Composite material horizontal tail wing with leading edge slats

Abstract

The invention belongs to a helicopter structural design technology, and relates to a composite material horizontal tail wing with leading edge slats. The composite material horizontal tail wing comprises a horizontal tail wing box segment assembly, a left leading edge slat assembly and a right leading edge slat assembly, wherein the left leading edge slat assembly and the right leading edge slat assembly are connected with the left side and the right side of the front end of the horizontal tail wing box segment assembly correspondingly; the left leading edge slat assembly is formed by rivetinga left leading edge slat and a plurality of brackets; the right leading edge slat assembly is formed by riveting a right leading edge slat and a plurality of brackets; the cross section of the left leading edge slat is of an inverted water drop shape, and the contour shape of the leading edge of the left leading edge slat is consistent with the contour shape of the leading edge of a co-curing boxsegment; the contour of the right leading edge slat is the same as that of the left leading edge slat; the horizontal tail wing box segment assembly is a main body structure of the horizontal tail wing; and the horizontal tail wing box segment assembly comprises an integral co-curing box segment, a left trailing edge, a right trailing edge, a left front end rib, a right front end rib, a left rearend rib and a right rear end rib. The horizontal tail wing structure of the composite material horizontal tail wing has the advantages that the stability of the pitching moment is improved, and the effects are obvious on the improvement of the anti-bird-striking and anti-fatigue capabilities.

Description

technical field [0001] The invention belongs to the helicopter structural design technology, and relates to a composite material horizontal tail with leading edge slats. Background technique [0002] At present, single-rotor helicopters generally have a horizontal tail with a small area, which is used to improve the longitudinal stability and angle-of-attack stability of the helicopter. Most helicopter horizontal stabilizers are installed at a fixed angle. Since the installation angle of the horizontal stabilizer is fixed, the stability of the pitching moment of the helicopter will be affected when it is in a gust of wind or in a hovering state. With the development of military and civilian helicopter technology, helicopters have higher and higher requirements for improving the aerodynamic performance and safety of the horizontal tail, such as improving the stability of the pitching moment and the structure anti-bird strike ability required by the airworthiness of civil hel...

AI Technical Summary

Problems solved by technology

However, the load transfer efficiency of the horizontal tail of the invention is not high, and it is necessary to balance all the bending moments borne by the horizontal tail through the tail structure

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