Aircraft posture kinetics simplified model gain switching proportion-differential control design method

Abstract

The invention relates to a design method for derivative controlling the gain switching ratio of an aerocraft pose dynamics simplified model, which adopts a nonlinear gain switching PD controlling scheme and allows two PD subcontrollers (a rapid PD subcontroller and a heavy damping subcontroller) designed with different parameters and complementary performance cooperatively function by stages according to switching rules designed. Meanwhile, on the basis of the guarantee of stability of an enclosed ring controlling system in the large, the step response of the system with no overshoot is realized, and the adjusting time of the step response is flexibly adjusted to meet the design requirements of rapidity. The technical scheme of the designing method comprises that: a first step, the structure of the enclosed ring controlling system is designed; a second step, a gain switching strategy section is designed; a third step: the gain parameters of two PD subcontrollers are designed; a fourthstep: the rapidity of the step response is inspected and adjusted; a fifth step: the stability of an enclosed ring controlling system in the large is validated; a sixth step: the design is finished.

Description

(1) Technical field Aiming at the simplified model of aircraft attitude dynamics (belonging to double integral system), the invention provides a design method of gain switching proportional-derivative (Proportional-Derivative, PD) control, which belongs to the technical field of aircraft control. (2) Background technology Rapid system response and no overshoot are two contradictory performance indicators. When designing a controller, it is often necessary to take both control requirements into consideration. For example, in the takeoff-landing phase of fixed-wing flight, not only the response of angle of attack and attitude angle is required to be fast enough, but also the response of these two controlled quantities is required to have no or small overshoot (limited by ground angle). The book "Modern Flight Control" edited by Wen Chuanyuan and others pointed out: "The whole process of raising the front wheel of a certain type of fighter takes about 2 seconds" and "the aircr...

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Problems solved by technology

This control method takes into account the requirements of response speed and overshoot to a certain extent, but it is difficult to obtain the condition that the system step response has no overshoot

At present, although this type of research discusses the design of switching controllers and the stability analysis of closed-loop systems, it does not further discuss the impact of this type of gain switching controller on the performance of closed-loop systems, let alone discuss the system order under this type of control. Time-domain indicators of jump response, such as adjustment time and overshoot, etc.

Therefore, control engineers cannot directly apply this nonlinear control idea to design a step response non-overshoot controller

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