$UC^{2}AV$ Case Study

Abstract

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.