TY - GEN A1 - Mischke, Marcel A1 - Kazula, Stefan A1 - Höschler, Klaus T1 - Preliminary Safety Assessment on System Design Level for Broadband Acoustic Liner Concepts for Aviation T2 - Proceedings of the 9th EASN International Conference on Innovation in Aviation & Space N2 - Selected methods of the aviation safety assessment process according to ARP 4761 are introduced and conducted within the scope of a concept study for future broadband acoustic liners. While having similar primary functions and basic design, the acoustic liner concepts diverge concerning subfunctions and potential malfunctions. With the ARP 4761 safety assessment methods, significant differences in sub functions and possible malfunctions of the concepts can be identified. The results of the safety assessment are discussed, and the concepts are evaluated in terms of feasibility and safety. Y1 - 2019 UR - https://www.matec-conferences.org/articles/matecconf/abs/2019/53/matecconf_easn2019_04010/matecconf_easn2019_04010.html U6 - https://doi.org/10.1051/matecconf/201930404010 CY - Athen ER - TY - GEN A1 - Kazula, Stefan A1 - Wöllner, Mark A1 - Grasselt, David A1 - Höschler, Klaus T1 - Ideal Geometries and Potential Benefit of Variable Pitot Inlets for Subsonic and Supersonic Business Aviation T2 - 8TH EUROPEAN CONFERENCE FOR AERONAUTICS AND SPACE SCIENCES (EUCASS) N2 - The challenge of determining ideal inlet geometries for variable pitot aero engine inlets in transonic and supersonic civil aviation is presented. The trade-off in inlet design and the geometric inlet parameters are introduced. By means of a parametric design study, feasible inlet geometries for variable inlets are identified and the potential aerodynamic benefit of using variable pitot inlets for flight speeds from Mach 0.95, 1.3 up to 1.6 is examined. After considering the additional weight of variable inlets, for instance due to required actuators, a remaining range benefit of over 20% at a flight speed of Mach 1.6 is determined. Y1 - 2019 UR - https://eucass.eu/index.php/component/docindexer/?task=download&id=5871 U6 - https://doi.org/10.13009/EUCASS2019-314 ER - TY - GEN A1 - Kazula, Stefan A1 - Wöllner, Mark A1 - Grasselt, David A1 - Höschler, Klaus T1 - Parametric design and aerodynamic analysis of circular variable aero engine inlets for transonic and supersonic civil aviation T2 - Proceedings of the 24th ISABE Conference : ISABE 2019-24018 N2 - This paper focusses on the challenge of determining the ideal inlet geometries within a concept study for variable pitot aero engine inlets in transonic and supersonic civil aviation. The trade-off in inlet design and the geometric parameters of inlets for different Mach numbers are introduced. The utilised process of the parametric design study and its implementation are presented. The dependencies of inlet drag and occurrence of flow separation from geometric parameters are examined. The ideal inlet geometries are identified to determine the potential aerodynamic benefit of using variable pitot inlets. The comparison of the identified geometries with the reference reveals a significant drag reduction at the investigated flight speeds of Mach 0.95, 1.3 and 1.6. While the drag reduction potentially leads to decreased fuel consumption and increased flight range, the application of variable inlet systems entails additional weight and complexity. By means of a simplified Breguet range equation, the benefit of using variable pitot inlets has been determined. For an additional weight of 500 kg per variable inlet, the range benefit nearly disappears for subsonic applications up to Mach 0.95, while a range benefit of over 20% remains for supersonic applications at Mach 1.6. KW - benefit of supersonic variable axisymmetric pitot inlets KW - parametric design study KW - response surface optimisation KW - pitot inlet drag estimation KW - ideal aircraft intake geometries Y1 - 2019 UR - https://drive.google.com/drive/folders/1PZaMaLOLsybB3KFLmvP8hwM_lwmk3e4B CY - Canberra ER - TY - GEN A1 - Kazula, Stefan A1 - Höschler, Klaus T1 - Review of variable leading-edge patents for aircraft wings and engine inlets and their relevance for variable pitot inlets in future supersonic transport T2 - CEAS Aeronautical Journal N2 - The motivation for designing variable pitot inlets for future supersonic transport (SST) is explained. A comprehensive overview of existing technological solutions for variable leading edges of aircraft wings and engine inlets is given. The advantages and limitations of over 80 solutions, as well as their relevance for application on variable pitot inlets for SST are described. The challenges of existing solution options concerning design methodologies, level of detail, and experience with a technology are identified. KW - Overview of variable inlet lips KW - Variable aero engine inlet KW - Morphing nacelle intake KW - SST Y1 - 2021 U6 - https://doi.org/10.1007/s13272-021-00520-y SN - 1869-5582 SN - 1869-5590 VL - 12 IS - 3 SP - 685 EP - 700 ER -