The Experts below are selected from a list of 198 Experts worldwide ranked by ideXlab platform

Carlos Ilario Da Silva - One of the best experts on this subject based on the ideXlab platform.

  • flight path and wing optimization of lithium air battery powered passenger Aircraft
    53rd AIAA Aerospace Sciences Meeting, 2015
    Co-Authors: Julius M Vegh, Juan J Alonso, Tarik H Orra, Carlos Ilario Da Silva
    Abstract:

    The design of electric-powered Aircraft for use in the commercial aviation sector is a complex, heavily multidisciplinary problem that requires careful consideration of power and energy tradeoffs, in addition to more traditional performance metrics. A multidisciplinary, multifidelity Aircraft design code called SUAVE (Stanford University Aerospace Vehicle Environment) has been developed in part to address these considerations. This paper explores the application of this design code towards a passenger Aircraft at the commercial scale, with the wing, flight path, and an electric propulsion system designed and optimized for a prescribed number of passengers at a variety of different ranges. Additionally, Aircraft Weight sensitivities to battery technology, motor technology, as well as takeoff and landing constraints were evaluated, and their relative feasibility assessed.

Julius M Vegh - One of the best experts on this subject based on the ideXlab platform.

  • flight path and wing optimization of lithium air battery powered passenger Aircraft
    53rd AIAA Aerospace Sciences Meeting, 2015
    Co-Authors: Julius M Vegh, Juan J Alonso, Tarik H Orra, Carlos Ilario Da Silva
    Abstract:

    The design of electric-powered Aircraft for use in the commercial aviation sector is a complex, heavily multidisciplinary problem that requires careful consideration of power and energy tradeoffs, in addition to more traditional performance metrics. A multidisciplinary, multifidelity Aircraft design code called SUAVE (Stanford University Aerospace Vehicle Environment) has been developed in part to address these considerations. This paper explores the application of this design code towards a passenger Aircraft at the commercial scale, with the wing, flight path, and an electric propulsion system designed and optimized for a prescribed number of passengers at a variety of different ranges. Additionally, Aircraft Weight sensitivities to battery technology, motor technology, as well as takeoff and landing constraints were evaluated, and their relative feasibility assessed.

Juan J Alonso - One of the best experts on this subject based on the ideXlab platform.

  • flight path and wing optimization of lithium air battery powered passenger Aircraft
    53rd AIAA Aerospace Sciences Meeting, 2015
    Co-Authors: Julius M Vegh, Juan J Alonso, Tarik H Orra, Carlos Ilario Da Silva
    Abstract:

    The design of electric-powered Aircraft for use in the commercial aviation sector is a complex, heavily multidisciplinary problem that requires careful consideration of power and energy tradeoffs, in addition to more traditional performance metrics. A multidisciplinary, multifidelity Aircraft design code called SUAVE (Stanford University Aerospace Vehicle Environment) has been developed in part to address these considerations. This paper explores the application of this design code towards a passenger Aircraft at the commercial scale, with the wing, flight path, and an electric propulsion system designed and optimized for a prescribed number of passengers at a variety of different ranges. Additionally, Aircraft Weight sensitivities to battery technology, motor technology, as well as takeoff and landing constraints were evaluated, and their relative feasibility assessed.

Tarik H Orra - One of the best experts on this subject based on the ideXlab platform.

  • flight path and wing optimization of lithium air battery powered passenger Aircraft
    53rd AIAA Aerospace Sciences Meeting, 2015
    Co-Authors: Julius M Vegh, Juan J Alonso, Tarik H Orra, Carlos Ilario Da Silva
    Abstract:

    The design of electric-powered Aircraft for use in the commercial aviation sector is a complex, heavily multidisciplinary problem that requires careful consideration of power and energy tradeoffs, in addition to more traditional performance metrics. A multidisciplinary, multifidelity Aircraft design code called SUAVE (Stanford University Aerospace Vehicle Environment) has been developed in part to address these considerations. This paper explores the application of this design code towards a passenger Aircraft at the commercial scale, with the wing, flight path, and an electric propulsion system designed and optimized for a prescribed number of passengers at a variety of different ranges. Additionally, Aircraft Weight sensitivities to battery technology, motor technology, as well as takeoff and landing constraints were evaluated, and their relative feasibility assessed.

Gabriel Pinho Chiozzotto - One of the best experts on this subject based on the ideXlab platform.

  • initial Weight estimate of advanced transport Aircraft concepts considering aeroelastic effects
    55th AIAA Aerospace Sciences Meeting, 2017
    Co-Authors: Gabriel Pinho Chiozzotto
    Abstract:

    This paper presents a semi-empirical method for the Weight estimation of advanced transport Aircraft concepts in early design stages. The Aircraft Weight is estimated according to four component groups with different sizing drivers. Emphasis is placed on the wing Weight estimation considering aeroelastic effects. A physics-based wing Weight estimation tool is used in a Design of Experiments and the results are applied in a least-squares regression obtaining wing Weight Estimating Relationships (WERs). Typical parameters covering a wide design space are considered so the method is applicable to business jets, regional turboprops, short-range and long-range transport Aircraft. The WERs equations are presented in typical handbook form for simple application. Static aeroelastic loads, aileron efficiency and aeroelastic divergence effects on the wing Weight are considered. Equations are presented for conventional transport Aircraft, forward swept wing, strut-braced wing, and forward-swept strut-braced wing concepts. The WERs are applicable to aluminum or carbon-fiber reinforced plastic wings. The equations are verified for accuracy with available designs and the sensitivities are checked against the Weights tool used to generate them. Application of the method in a simple design study illustrates its usefulness in quickly assessing different concepts for a set of requirements.