Multi-Objective Hypersonic Entry Aeroshell Shape Optimization

Theisinger, John E.; Braun, Robert D.

doi:10.2514/1.41136

Cited by 29 publications

(13 citation statements)

References 9 publications

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“…Although such methods are obviously highly simplified, reasonable results can be obtained by using them. Due to this combination of simplicity and reasonable validity, this type of method finds wide use in conceptual design [7][8][9][10][11] and are very well suited to use in conceptual design optimization. The long heritage has also made them well documented.…”

Section: Iiia Local Inclination Methodsmentioning

confidence: 99%

Continuous Aerodynamic Modelling of Entry Shapes

Dirkx¹,

Mooij²

2011

AIAA Atmospheric Flight Mechanics Conference

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During the conceptual design phase of a re-entry vehicle, the vehicle shape can be varied and its impact on performance evaluated. To this end, the continuous modeling of the aerodynamic characteristics as a function of the shape is useful in exploring the full design space. Local inclination methods for aerodynamic analysis have proven sufficiently accurate for use at such a design stage, but manual selection of methods over the vehicle is inefficient for the exploration of a large number of design possibilities. This paper describes the model of an aerodynamic analysis code, written for use in conceptual vehicle shape optimization, which includes an automatic method selection algorithm. Panel shielding is also included in the analysis code to allow for the analysis of more complex geometries. The models used for the shape and aerodynamics are described and results for the Space Shuttle and Apollo are compared to wind tunnel data. They show an accuracy of better than 15% for most cases, which is sufficient for the use in conceptual design. Panel shielding is shown to be important in the prediction of control derivatives at low angle of attack, as well as the prediction of lateral stability derivatives. Finally, a simple guidance algorithm is used to assess the impact of the errors in the aerodynamic coefficients on the vehicle heat load and ground track length. Both show discrepancies of less than 10%.

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Section: Iiia Local Inclination Methodsmentioning

confidence: 99%

Continuous Aerodynamic Modelling of Entry Shapes

Dirkx¹,

Mooij²

2011

AIAA Atmospheric Flight Mechanics Conference

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“…7,8,9,22,23,24,25,26 This can be observed by the many recent shape design studies that employ panel methods. 27,28 Recent advances in symbolic manipulation tools, such as Mathematica 29 and Maple, 30 enable the modern construction of analytic relations for various shapes. These symbolic tools are capable of querying large databases of integral tables and substitution techniques, addressing some of the limitations that have historically prevented the adoption of analytic methods.…”

Section: Ib Absence Of Analytic Aerodynamics In Present-day Analysesmentioning

confidence: 99%

The Construction of Analytic Hypersonic Pitch Moment Coefficients Using a Curl Transformation

Grant

2013

51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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This study investigates the creation of analytic hypersonic pitch moment coefficients by converting the traditional Newtonian surface integration into a mathematically equivalent curl calculation. This manipulation enables analytic pitch moment coefficients to be derived for shapes of increasing complexity. The analytic solutions are obtained by converting the physical moment calculation across the unshadowed surface to an equivalent volumetric curl calculation of a mathematical vector field that is directed away from the center of gravity location. This capability is made possible by the analytic expression of the Newtonian moment calculation and is not available in present-day studies that rely on approximate panel methods. The results of this investigation enable the construction of analytic relations for new hypersonic configurations of interest, and this approach serves as the foundation to construct efficient hybrid exact-approximate solutions for more complex configurations. A state-of-the-art hypersonic design tool validates all of the analytic relations developed in this investigation. The rapid longitudinal analysis made possible by the analytic pitch moment relations enable packaging considerations and trim control surface deflections to be incorporated into conceptual design studies.

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“…7,8,9,19,20,21,22,23 This can be observed by the many recent shape design studies that employ panel methods. 24,25 Recent advances in symbolic manipulations tools, such as Mathematica 26 and Maple, 27 enable the modern construction of analytic relations for various shapes. These symbolic tools are capable of querying large databases of integral tables and substitution techniques, addressing some of the limitations that have historically prevented the adoption of analytic methods.…”

Section: Ib Absence Of Analytic Aerodynamics In Present-day Analysesmentioning

confidence: 99%

The Extension of Analytic Hypersonic Force Coefficients for Conceptual Design Using the Divergence Theorem

Grant

Braun

2012

AIAA Atmospheric Flight Mechanics Conference

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This study investigates the type and performance of analytic Newtonian aerodynamic solutions made possible using the Divergence Theorem. A reformulation of the Newtonian surface pressure calculation enables a mathematically equivalent divergence calculation to be performed as a substitute. This manipulation enables analytic force coefficients to be derived for shapes of increasing complexity while also reducing computational cost when compared to existing analytic solutions. The divergence solutions are obtained by converting the physical flow field into a mathematical flow field that is constant in direction but with magnitude that is equivalent to the Newtonian pressure coefficient. This unique property allows various mathematical techniques that are not available with the traditional Newtonian calculation to be performed that further reduce computational cost. The results of this investigation enable the construction of analytic relations for new hypersonic configurations of interest, and this approach serves as the foundation to construct efficient hybrid exact-approximate solutions for more complex configurations. Comparisons of the current analytic database to a state-of-the-art hypersonic design tool illustrate the computational advantages of the analytic relations to support hypersonic conceptual design.

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Multi-Objective Hypersonic Entry Aeroshell Shape Optimization

Cited by 29 publications

References 9 publications

Continuous Aerodynamic Modelling of Entry Shapes

Continuous Aerodynamic Modelling of Entry Shapes

The Construction of Analytic Hypersonic Pitch Moment Coefficients Using a Curl Transformation

The Extension of Analytic Hypersonic Force Coefficients for Conceptual Design Using the Divergence Theorem

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