Morphing Concept for Quiet Supersonic Jet Boom Mitigation

Simmons, Frank; Freund, Donald

doi:10.2514/6.2005-1015

Cited by 21 publications

(9 citation statements)

References 2 publications

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“…Wind tunnel testing and CFD show the potential of the approach. Further work 60 investigates the engineering aspects of integrating the nose spike. Work reports on proposed extension and retraction mechanisms and drive systems, prototype hardware and ground tests.…”

Section: Extendable Nose Spikementioning

confidence: 99%

Innovation in supersonic passenger air travel

Smith

2012

Innovation in Aeronautics

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Section: Extendable Nose Spikementioning

confidence: 99%

Innovation in supersonic passenger air travel

Smith

2012

Innovation in Aeronautics

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“…The MDL and bootstrap technique were applied to experimental flight-test data from the F-15B Quiet Spike project by Gulfstream Aerospace Corporation (Savannah, Georgia) and NASA Dryden Flight Research Center [10][11][12]. The data analyzed for this study used the structural accelerometer response output of the Quiet Spike boom tip when fully extended.…”

Section: Experimental F-15b Quiet Spike Datamentioning

confidence: 99%

“…The data analyzed in this study are from the F-15B Quiet Spike TM flight-test program, which was a collaborative effort between Gulfstream Aerospace Corporation (Savannah, Georgia) and NASA Dryden Flight Research Center [10][11][12]. The results show that 1) Linear models are inefficient for modeling aeroservoelastic data.…”

mentioning

confidence: 94%

Structure Computation of Quiet Spike Flight-Test Data During Envelope Expansion

Kukreja

2008

Journal of Aircraft

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System identification or mathematical modeling is used in the aerospace community for development of simulation models for robust control law design. These models are often described as linear time-invariant processes. Nevertheless, it is well known that the underlying process is often nonlinear. The reason for using a linear approach has been due to the lack of a proper set of tools for the identification of nonlinear systems. Over the past several decades, the controls and biomedical communities have made great advances in developing tools for the identification of nonlinear systems. These approaches are robust and readily applicable to aerospace systems. In this paper, we show the application of one such nonlinear system identification technique, structure detection, for the analysis of F-15B Quiet Spike TM aeroservoelastic flight-test data. Structure detection is concerned with the selection of a subset of candidate terms that best describe the observed output. This is a necessary procedure to compute an efficient system description that may afford greater insight into the functionality of the system or a simpler controller design. Structure computation as a tool for black-box modeling may be of critical importance for the development of robust parsimonious models for the flight-test community. Moreover, this approach may lead to efficient strategies for rapid envelope expansion, which may save significant development time and costs. The objectives of this study are to demonstrate via analysis of F-15B Quiet Spike aeroservoelastic flight-test data for several flight conditions that 1) linear models are inefficient for modeling aeroservoelastic data, 2) nonlinear identification provides a parsimonious model description while providing a high percent fit for cross-validated data, and 3) the model structure and parameters vary as the flight condition is altered.

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“…Long extensions to the nose of an aircraft are likely to compromise the structural integrity and pitch/yaw controls due to the increased moment arm. The length and base diameter constraints used in the current study are determined rather arbitrarily with some insight to the problem gained from Gulfstream's Quiet Spike™ development, where the nose spike attached covers 30% of the entire aircraft length, and the base diameter is about half the maximum fuselage diameter [5]. The concerns associated with this design are listed as its weight and aeroelastic stability.…”

Section: Geometric Constraints and Profile Parameterizationmentioning

confidence: 99%

Design Optimization of Nose Geometry of F-5E Aircraft for Sonic Boom Mitigation

Ozcer

Kandil

2009

47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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The modified F-5E aircraft of Northrop Grumman for sonic boom shaping, also known as the Shaped Sonic Boom Demonstrator is equipped with an optimized nose attachment for sonic boom mitigation. The nose is extended by 20% of the aircraft length using an axisymmetric attachment. The geometry of the extension is optimized for ground level sonic boom mitigation using Response Surface Methodology and Computational Fluid Dynamics. 42.1% reduction on the ground signal leading shock strength is predicted for the proposed nose modification, with 0.96% increase in lift and 1.08 decrease in drag. High fidelity nonlinear prediction methods are used which include unstructured Euler near-field solution with grid adaptation and shock fitting and 2 nd order non-linear full potential signal marching in entire cross-flow through mid-field.

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Morphing Concept for Quiet Supersonic Jet Boom Mitigation

Cited by 21 publications

References 2 publications

Innovation in supersonic passenger air travel

Innovation in supersonic passenger air travel

Structure Computation of Quiet Spike Flight-Test Data During Envelope Expansion

Design Optimization of Nose Geometry of F-5E Aircraft for Sonic Boom Mitigation

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