Adaptive recursive control method and system for posture of hypersonic aircraft

Abstract

The invention discloses an adaptive recursive control method and system for the posture of a hypersonic aircraft. The method comprises the following steps of 1, building a posture error feature model with an expansion state through combining a control target, aircraft reentry attitude kinetic analysis and unmodelled dynamics and interference analysis, wherein the expansion state is used for describing the unmodelled dynamics and interference of the system; 2, building a fuzzy neural network estimator to estimate the expansion state in the feature mode, and combining with the structure of the feature model to jointly design an adaptive law of feature mode parameters and neural network parameters; and 3, based on an error surface, designing an adaptive control law in a recursive form to further improve the robustness of the control system. The method provided by the invention has better adaptive capacity to nondeterminacy, has the advantages of relatively strong robustness and relatively high control accuracy, and is applicable to accurately tracking the posture of the hypersonic aircraft under the complex unmodelled dynamics and strong interference environments.

Description

technical field [0001] The invention belongs to the field of aerospace and aviation, and relates to an attitude self-adaptive recursive control method based on a neural network feature model for highly uncertain hypersonic vehicles. Background technique [0002] Hypersonic vehicles often face a complex flight environment, the structural parameters and aerodynamic parameters during the flight are violently perturbed, and there are many unmodeled dynamic characteristics, which lead to strong uncertainties in the hypersonic vehicle model used for control system design. It brings difficulties to the design of high-precision attitude control. Adaptive control is a common method to solve the problem of object uncertainty, but the current aircraft attitude adaptive control method requires the specific structure of the aircraft aerodynamic model to be known, and can only solve the problem of parameter uncertainty. However, due to the lack of sufficient flight and ground tests, it i...

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Problems solved by technology

However, due to the lack of sufficient flight and ground tests, it is difficult to fully grasp the law of hypersonic gas flow, and there are strong uncertainties in the structure of the aerodynamic model

Robust control methods are also commonly used to solve the problem of object uncertainty, but the design of attitude control systems using robust control methods is based on the nominal structure of the model

However, the unmodeled dynamic characteristics of the aircraft lead to distortion of the basic structure of the control system

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