TY - GEN A1 - Grasselt, David A1 - Höschler, Klaus A1 - Kazula, Stefan T1 - A Design Approach for a Coupled Actuator System for Variable Nozzles and Thrust Reverser of Aero Engines T2 - Proceedings of ISABE 2017, ISABE-2017-21450, Manchester, September 3.-8., 2017 Y1 - 2017 UR - https://isabe2017.org/ UR - https://drive.google.com/uc?id=0B0DfCIh2pyLOeXVtazZBcUFEcVE&export=download SP - 11 PB - ISABE ER - TY - GEN A1 - Kazula, Stefan A1 - Grasselt, David A1 - Mischke, Marcel A1 - Höschler, Klaus T1 - Preliminary safety assessment of circular variable nacelle inlet concepts for aero engines in civil aviation T2 - Safety and Reliability – Safe Societies in a Changing World N2 - A safe design process and its application are introduced to a concept study for circular variable aero engine inlets. The paper highlights the tasks of inlets, the compromise in designing them and how using variable inlets could solve this compromise and allow for faster and more efficient commercial aircraft. However, high safety and reliability requirements bring up disadvantages. Tackling these disadvantages, a systems engineering approach is complemented by a safety assessment process, according to Aerospace Recommended Practice ARP 4754A. Safety methods that are applicable during early phases of the product development process are presented and applied to develop feasible variable inlet concepts. Hence, safety requirements, potential failure events and resulting failure modes are systematically identified, assessed and mitigated. The mitigation of a failure condition by the means of redundancy within the adjustment control system is presented. KW - Preliminary System Safety Assessment KW - Fault Tree Analysis KW - Variable Aero Engine Intake Y1 - 2018 UR - https://www.taylorfrancis.com/books/e/9781351174657/chapters/10.1201%2F9781351174664-309 SN - 978-0-8153-8682-7 SP - 2459 EP - 2467 PB - Taylor & Francis Group CY - London ER - TY - GEN A1 - Kazula, Stefan A1 - Höschler, Klaus T1 - Ice detection and protection systems for circular variable nacelle inlet concepts T2 - Deutscher Luft- und Raumfahrtkongress 2018, Friedrichshafen, 4. bis 6. September 2018 N2 - This paper presents the challenge of ice protection within a concept study for variable aero engine inlets in civil aviation. An overview of variable inlet concept groups, ice detection and protection mechanisms is given. These ice protection systems are assigned to the respective inlet concept groups and evaluated regarding economic, functional and safety requirements to determine the most suitable combinations. Y1 - 2018 UR - https://dlrk2018.dglr.de/nc/paper_download/index.html SP - 1 EP - 15 ER - TY - GEN A1 - Rich, Beatrice Monique A1 - Worlitz, Jane A1 - Goldmann, Christine A1 - Schulze, Mathias A1 - Kazula, Stefan A1 - Woll, Ralf T1 - Preparing STEM Students for Leading Positions through Supervising Younger Students T2 - 2018 International Conference on Teaching, Assessment, and Learning for Engineering (TALE), 4-7 December 2018, Wollongong, NSW, Australia N2 - Social and leadership skills are often neglected during studies (especially in STEM subjects). It is precisely these skills that are urgently needed in professional life. The CoMeT “Concepts, Methods and Techniques for Project Management” module was developed to meet the need to acquire social and leadership skills. After a preliminary consideration an overview of the module is given. First, the teaching and learning concept is presented and insights into the seminar work are given. In addition to the competence-oriented examination methods, the integration of digital elements are presented. The continuous further development of the module, adapted to the needs of students and the economy, is a constant goal of the teachers. For this reason, there are already transmission possibilities of the module in planning. Instead of instructing groups of students in project work, pupils are to be introduced to science and study through small projects. Y1 - 2018 UR - https://ieeexplore.ieee.org/document/8615359 SN - 978-1-5386-6522-0 U6 - https://doi.org/10.1109/TALE.2018.8615359 SP - 835 EP - 839 PB - IEEE CY - Piscataway, NJ ER - TY - GEN A1 - Kazula, Stefan A1 - Rich, Beatrice Monique A1 - Höschler, Klaus A1 - Woll, Ralf T1 - Awakening the Interest of High School Pupils in Science, Technology, Engineering