High-speed aircraft attack angle tracking method adopting force and moment adaptive estimation

The invention relates to a high-speed aircraft attack angle tracking method adopting force and moment adaptive estimation, and belongs to the field of aircraft control. Firstly, an attack angle erroris formed by comparing a measured attack angle of an aircraft with an attack angle instruction, and t...

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Bibliographische Detailangaben
Hauptverfasser: ZHANG PEIFAN, GAO GUANGSHUN, LIN YUN
Format: Patent
Sprache:chi ; eng
Schlagworte:
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Beschreibung
Zusammenfassung:The invention relates to a high-speed aircraft attack angle tracking method adopting force and moment adaptive estimation, and belongs to the field of aircraft control. Firstly, an attack angle erroris formed by comparing a measured attack angle of an aircraft with an attack angle instruction, and then force adaptive compensation, attack angle error feedback and an uncertainty robust item are formed by analyzing a stress model of the aircraft to form an expected value of a pitch angle speed of the aircraft. Then a moment adaptive compensation item, a pitch angle speed error feedback item anda robust control item are formed through aircraft moment analysis to form an expected signal of a pitch rudder deflection angle, and then dynamic characteristics of a rudder system are considered, feedback control is formed through a rudder deflection angle error signal, and a final inversion adaptive attack angle tracking control method is realized. The method has advantages that a layer-by-layerback-stepping design is ri