CEAS Aeronautical Journal

, Volume 11, Issue 1, pp 229–248 | Cite as

Ice detection and protection systems for circular variable nacelle inlet concepts

  • S. KazulaEmail author
  • K. Höschler
Original Paper


This paper presents the challenge of ice protection within a concept study for variable pitot inlets of aero engines in transonic and supersonic civil aviation. An overview of variable inlet concept groups that adjust the inlet geometry by rigid segment repositioning, elastic surface deformation, or boundary layer control is given. Ice detection mechanisms and various pneumatic, fluid, as well as electric ice protection systems are presented. These ice protection systems are assigned to the respective inlet concept groups and evaluated regarding economic, functional, and safety requirements by means of pairwise comparison and weighted point rating to determine the most suitable combinations.


Ice protection in aviation Variable aero engine inlet Morphing nacelle intake 



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Copyright information

© Deutsches Zentrum für Luft- und Raumfahrt e.V. 2019

Authors and Affiliations

  1. 1.Chair of Aero Engine DesignBrandenburg University of TechnologyCottbusGermany

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