and Mathematics Studies and Careers through Scientific Projects T2 - 2018 International Conference on Teaching, Assessment, and Learning for Engineering (TALE), 4-7 December 2018, Wollongong, NSW, Australia N2 - This paper presents the application of a scientific project concerning variable aero engine inlets, which was conducted within the scope of a high school course over the period of two years. The motivation of developing variable aero engine inlets with a group of pupils is introduced. The approach that is utilised during that course and its implementation are described. The results and benefits of this project for pupils, supervisor, school and university are summarised, e.g. providing the pupils with necessary knowledge and assisting them with their career choices, potentially resulting in increased enrolment numbers and lower dropout rates in science, technology, engineering and mathematics study programmes. An overview of a follow-up project that enables a larger group of pupils and a yearly implementation of a similar course is given. Within the scope of that course, university students will supervise smaller scientific projects that are conducted by groups of pupils over the period of one semester, providing additional benefits for students’ soft skills, e.g. communication and conflict management skills. KW - project-based learning KW - increasing interest in STEM KW - reducing dropout rates KW - soft skills KW - cooperation between school and university Y1 - 2018 SN - 978-1-5386-6522-0 U6 - https://doi.org/10.1109/TALE.2018.8615418 SP - 259 EP - 265 PB - IEEE CY - Piscataway, NJ ER - TY - GEN A1 - König, Paul A1 - Mischke, Marcel A1 - Pohl, Michael A1 - Kazula, Stefan A1 - Höschler, Klaus T1 - Concept Development and Evaluation for a Broadband Noise Absorbing Acoustic Liner Concept for Aviation T2 - 24th International Society For Air Breathing Engines (ISABE-2019-24261), 22.-27. September 2019 N2 - This paper presents design adaptations during the further development of innovative broadband acoustic liner concepts (Foil Helmholtz Resonator Liner; FHR-Liners) which utilise flexible foils within a honeycomb structure to attenuate engine and aircraft noise. The requirements for acoustic liners in aviation are described and utilised to derive evaluation criteria. Modifications of the FHR-Liner concept are introduced. A suitable concept evaluation method based on VDI 2225 is applied to evaluate the modified liner concepts concerning the main evaluation criteria. Y1 - 2019 UR - https://2019.isabe.org/content/uploads/ISABE2019_Technical_Program.pdf ER - TY - GEN A1 - Kazula, Stefan A1 - Höschler, Klaus T1 - Ice detection and protection systems for circular variable nacelle inlet concepts T2 - CEAS Aeronautical Journal N2 - 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. KW - Ice protection in aviation KW - Variable aero engine inlet KW - Morphing nacelle intake Y1 - 2020 U6 - https://doi.org/10.1007/s13272-019-00413-1 SN - 1869-5590 VL - 11 IS - 1 SP - 229 EP - 248 ER - TY - GEN A1 - Kazula, Stefan A1 - Wöllner, Mark A1 - Grasselt, David A1 - Höschler, Klaus T1 - Parametric Design Study on Aerodynamic Characteristics of Variable Pitot Inlets for Transonic and Supersonic Civil Aviation T2 - MATEC Web of Conferences : Proceedings of the 9th EASN International Conference on Innovation in Aviation & Space N2 - This paper reveals the influence of selected geometric parameters on the aerodynamic performance of circular variable aero engine inlets in transonic and supersonic civil aviation. The trade-off in inlet design and aerodynamic evaluation parameters are presented. The approach to investigate the dependencies between the aerodynamic and geometric parameters at different flight conditions by means of a parametric design study is introduced. The dependencies of inlet drag and efficiency from geometric parameters at flight speeds of Mach 0.95 up to Mach 1.6 are identified. Although entailing additional weight, the inlet length represents the parameter with the highest potential for drag reduction by up to 50% in the selected design space. Ideal geometries for variable pitot inlets are determined. After considering weight, their potential range benefit nearly disappears for subsonic applications, but remains above 20% for supersonic flight at Mach 1.6. Y1 - 2019 U6 - https://doi.org/10.1051/matecconf/201930402017 SN - 2261-236X VL - 304 ER - TY - GEN A1 - Kazula, Stefan A1 - Mischke, Marcel A1 - König, Paul A1 - Höschler, Klaus T1 - Evaluation of Variable Pitot Inlet Concepts for Transonic and Supersonic Civil Aviation T2 - MATEC Web of Conferences : Proceedings of the 9th EASN International Conference on Innovation in Aviation & Space N2 - This paper describes the selection of the ideal variable inlet concept group by utilising results of aerodynamic investigations, system safety analyses and integration studies. Aerodynamic and functional inlet requirements are explained and variable inlet concept groups are introduced. The concept evaluation by means of a weighted point rating is presented. The respective concept groups are analysed and evaluated regarding economic, functional and safety requirements. By means of this evaluation, the concept group that adjusts the inlet geometry by rigid segment repositioning is identified as most suitable concept group. The early selection of the most suitable concept group enables more detailed subsequent concept investigations, potentially enabling the technology of variable inlets for future commercial aircraft. Y1 - 2019 U6 - https://doi.org/10.1051/matecconf/201930402016 SN - 2261-236X VL - 304 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 - Deutscher Luft- und Raumfahrtkongress 2020, Online, 1. bis 3. September 2020 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 engines 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 analysed. These analyses emphasis challenges of existing solution options concerning design methodologies, level of detail and experience with a technology. Y1 - 2020 UR - https://dlrk2020.dglr.de/programmheft/index.html ER - TY - GEN A1 - Kazula, Stefan A1 - Rich, Beatrice Monique A1 - Höschler, Klaus A1 - Woll, Ralf T1 - Interest High School Students in STEM Studies, while Preparing STEM Students for Leading Positions T2 - 2021 IEEE Global Engineering Education Conference Y1 - 2021 SN - 978-1-7281-8478-4 SN - 978-1-7281-8479-1 U6 - https://doi.org/10.1109/EDUCON46332.2021.9454011 VL - 2021 SP - 910 EP - 914 ER - TY - CHAP A1 - Mischke, Marcel A1 - Kazula, Stefan A1 - Höschler, Klaus T1 - A Comparative Concept Study and Evaluation for New Broadband Noise Absorbing Acoustic Liner Concepts for Civil Aviation T2 - Proceedings of Global Power and Propulsion Society, Technical Conference 2019, Zurich N2 - This paper presents an approach to product rating and evaluation of different product solutions for broadband attenuation acoustic liner concepts for aerospace application. In the process, corresponding requirements have been defined for the considered system and evaluation criteria have been derived. Three “Main Evaluation Categories” (Acoustics, System Safety and Integration, Structure and Material) have been introduced to not falsify the assessment results by subject-specific exclusion criteria. A ranked space method has been selected for weighting the evaluation criteria to ensure an objective and knowledge-based rating. The rating has been carried out by a weighted point rating. Concise operational requirements and previously not considered system functions have been identified and linked to the rating and evaluation process. Building on this, further steps for the optimisation and development of the acoustic liner concepts have been presented and explained. KW - Concept Evaluation KW - Concept Rating KW - Acoustic Liner KW - Broadband Attenuation Y1 - 2019 UR - https://gpps.global/proceedings/gpps-zurich19-proceedings/108-zu19-ducts-nozzels/268-gpps-z-2019-46.html SP - 1 EP - 9 ER - TY - CHAP A1 - Kazula, Stefan A1 - Grasselt, David A1 - Höschler, Klaus ED - Silva Gomes, J. F. ED - Meguid, Shaker A. T1 - Common cause analysis of circular variable nacelle inlet concepts for aero engines in civil aviation T2 - Proceedings IRF2018: 6th International Conference Integrity-Reliability-Failure, Lisbon/Portugal, 22-26 July 2018 N2 - This paper presents the application of a safe design process within a concept study for variable aero engine inlets. The safety assessment method Common Cause Analysis (CCA), consisting of a Zonal Safety Analysis (ZSA), a Particular Risk Analysis (PRA) and a Common Mode Analysis (CMA), is performed on variable inlet concepts. By the means of the