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Developing Conceptual Hypersonic Airbreathing Engines Using Design of Experiments MethodsDesigning a hypersonic vehicle is a complicated process due to the multi-disciplinary synergy that is required. The greatest challenge involves propulsion-airframe integration. In the past, a two-dimensional flowpath was generated based on the engine performance required for a proposed mission. A three-dimensional CAD geometry was produced from the two-dimensional flowpath for aerodynamic analysis, structural design, and packaging. The aerodynamics, engine performance, and mass properties arc inputs to the vehicle performance tool to determine if the mission goals were met. If the mission goals were not met, then a flowpath and vehicle redesign would begin. This design process might have to be performed several times to produce a "closed" vehicle. This paper will describe an attempt to design a hypersonic cruise vehicle propulsion flowpath using a Design of' Experiments method to reduce the resources necessary to produce a conceptual design with fewer iterations of the design cycle. These methods also allow for more flexible mission analysis and incorporation of additional design constraints at any point. A design system was developed using an object-based software package that would quickly generate each flowpath in the study given the values of the geometric independent variables. These flowpath geometries were put into a hypersonic propulsion code and the engine performance was generated. The propulsion results were loaded into statistical software to produce regression equations that were combined with an aerodynamic database to optimize the flowpath at the vehicle performance level. For this example, the design process was executed twice. The first pass was a cursory look at the independent variables selected to determine which variables are the most important and to test all of the inputs to the optimization process. The second cycle is a more in-depth study with more cases and higher order equations representing the design space.
Document ID
20000061968
Acquisition Source
Langley Research Center
Document Type
Preprint (Draft being sent to journal)
Authors
Ferlemann, Shelly M.
(NASA Langley Research Center Hampton, VA United States)
Robinson, Jeffrey S.
(NASA Langley Research Center Hampton, VA United States)
Martin, John G.
(NASA Langley Research Center Hampton, VA United States)
Leonard, Charles P.
(NASA Langley Research Center Hampton, VA United States)
Taylor, Lawrence W.
(NASA Langley Research Center Hampton, VA United States)
Kamhawi, Hilmi
(TechnoSoft, Inc. Hampton, VA United States)
Date Acquired
September 7, 2013
Publication Date
January 1, 2000
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA Paper 2000-2694
Meeting Information
Meeting: Aerodynamic Measurement Technology and Ground Testing
Location: Denver, CO
Country: United States
Start Date: June 19, 2000
End Date: June 22, 2000
Sponsors: American Inst. of Aeronautics and Astronautics
Distribution Limits
Public
Copyright
Public Use Permitted.
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