Title:
Hypersonic Entry Aeroshell Shape Optimization
Hypersonic Entry Aeroshell Shape Optimization
Author(s)
Theisinger, John E.
Advisor(s)
Braun, Robert D.
Editor(s)
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Abstract
Several different approaches to shape optimization are explored to identify hypersonic
aeroshell shapes that will increase landed mass capability by maximizing drag-area for a
specified lift-to-drag ratio. The most basic approach manipulates standard parameters
associated with analytic aeroshell shapes like the sphere-cone and ellipsled. More general
approaches manipulate the control points of a spline curve or surface. The parametric
polynomial formulations of the Bezier and B-spline curves and surfaces are employed due to
their desirable properties in shape design. Hypersonic aerodynamic analyses are carried out
using Newtonian flow theory panel methods. An integrated optimization environment is
created, and a variety of optimization methods are applied. In addition to a lift-to-drag ratio
constraint, size constraints are imposed on the aeroshell, as determined by payload volume
requirements and launch vehicle shroud size restrictions. Static stability and center-of gravity placement required to achieve hypersonic trim are also considered during
optimization. An example case is presented based on the aeroshell for the Mars Science
Laboratory mission.
Sponsor
Date Issued
2007-12-01
Extent
Resource Type
Text
Resource Subtype
Masters Project
Rights Statement
Unless otherwise noted, all materials are protected under U.S. Copyright Law and all rights are reserved