Title :
Nonlinear modelling and adative backstepping control design for one hypersonic aircraft
Author :
Chen Jie ; Pan Changpeng ; Wu Jinhua
Author_Institution :
Naval Aeronaut. & Astronaut. Univ., Yantai, China
Abstract :
A six degree-of-freedom nonlinear model of the near space hypersonic aircraft is founded and modified according to the series of literatures of Winged-Cone offered by America NASA Langly Lab. Presented model can meet the demand of strongly nonlinear, highly coupled, rapidly time variation, and be applied to theory study and simulate validation of hypersonic aircraft control system. Adative backstepping control to design the nonlinear control system.
Keywords :
adaptive control; aircraft control; control system synthesis; nonlinear control systems; adaptive backstepping control design; near space hypersonic aircraft control system; nonlinear control system; six degree-of-freedom nonlinear model; Aerospace control; Aircraft; Aircraft navigation; Atmospheric modeling; Backstepping; NASA; Vehicle dynamics; A six degree-of-free domnonlinear model; Adative backstepping control; Hypersonic Aircraft; highly coupled;
Conference_Titel :
Control and Decision Conference (CCDC), 2011 Chinese
Conference_Location :
Mianyang
Print_ISBN :
978-1-4244-8737-0
DOI :
10.1109/CCDC.2011.5968180
