\(UC^{2}AV\) Case Study

  • Michail G. MichailidisEmail author
  • Kimon P. Valavanis
  • Matthew J. Rutherford
Part of the Springer Tracts in Autonomous Systems book series (STRAUS, volume 1)


The proposed controller design framework has been validated for stability and navigational control of the \(UC^{2}AV\). For CC to be implemented on the \(UC^{2}AV\), a forward impeller centrifugal compressor is used, located in the fuselage and called Air Supply Unit (ASU), while an Air Delivery System (ADS) integrated with a plenum is capable of distributing air uniformly across the wingspan [1]. CC is applied through the ASU by regulating the RPM of the centrifugal compressor. For future missions and scenarios, the RPM of the ASU will need to be optimally controlled (CC-on-demand) with respect to power consumption or mission performance, to complete a variety of tasks. As a result, the RPM of the centrifugal compressor ranges between 0 and maximum (28,000) according to the ongoing mission. Different RPM will generate different values for the aerodynamic coefficients of the \(UC^{2}AV\), which will, in turn, generate different \(UC^{2}AV\) flight dynamics. Therefore, the actual \(UC^{2}AV\) flight dynamics are explicitly described by a family of models or by model uncertainty mainly stemming from the aerodynamic coefficients, with predefined upper and lower bounds.


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Copyright information

© Springer Nature Switzerland AG 2020

Authors and Affiliations

  • Michail G. Michailidis
    • 1
    Email author
  • Kimon P. Valavanis
    • 1
  • Matthew J. Rutherford
    • 1
  1. 1.Ritchie School of Engineering and Computer Science, Electrical and Computer EngineeringUniversity of DenverDenverUSA

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