CCA individual failure modes and external events, which can lead to failure conditions, are identified. Potential design adaptations to mitigate these failure conditions are presented. KW - variable aero engine inlets KW - coupled design and safety process KW - safety and reliability KW - safety assessment methods Y1 - 2018 UR - https://paginas.fe.up.pt/~irf/Proceedings_IRF2018/data/papers/7148.pdf SN - 978-989-20-8313-1 SP - 759 EP - 770 PB - INEGI/FEUP CY - Lisbon ER - TY - CHAP A1 - Kazula, Stefan A1 - Höschler, Klaus T1 - A Systems Engineering Approach to Variable Intakes for Civil Aviation T2 - 7th European Conference for Aero Nautics and Space Sciences (EUCASS), Milan (Italien), 2017 N2 - A systems engineering approach to develop variable nacelle intakes for aero engines in civil aviation is presented. The goal of this methodical approach is to find solutions to design problems that can be successfully utilised in aviation without further effort during the certification. By using variable intakes, aircraft and aero engine manufacturers can fulfil their customers’ needs for safe, efficient and fast travelling. Therefore, a system shall be installed which is able to modify the nacelle intake contour between two extrema. On the one hand, a sharp thin contour, which produces low drag and allows to fly faster or more efficiently, is optimal during cruise condition. On the other hand, a round thick intake lip is necessary to avoid flow separations with the potential to cause dangerous events during take-off and climb conditions. The utilised systems engineering approach is introduced. The executed steps and methods used for creating and evaluating concept variants for variable intakes are displayed particularly. Those contain the determination and evaluation of requirements and functions, as well as the generation and assessment of concepts. Finally yet importantly, following tasks are presented. KW - Variable nacelle intake KW - Adaptive aero engine inlet KW - Systems engineering (SE) KW - Safe design process KW - Design methods Y1 - 2017 UR - https://www.eucass.eu/doi/EUCASS2017-020.pdf U6 - https://doi.org/10.13009/EUCASS2017-20 ER - TY - THES A1 - Kazula, Stefan T1 - Variable Pitot-Triebwerkseinlässe für kommerzielle Überschallflugzeuge - Konzeptstudie mittels eines Entwicklungsansatzes für sichere Produkte KW - Variable Pitot-Triebwerkseinlässe Y1 - 2021 SN - 978-3-658-35455-8 SN - 978-3-658-35456-5 U6 - https://doi.org/10.1007/978-3-658-35456-5 PB - Springer Vieweg CY - Wiesbaden ER - TY - GEN A1 - Kazula, Stefan A1 - Höschler, Klaus T1 - Sustainable Supersonic Transport: a Case Study on Variable Pitot Inlets T2 - 9th European Conference for Aeronautics and Space Sciences (Eucass) Y1 - 2022 UR - https://www.eucass.eu/conferences-and-publications/search-on-this-website?searchword=Sustainable%20Supersonic%20Transport:%20a%20Case%20Study&searchphrase=all&limit=20 U6 - https://doi.org/10.13009/EUCASS2022-4600 ER - TY - GEN A1 - Kazula, Stefan A1 - Wöllner, Mark A1 - Höschler, Klaus T1 - Identification of efficient geometries for variable pitot inlets for supersonic transport T2 - Aircraft Engineering and Aerospace Technology N2 - Purpose – This paper aims to reveal the influence of selected geometric parameters on the aerodynamic performance of circular variable aero engine inlets in transonic and supersonic civil aviation. Design/methodology/approach – The trade-off in inlet design and aerodynamic evaluation parameters is presented. The approach to investigate the dependencies between the aerodynamic and geometric parameters at different flight conditions by means of a parametric design study is introduced. Findings – The dependencies of inlet drag and efficiency from geometric parameters at flight speeds of Mach 0.95 up to Mach 1.6 are identified. Although entailing additional weight, the inlet length represents the parameter with the highest potential for drag reduction by up to 50% in the selected design space. Ideal geometries for variable pitot inlets are determined. After considering weight, their potential range benefit nearly disappears for subsonic applications, but remains above 20% for supersonic flight at Mach 1.6. Originality/value – Hence, the technology of circular variable pitot inlets for supersonic transport aircraft could be a way to achieve the ambitious