Plane with nose-up pitching moment

Abstract

The invention discloses a plane with nose-up pitching moment and relates to the technical field of aviation aircrafts. The plane structurally comprises a plane body and an empennage, wherein the empennage comprises a vertical empennage and a horizontal empennage; the vertical empennage is arranged at the rear part of the plane body; the horizontal empennage is arranged at the top end of the vertical empennage to form a T-shaped empennage; a bulge part is arranged on the top surface of the front part of the plane body; and smooth transition is adopted between the bulge part and the rear part of the plane body, so that the top surface of the plane body forms a streamlined surface. The height difference between the highest point and the lowest point of the top surface of the plane body is D, and the height difference between the lowest points of the upper surface of the horizontal empennage and the top surface of the plane body is H, wherein D is more than 0.3H and less than 2H. The plane disclosed by the invention has the advantages that the top surface of the front part of the plane body is bulged, so that the flow field generates deflection; and the flow fields of the upper surface and lower surface of the horizontal empennage are not symmetrical, and at the time, the nose-up pitching moment is generated for the plane body, so that the stability of the plane in the flight process is guaranteed.

Description

technical field [0001] The invention relates to the technical field of aviation aircraft, in particular to an aircraft with nose-up moment. Background technique [0002] Horizontal stabilizer, referred to as the horizontal tail, is installed at the rear of the fuselage and is mainly used to maintain the stability of the aircraft in flight and control the flight attitude of the aircraft. However, in practical applications, the horizontal stabilizer does not take into account the influence of the fuselage in the design, so that its effect is greatly reduced. Under normal circumstances, the horizontal tail is installed at the tail of the fuselage. Due to the influence of the flow field of the fuselage, the lift generated by the horizontal tail will often be weakened, which will produce a different effect than expected, resulting in slow take-off and weak climbing ability of the aircraft. The anti-jamming ability is poor, which is not conducive to controlling the flight attitud...

AI Technical Summary

Problems solved by technology

However, in practical applications, the horizontal stabilizer does not consider the influence of the fuselage in its design, which greatly reduces its effect

Under normal circumstances, the horizontal tail is installed at the tail of the fuselage. Due to the influence of the flow field of the fuselage, the lift generated by the horizontal tail will often be weakened, which will produce a different effect than expected, resulting in slow take-off and weak climbing ability of the aircraft. Poor anti-jamming capability, which is not conducive to controlling the flight attitude of the aircraft and improving flight stability

Images