Control surface control method based on discrete system direct control distribution

Abstract

The invention relates to the technical field of aircraft control, and provides a control surface control method based on discrete system direct control distribution. According to the method, constraints of rudder deviators and rudder deflection rates of a plurality of control surfaces are considered at the same time according to pitching, rolling and yawing moments required by aircraft control; based on discrete flight point data of an aircraft control surface pneumatic database, a direct distribution method is adopted to calculate respective rudder deviation distribution amounts of the plurality of control surfaces, and accurate control over the flight state of an aircraft is realized. According to the invention, discretization improvement is carried out on the basis of a direct distribution method, and piecewise linearization is carried out according to an aerodynamic control surface database so as to adapt to nonlinear characteristics of the aerodynamic control surface database. Meanwhile, in order to clarify the physical significance of each control surface and facilitate state analysis in the use process, a chain type distribution thought is introduced, and the use conditionsof each control surface are used in a graded and classified mode according to aerodynamic characteristics.

Description

technical field [0001] The invention relates to the technical field of aircraft control, in particular to a rudder surface control method based on discrete system direct control distribution. Background technique [0002] With the increasing complexity of the modern war environment and combat missions, a variety of new aerodynamic UAVs have attracted more and more attention, among which the research on UAVs with flying wings is the most popular. In order to improve the reliability of UAVs and ensure the safety of UAVs and equipment to the greatest extent, most flying-wing UAVs have increased the number of aerodynamic rudder surfaces to improve the fault tolerance of UAV control. The multi-rudder surface configuration of the flying-wing UAV effectively solves the fault tolerance problem of the rudder surface failure. Its single rudder surface can produce different control effects, and the same control axis can also be manipulated by different rudder surfaces. Therefore, when ...

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Problems solved by technology

[0004] The traditional direct allocation method only considers the deflection position constraint of the rudder surface, and considers that the aerodynamic characteristics of the rudder surface have no obvious nonlinear characteristics under this constraint. Its aerodynamic characteristics present certain nonlinear characteristics, and the traditional direct distribution method cannot meet the distribution accuracy required for engineering applications

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