Aircraft guidance and control integrated method facing accelerator constraint

Abstract

The invention provides an aircraft guidance and control integrated method facing accelerator constraint, belongs to the field of flight control, and is used for solving the problem of accelerator strong constraint caused by coupling of an aircraft fuselage propulsion system. The method is oriented to an aircraft longitudinal dynamics model, a control law is designed based on a backstepping method framework thought by analyzing an internal dynamics mechanism, a constraint model of quadratic programming is established for a speed guidance system in combination with an accelerator constraint index, and a loss function is defined and is solved and optimized by utilizing a KKT algorithm. A neural network technology is adopted to learn dynamics uncertainty, a series-parallel model is established to design a prediction error, interaction parameters of a guidance system and a control system are established, and a self-adaptive updating law of a neural network weight is designed by combining a tracking error, the prediction error and the interaction parameters. The flight stability under the throttle constraint and the high-precision flight state tracking under the complex environment are realized.

Description

Technical field [0001] The present invention involves a method of aircraft control, especially in an integrated method for aircraft guidance control control constraints, which is the field of flight control. Background technique [0002] Due to the complexity of the aircraft dynamics and the coupling between the fuselage advance system, there is an inevitable constraint on the aircraft control input, which will exacerbate the design difficulties of the control system. The aircraft engine of the aircraft is prone to heat stuffing and increases the resistance of the aircraft to reduce the thrust of the engine, which seriously affects the safety of the flight. At the same time The necessary conditions for operation, so this is a strict constraint that must be solved and guided and controlled to avoid the engine heat stuffy. [0003] 《Integrated Adaptive Guidance and Control of Constrained NonlinearAir-breathing Hypersonic Vehicle Models》(Andrea Serrani,《Conference onAmerican Control...

AI Technical Summary

Problems solved by technology

However, the paper did not design the controller for the dynamic model mechanism, and did not consider the strong uncertainty caused by the change of aerodynamic parameters in the design. It is difficult to achieve high-precision flight state tracking in a complex flight environment.

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