An adjustable stabilization device for a hypersonic vehicle

Abstract

The invention discloses an adjustable stability improving device of a hypersonic aircraft. The device comprises first tail skirts, second tail skirts, a first shaft sleeve, a second shaft sleeve and acenter shaft, wherein the first tail skirts and the second tail skirts are formed by a plurality of partially overlapped scales in a surrounding mode, and the scales of the first tail skirts are movably connected with the tail end of the aircraft and surround the aircraft by a circle; the scales of all the first tail skirts are connected with the first shaft sleeve through a framework; the scalesof the second tail skirts are movably connected with the tail ends of the scales of the first tail skirts in the axial direction of the aircraft, and the scales of all the second tail skirts are connected with the second shaft sleeve through a framework; the center shaft is sequentially sleeved with the first shaft sleeve and the second shaft sleeve in the axial direction of the aircraft, and thetension angles of the first tail skirts and the second tail skirts are changed freely along the central axis, so that the flight stability of the hypersonic aircraft is adjusted.

Description

technical field [0001] The invention relates to an adjustable stabilization device for a hypersonic aircraft, which belongs to the field of high-speed aircraft. Background technique [0002] With the development of hypersonic flight technology, the aerodynamic layout of hypersonic vehicles has gradually evolved to a plane-symmetrical lift layout. Although this type of hypersonic vehicle has many advantages, it has brought many problems in terms of flight stability. The lateral stability of the aircraft is low, and the flight speed is fast, which can easily cause strong uncontrollable motion of the aircraft. Foreign countries have carried out a lot of calculation and experimental research work on the lateral stability of hypersonic vehicles, such as improving the lateral stability by increasing the area of ​​the vertical tail, and arranging the head side strips or the longitudinal deflectors of the front body. Reduce asymmetric lateral forces, etc. Domestic research on the ...

AI Technical Summary

Problems solved by technology

However, the installation of the fixed tail skirt at the tail of the aircraft will occupy a certain amount of space, and the launch of the aircraft is often limited by the launch conditions, and the tail skirt will generate large air resistance during the boosting and climbing phase of the aircraft, which will affect the flight height and distance, and reduce economic benefits.

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