ecological, safety and economic goals for future civil aviation. KW - Benefit of supersonic variable axisymmetric pitot inlets KW - Supersonic transport (SST) KW - Ideal aircraft intake geometries KW - Pitot inlet drag estimation Y1 - 2020 U6 - https://doi.org/10.1108/AEAT-11-2019-0228 SN - 0002-2667 VL - 92 IS - 7 SP - 981 EP - 992 ER - TY - GEN A1 - Kazula, Stefan A1 - Höschler, Klaus T1 - Evaluation of variable pitot inlet concepts for transonic and supersonic civil aviation T2 - Aircraft Engineering and Aerospace Technology N2 - Purpose – This paper aims to describe the selection of the ideal variable inlet concept group by using results of aerodynamic investigations, system safety analyses and integration studies. Design/methodology/approach – Aerodynamic and functional inlet requirements are explained and variable inlet concept groups are introduced. The concept evaluation by means of a weighted point rating is presented. The respective concept groups are analysed and evaluated regarding economic, functional and safety requirements. Findings – By means of this evaluation, the concept group that adjusts the inlet geometry by rigid segment repositioning is identified as most suitable concept group. Originality/value – The early selection of the most suitable concept group enables more detailed subsequent concept investigations, potentially enabling the technology of variable inlets for future commercial aircraft. KW - Design evaluation KW - Variable aero engine inlet KW - Morphing nacelle intake Y1 - 2020 U6 - https://doi.org/10.1108/AEAT-11-2019-0225 SN - 0002-2667 VL - 92 IS - 6 SP - 807 EP - 815 ER - TY - GEN A1 - Kazula, Stefan A1 - Höschler, Klaus T1 - A Variable Pitot-Inlet Concept for Supersonic Aviation T2 - Global Power & Propulsion Society GPPS Chania20, Online, 7th - 9th September 2020 N2 - An overview of aero-engine inlets, the design process in aviation and a safe design approach for academic studies is provided. By means of a safe design approach, a variable inlet concept is developed up to technology readiness level (TRL) 3 and described. The application of safety and reliability methods, aerodynamic and structural analyses, as well as functional demonstrators proves the feasibility of the present variable inlet concept and highlights its potential for application in future supersonic transport (SST). Y1 - 2020 U6 - https://doi.org/10.33737/gpps20-tc-49 SN - 2504-4400 ER - TY - GEN A1 - Kazula, Stefan A1 - Höschler, Klaus T1 - A systems engineering approach to variable intakes for civil aviation T2 - Proceedings of the Institution of Mechanical Engineers. Part G, Journal of Aerospace Engineering N2 - A systems engineering approach to develop variable nacelle intakes for aero engines in civil aviation is presented. The goal of this methodical approach is to find solutions to design problems that can be successfully utilised in aviation without further effort during the certification. By using variable intakes, aircraft and aero engine manufacturers can fulfil their customers’ needs for safe, efficient and fast travelling. Therefore, a system shall be installed which is able to modify the nacelle intake contour between two extrema. On the one hand, a sharp thin contour, which produces low drag and allows to fly faster or more efficiently, is optimal during cruise condition. On the other hand, a round thick intake lip is necessary to avoid flow separations with the potential to cause dangerous events during take-off and climb conditions. The utilised systems engineering approach is introduced. The executed steps and methods used for creating and evaluating concept variants for variable intakes are displayed particularly. Those contain the determination and evaluation of requirements and functions as well as the generation and assessment of concepts. Finally, yet importantly, following tasks are presented. KW - adaptive nacelle inlet KW - aero engine nacelle KW - morphing nacelle inlet KW - morphological box KW - safe design approach KW - safe design in civil aviation KW - systems engineering approach KW - variable inlet KW - variable intake Y1 - 2019 UR - https://journals.sagepub.com/doi/10.1177/0954410019836903 U6 - https://doi.org/10.1177/0954410019836903 SN - 2041-3025 VL - 234(2020) IS - 10 SP - 1721 EP - 1729 ER - 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 -