directly related to the layout and design of all subsystems, and is also a key factor for each system to realize its potential. [0003] At present, there are few aircraft aerodynamic layout schemes that take into account performance indicators such as stealth performance, take-off and landing performance, sub- and transonic maneuvering, supersonic cruise, and post-stall maneuvering. , it is necessary to consider a ...

AI Technical Summary

Problems solved by technology

Among them, the conventional layout scheme can better take into account various indicators, especially the take-off and landing performance, but the supersonic performance, stealth characteristics and other indicators have no obvious advantages; the delta wing layout scheme with short-range / long-distance canards is adopted, While inheriting the advantages of good high-speed performance and high structural efficiency of the delta wing, it can better solve the shortcomings of the delta wing's poor low-speed performance and insufficient trimming ability. The disadvantage of this type of layout is poor stealth performance; the flying wing layout adopts the piggyback inlet The scheme has the characteristics of high lift-to-drag ratio and high stealth, and is mostly used for bombers and drones that do not have maneuverability and supersonic flight capabilities; the variant layout scheme is relatively advanced, and is mostly based on complex variant mechanisms Or smart materials, piezoelectric materials and other new concept technologies can realize the variable aerodynamic layout of aircraft wings such as folding / expanding or wing airfoil and sweep angle, etc., to achieve the purpose of taking into account various indicators. The disadvantage is that the structure is complex and It is difficult to realize, and at the same time, the aerodynamic problem is prominent in the layout change, etc.

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