Fuzzy coordinated control method for hypersonic vehicle with interfered observation of variable inlet

Abstract

The invention relates to hypersonic vehicle control and aims to propose a coordinated control method for a variable inlet hypersonic vehicle fuzzy system with external disturbances. The steps in the method are as follows: The first part is a transformation design of a strict feedback form of a variable inlet hyperplane; the second part is a design of a speed controller and a nonlinear disturbanceobserver; the third part is a design of a height controller and a nonlinear disturbance observer. The nonlinear disturbance observer is used to compensate the designed subsystem controller, observe the interference in a real-time manner, and enhances the robustness of the designed subsystem controller. The method in the invention is mainly applied to situations of hypersonic vehicle control.

Description

technical field [0001] The present invention relates to the invention in the field of control system design of hypersonic aircraft, in particular to the field of research on coordinated control of variable inlet hypersonic aircraft. Specifically, it involves a fuzzy coordinated control method for hypersonic vehicles with variable inlets. It specifically relates to the fuzzy coordinated control method of the disturbance observation variable inlet hypersonic vehicle. Background technique [0002] A hypersonic aircraft refers to an aircraft with a flight speed greater than Mach 5, flying in near space, and integrating the advantages of orbital fighters, space vehicles, and even satellite space stations. It has the characteristics of large airspace, ultra-high speed, and long distance. Fast and precise strategic strike is one of the important guarantees to ensure national strategic security. It has the characteristics of extremely high flight speed, long operating cycle, stable...

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Problems solved by technology

[0003] However, the hypersonic vehicle uses a scramjet engine, and its unique airframe / engine integrated structure not only reduces the burden on the airframe, but also increases the nonlinearity of the model. more difficult to control

In addition, in order to ensure the best performance of the engine at high Mach, the design of the inlet generally adopts a fixed geometry inlet, and its structural design can only ensure the operational performance of the aircraft at its design point. When the control performance drops sharply, especially at low Mach, the shock angle increases, and the engine intake cover cannot capture sufficient airflow, which limits the engine operation

The structural design of the variable geometry inlet breaks through this limitation. However, the research on the control field of the variable geometry inlet is still in its infancy, and the existing control difficulties are reflected in the following aspects: (1) The introduction of the variable geometry inlet The airway structure will cause aerodynamic uncertainty, especially the impact on the thrust; (2) The introduction of the variable geometry inlet structure will increase the nonlinearity of the aircraft control model; (3) The variable geometry The coupling effect of airway control and flight control greatly increases the complexity of the control system; (4) When the flight control is in a complex environment near space, the external interference changes drastically, which leads to the increase of the uncertainty of the aircraft system and the flight control performance. It is difficult to achieve the desired control effect

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