Supersonic missile anti-drag wings

Abstract

Disclosed are supersonic missile anti-drag wings. Two sets of missile wings are distributed on two sides of a missile body symmetrically. Each missile wing comprises an upper wing piece and a lower wing piece. Root chord lengths of the upper wing pieces and the lower wing pieces are both 0.52m, and stretching lengths of the upper wing pieces and the lower wing pieces are both 0.52m. The upper reflex angle of each upper wing piece is -9 degrees, and the upper reflex angle of each lower wing piece is 9 degrees. The leading edge backward sweep angles of the upper wing pieces and the lower wing pieces are both 63.6 degrees. Each upper wing piece and each lower wing piece are respectively connected with a driving mechanism. When a Mach number of a supersonic cruise missile is lower than a design point, the upper wing pieces on the two sides of the missile body deflect downwards, the lower wing pieces deflect upwards so that the area ratio of the maximum thickness portion of the wings and the leading edge inlet is 1. Upper stream passes between the wings so that occurrence of jamming is avoided. When the Mach number continues to increase and reaches the designed Mach number, the upper wing pieces on the two sides of the missile body deflect upwards, the lower wing pieces deflect downwards, and the Busemann double-wing outward position is realized. Shock wave resistance can be reduced by utilizing wave interference effect of shock wave weakening and shock wave expanding.

Description

technical field [0001] The invention relates to the field of modern aerospace, in particular to a variable double-wing drag-reducing configuration of a supersonic missile. Background technique [0002] For supersonic cruise missiles, wave resistance is an important part of the total resistance, and most of the time the cruise missile will fly at the designed Mach number in the cruising state. horn. In order to improve the aerodynamic performance of the missile in cruising state, thereby increasing its firing range, it is of great significance to reduce the wave resistance in cruising flight state. As the main load-bearing part of the cruise missile, the resistance generated by the wing, especially the shock wave resistance, accounts for a large part of the total resistance. It is very difficult to reduce the wave resistance by significantly reducing the strength of the shock wave on it by conventional layout. [0003] As early as 1935, Adolf Busemann proposed to place anot...

AI Technical Summary

Problems solved by technology

However, this Busemann wing will appear "choked up" when it deviates from the design Mach number, and the resistance will increase sharply even much greater than the conventional wing layout (such as diamond wing)

Since there is no good solution to the sharp increase in drag caused by the choked flow that occurs when deviating from the design point, Busemann's biplane theory has not been specifically applied to actual supersonic aircraft for half a century

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