Decoupling flight control synthesis to helicopter in hover condition with unstructured uncertainty

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Abstract

This paper presents a synthesis of the decoupling compensator for multiinput multioutput systems with considerations of the robust stabilization. The restriction of constant pole number for a controlled plant with uncertainty from small gain theorem is relaxed as the robustness is considered. Both the nominal plant and the uncertain plant with varying numbers of right half plane poles could be stabilized internally and simultaneously after decoupling. The two-parameter compensator is also employed with output feedback. Furthermore, the H sub-optimal compensator can be achieved with the robust criterion of the normalized coprime factor plant. The robust bound of the system with the synthesized compensator is also evaluated. Furthermore, all the necessary state space formulae of the robust-decoupling compensator are provided. This approach will be applied to a rotorcraft flight control in hover condition. The decouple objective is achieved with internal stability. The robustness of the system is also conserved even in the severe conditions, plant with different RHP pole number with the uncertainties. The simulation illustrates the results that are inspired by the compensator synthesized in this paper.

Original languageEnglish
Pages (from-to)57-70
Number of pages14
JournalHangkong Taikong ji Minhang Xuekan/Journal of Aeronautics, Astronautics and Aviation
Volume39 A
Issue number1
Publication statusPublished - 2007 Mar 1

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flight control
helicopters
compensators
Helicopters
decoupling
Poles
flight
synthesis
poles
Stabilization
rotary wing aircraft
Feedback
half planes
stabilization
Uncertainty
constrictions
theorems
output
simulation

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Space and Planetary Science

Cite this

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title = "Decoupling flight control synthesis to helicopter in hover condition with unstructured uncertainty",
abstract = "This paper presents a synthesis of the decoupling compensator for multiinput multioutput systems with considerations of the robust stabilization. The restriction of constant pole number for a controlled plant with uncertainty from small gain theorem is relaxed as the robustness is considered. Both the nominal plant and the uncertain plant with varying numbers of right half plane poles could be stabilized internally and simultaneously after decoupling. The two-parameter compensator is also employed with output feedback. Furthermore, the H∞ sub-optimal compensator can be achieved with the robust criterion of the normalized coprime factor plant. The robust bound of the system with the synthesized compensator is also evaluated. Furthermore, all the necessary state space formulae of the robust-decoupling compensator are provided. This approach will be applied to a rotorcraft flight control in hover condition. The decouple objective is achieved with internal stability. The robustness of the system is also conserved even in the severe conditions, plant with different RHP pole number with the uncertainties. The simulation illustrates the results that are inspired by the compensator synthesized in this paper.",
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N2 - This paper presents a synthesis of the decoupling compensator for multiinput multioutput systems with considerations of the robust stabilization. The restriction of constant pole number for a controlled plant with uncertainty from small gain theorem is relaxed as the robustness is considered. Both the nominal plant and the uncertain plant with varying numbers of right half plane poles could be stabilized internally and simultaneously after decoupling. The two-parameter compensator is also employed with output feedback. Furthermore, the H∞ sub-optimal compensator can be achieved with the robust criterion of the normalized coprime factor plant. The robust bound of the system with the synthesized compensator is also evaluated. Furthermore, all the necessary state space formulae of the robust-decoupling compensator are provided. This approach will be applied to a rotorcraft flight control in hover condition. The decouple objective is achieved with internal stability. The robustness of the system is also conserved even in the severe conditions, plant with different RHP pole number with the uncertainties. The simulation illustrates the results that are inspired by the compensator synthesized in this paper.

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