Conceptual design of a 'SHARP' - CTV

Kinney, David J.; Bowles, Jeffrey V.; Yang, Lily; Roberts, Cathy; Itss, Raytheon

doi:10.2514/6.2001-2887

Cited by 25 publications

(13 citation statements)

References 22 publications

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“…Some high performance entry vehicles include blended wedge designs, such as the SHARP L1, that consist of flat plates, conical frustums, and nose blunting through a cylindrical segment. 16 These examples represent a subset of missions that implement relatively simple vehicle geometries, and Figure 3 illustrates the wide range of applications for these vehicles. The surface geometry of these basic shapes, along with additional complex shapes, can be expressed analytically.…”

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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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 distribution is based on a worst-case estimate of reentry conditions for a winged crew transfer vehicle. 67 The WLE cross-section is a cylinder-wedge configuration with a nose radius of 1 mm, a half angle of 5.6 • and an overall length of the 76.2 mm (3 in.). Fig.…”

Section: Computational Examplementioning

confidence: 99%

Material property requirements for analysis and design of UHTC components in hypersonic applications

Squire

Marschall

2010

Journal of the European Ceramic Society

324

106

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“…Life-cycle analysis includes the evaluation of costs, operations, economics, safety and reliability parameters. The initial step in vehicle performance and sizing was done using one or more of three possible tools: CONSIZ [7] , HAVOC [8] and INTROS [9] . CONSIZ is a weights and sizing code based on empirical weight estimating relationships (WERs).…”

Section: Grlv Iatr Capabilitiesmentioning

confidence: 99%

Multi-Disciplinary Analysis for Future Launch Systems Using NASA's Advanced Engineering Environment (AEE)

Monell

Mathias

Reuther

et al. 2003

16th AIAA Computational Fluid Dynamics Conference

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A new engineering environment constructed for the purposes of analyzing and designing Reusable Launch Vehicles (RLVs) is presented. The new environment has been developed to allow NASA to perform independent analysis and design of emerging RLV architectures and technologies. The new Advanced Engineering Environment (AEE) is both collaborative and distributed. It facilitates integration of the analyses by both vehicle performance disciplines and life-cycle disciplines. Current performance disciplines supported include: weights and sizing, aerodynamics, trajectories, propulsion, structural loads, and CAD-based geometries. Current life-cycle disciplines supported include: DDT&E cost, production costs, operations costs, flight rates, safety and reliability, and system economics. Involving six NASA centers (ARC, LaRC, MSFC, KSC, GRC and JSC), AEE has been tailored to serve as a webaccessed agency-wide source for all of NASA' s future launch vehicle systems engineering functions. Thus, it is configured to facilitate (a) data management, (b) automated tooYprocess integration and execution, and (c) data visualization and presentation. The core components of the integrated framework are a customized PTC Windchill product data management server, a set of RLV analysis and design tools integrated using Phoenix Integration's Model Center, and an =-based data capture and transfer protocol. The AEE system has seen production use during the Initial Architecture and Technology Review for the NASA 2" Generation RLV program, and it continues to undergo development and enhancements in support of its current main customer, the NASA Next Generation Launch Technology (NGLT)program.

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Conceptual design of a 'SHARP' - CTV

Cited by 25 publications

References 22 publications

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

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

Material property requirements for analysis and design of UHTC components in hypersonic applications

Multi-Disciplinary Analysis for Future Launch Systems Using NASA's Advanced Engineering Environment (AEE)

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