Separation Controller Based on Parameter Identification

Abstract

The invention provides a separation controller based on parameter identification, which includes a feedback controller, an instruction generator and a state observer group; the instruction generator generates an attack angle instruction according to an attack angle instruction profile designed based on a constant pitch angle speed instruction, and inputs the feedback control The state observer group includes a first state observer and a second state observer, which are used to observe the controlled object and input the instruction generator, and the first state observer also takes its observation result as the input of the feedback controller; During the control process, the first state observer and the second state observer identify the stable zero-control equilibrium state of the controlled object; the command generator determines the initial time when the equilibrium state arrives, and after this time, will generate The attack angle control command is switched to the equilibrium state attack angle control command. The controller of the invention effectively realizes the identification and stable control of the stable equilibrium state of the aircraft, and avoids the problems of non-convergence of algorithms and poor real-time performance in the prior identification methods.

Description

technical field [0001] The invention relates to the technical field of aircraft control, in particular to a separate controller based on parameter identification. Background technique [0002] Existing hypersonic vehicles mostly adopt boost + cruise two-stage flight mode. The purpose of the booster stage is to send the load into the predetermined transfer window. In order to save weight and energy, most of the thrust reversers are not used. Therefore, in order to successfully realize the separation between the stages, the separation command must be issued at the end of the thrust. At the same time, for the aircraft that only achieves attitude stability control through thrust vector during the boosting process, facing the problems of insufficient control ability and large uncertainty in the later stage of thrust trailing, it is necessary to choose a statically stable equilibrium state where the torque is zero in the uncontrolled state. achieve stability control. Affected by...

AI Technical Summary

Problems solved by technology

The general disadvantages of these methods are that the algorithm is complex, the demand for computing resources is large, and the convergence is often difficult to guarantee in the actual application process. It is generally suitable for slowly changing industrial processes, and it is difficult to truly apply to the aircraft control system.

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