Rapid Design Space Exploration for Conceptual Design of Hypersonic Missions

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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Section: Ia Motivation For Analytic Hypersonic Aerodynamicsmentioning

confidence: 98%

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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“…35,36 Note that this form also enables a partial recovery of the potential function in the gradient magnitude as shown in Eq. (17). The pitch moment coefficients for the configurations shown in Fig.…”

Section: Application Of the Analytic Curl Calculation To Various mentioning

confidence: 98%

“…More importantly, however, these relations eliminate the large aerodynamic tables that fundamentally segregate aerodynamics from other analyses during conceptual design and enable the construction of a unified, mathematical framework to perform rapid, simultaneous hypersonic aerodynamic and trajectory optimization. 17,18,19 The construction of analytic pitch moment coefficients enables this new, rapid design framework to be expanded to also include longitudinal analysis. For example, packaging considerations could be incorporated into this rapid design environment to identify valid trim angles of attack.…”

Section: Ia Motivation For Analytic Hypersonic Aerodynamicsmentioning

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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“…It is a common methodology used in many different industries and disciplines 14,15 . The major drawback of design space exploration is the large number of evaluations that will be needed to capture the effect of all the design variables.…”

Section: Case Study: Small Business Jet Wing Boxmentioning

confidence: 99%

A Preliminary Study of Wing Substructure Layouts Using a Parametric Structures Evaluation Tool

Potter

Russell

Kim

et al. 2013

54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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Increased demand for improved aircraft performance and efficiency has led to consideration of structural weight reduction and manufacturing cost savings opportunities early in the design cycle. SPANDSET is a toolkit developed to facilitate these goals. By using lower fidelity classical analysis methods it is able to automate preliminary airplane wing box sizing at rapid speeds suitable for design space exploration. A case study illustrates how SPANDSET enables top-down design for a previously existing small business jet wing box structure and resulted in an improved design in terms of weight and cost.

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Rapid Design Space Exploration for Conceptual Design of Hypersonic Missions

Cited by 9 publications

References 26 publications

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

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

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

A Preliminary Study of Wing Substructure Layouts Using a Parametric Structures Evaluation Tool

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