A lateral control method and control system for a plane-symmetrical hypersonic vehicle using coupling

Abstract

The invention discloses a transverse and lateral control method and system for a plane-symmetry hypersonic flight vehicle by using coupling. The method comprises the following steps: (1) obtaining measurement information of an airborne sensor of the plane-symmetry hypersonic flight vehicle; (2) analyzing the roll-to-swing ratio characteristic of the hypersonic flight vehicle in the transverse direction and the stability characteristic of the Dutch roll coupling mode; (3) analyzing control coupling modal characteristics of the hypersonic flight vehicle aileron during operation; (4) feeding backthe roll angle rate to the aileron to improve the damping characteristic of the Dutch roll; (5) feeding back the sideslip angular rate to a rudder to improve the damping characteristic of the Dutch roll coupling mode, and restraining the motion coupling influence; (6) feeding back the sideslip angle deviation to the rudder to improve the stability characteristic of the Dutch roll coupling mode; and (7) feeding back a roll angle deviation to a sideslip angle instruction, and realizing roll control by using Dutch roll coupling. The requirement of coupling control on the pneumatic control surface control capacity is lowered, and the overall design pressure of the aircraft is reduced.

Description

technical field [0001] The present invention relates to hypersonic aircraft control technology, in particular to a lateral control method and control system of a plane-symmetrical hypersonic aircraft utilizing coupling. Background technique [0002] The hypersonic aircraft adopts a symmetrical layout and a high lift-to-drag ratio shape. It has the characteristics of fast flight speed, long flight distance, strong maneuverability, and high penetration probability. With its unique advantages, it plays an important role in the long-range penetration of modern warfare. , has been highly valued by countries all over the world. In 2010, the United States successively launched three hypersonic vehicles with different purposes: HTV-2, X-37B and X-51A. Another climax of development. Driven by this development trend, it is of great significance both in theory and in engineering to carry out research on theories and methods related to hypersonic vehicle control. [0003] Due to the ...

AI Technical Summary

Problems solved by technology

Compared with traditional aircraft, the Mach number, angle of attack, altitude, and dynamic pressure of hypersonic aircraft vary widely, and instability, strong coupling, strong nonlinearity, and strong uncertainty are superimposed on each other, which seriously affects the stability of the aircraft. Especially when flying at a high angle of attack, the three-channel coupling is serious, and the horizontal direction shows serious non-minimum phase characteristics, which poses a serious challenge to the design of the control system

[0004] At present, decoupling control is mostly used for the three-channel coupling problem of surface-symmetric aircraft. However, due to the large span of airspace and speed domain of hypersonic aircraft, the control ability varies greatly in different dynamic pressure areas, especially when flying at high angles of attack. The control ability of the rudder surface is insufficient, and it is difficult to directly perform decoupling control

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