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Coupling-analysis-based attitude coordination control method of hypersonic flight vehicle

A hypersonic and coupling analysis technology, applied in the direction of attitude control, adaptive control, general control system, etc., can solve problems such as no analytical expression, difficult coupling analysis results, coupling analysis stays in qualitative analysis, etc.

Inactive Publication Date: 2017-08-22
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

Obviously, the unremitting efforts of the predecessors have made significant research results in the research on the coupling problem of hypersonic vehicles. However, the disadvantage is that most of the coupling analysis stays in the qualitative analysis stage, and there is no precise analytical expression. The coupling analysis The result is difficult to apply to controller design, which makes its corresponding controller less specific for coupling

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  • Coupling-analysis-based attitude coordination control method of hypersonic flight vehicle

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Embodiment Construction

[0124] The present invention will be further explained below in conjunction with the accompanying drawings and specific embodiments. It should be understood that the following specific implementation

[0125] The formulas are only used to illustrate the present invention and are not intended to limit the scope of the present invention.

[0126] The hypersonic vehicle attitude dynamics model is represented by the following mathematical model:

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[0129] Where, Ω=[α,β,μ] T are angle of attack, angle of sideslip, and yaw angle respectively, ω=[p,q,r] T are the three components of the angular velocity vector on the body coordinate system, f s =[f α ,f β ,f μ ] T , f f =[f p ,f q ,f r ] T They are:

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[0142] Among them, C L,α , are the lift coefficient caused by α, and the lift increment coefficients cau...

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Abstract

The invention discloses a coupling-analysis-based attitude coordination control method of a hypersonic flight vehicle. The method comprises step one, carrying out a coupling analysis on a hypersonic flight vehicle attitude system mathematical model; and step two, designing attitude coordination controllers; to be specific, designing an attitude angle coordination controller and an attitude angle rate coordination controller respectively. Therefore, the controllability of the attitude system and the mobility of the hypersonic flight vehicle can be improved and the application effect is good.

Description

technical field [0001] The invention relates to a hypersonic aircraft attitude coordination control method based on coupling analysis, and belongs to the technical field. Background technique [0002] Attitude control is an important part of hypersonic vehicle (HFV) flight control, which plays a primary role in ensuring the stability of HFV and realizing trajectory tracking. However, due to the problems of strong coupling, complex nonlinearity, aerodynamic rudder surface actuation range and engine thrust limitation, and limited load capacity during hypersonic flight, attitude control of hypersonic aircraft poses great challenges. [0003] In recent years, many valuable research results have been obtained in the attitude control of hypersonic vehicles, and these researches mainly focus on three aspects. At first, it was research on the problem of attitude control based on precise mathematical model. Some scholars proposed a nonlinear optimal controller based on Optimal Dyna...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/08G05B13/04
Inventor 王玉惠甄武斌应竣棫吴庆宪
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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