Analytical Off-Design Lift-to-Drag-Ratio Analysis for Hypersonic Waveriders

Starkey, Ryan P.; Lewis, Mark J.

doi:10.2514/2.3618

Cited by 41 publications

(24 citation statements)

References 6 publications

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“…Since the late 80s, design optimization of waverider shape has been the subject of several research projects. The Maryland University Hypersonics Team produced a great amount of work about this topic focusing attention on viscous (Bowcutt et al 1987), gas rarefaction (Anderson et al 1991a), off-design conditions (Starkey and Lewis 2000), and blunted nose effects on L/D performances (Gillum and Lewis 1997). Furthermore waveriders optimized for Cytherean and Martian atmosphere have been carried out; the obtained solutions, optimal according to aerodynamics and shape, turned out to be definitely similar to the Earth atmosphere optimization scenario (Anderson et al 1991b).…”

Section: Waverider Aerodynamic Modelmentioning

confidence: 77%

Aero-gravity assist maneuvers: controlled dynamics modeling and optimization

Armellín

Lavagna

Ercoli-Finzi

2006

Celestial Mech Dyn Astr

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The aero-gravity assist maneuver is here proposed as a tool to improve the efficiency of the gravity assist as, thanks to the interaction with the planetary atmospheres, the angular deviation of the velocity vector can be definitely increased. Even though the drag reduces the spacecraft velocity, the overall υ gain could be remarkable whenever a high lift-to-drag vehicle is supposed to fly. Earlier studies offer simplified approaches according to both the dynamics modeling and the atmospheric trajectory constraints. In this paper a 3D dynamical model is adopted and a more realistic L/D performance for the hypersonic vehicle is assumed. Some relevant aspects related to the multidisciplinary design have been considered such as heating rates and structural loads bounding. Comparisons between in and out of plane maneuvering have been performed by assuming, as control variables, either the angle of attack or the bank angle, respectively. The optimal control problem has been solved by selecting a direct method approach. The dynamics has been transcribed into a set of non-linear constraints and the arising non-linear programming problem has been solved with a sequential quadratic programming solver. To gain the global optimum convergence the initial guess has been supplied by solving the same problem by a direct shooting technique and a genetic optimizer.

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Section: Waverider Aerodynamic Modelmentioning

confidence: 77%

Aero-gravity assist maneuvers: controlled dynamics modeling and optimization

Armellín

Lavagna

Ercoli-Finzi

2006

Celestial Mech Dyn Astr

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“…The waverider baseline geometry is defined by three two-dimensional power-law equations [28]. The planform and the upper surfaces of the vehicle are parameterised by the length l, the width, w, a power law exponent n, the vehicle centre line wedge angle, θ, and β, which is the oblique shock wave inclination angle [28].…”

Section: Geometry and Shape Modelmentioning

confidence: 99%

“…Here the integrated technique is applied to the design of a medium scale USV, considering a more complex implementation, with two different trajectory optimisations: different control laws allow the same vehicle to follow a) the path that minimises the maximum heat flux, and b) the one maximising the orthodromic distance, during the re-entry phase. As in [19], here the shape of the vehicle is derived from on an ideal waverider configuration ( [29,15,28]), and its geometry is modified in order to introduce more realistic rounded edges.…”

Section: Introductionmentioning

confidence: 99%

Robust design of a re-entry unmanned space vehicle by multi-fidelity evolution control

Minisci

Vasile

2011

Proceedings of the 13th Annual Conference on Genetic and Evolutionary Computation

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This version is available at https://strathprints.strath.ac.uk/43206/ Strathprints is designed to allow users to access the research output of the University of Strathclyde. Unless otherwise explicitly stated on the manuscript, Copyright © and Moral Rights for the papers on this site are retained by the individual authors and/or other copyright owners. Please check the manuscript for details of any other licences that may have been applied. You may not engage in further distribution of the material for any profitmaking activities or any commercial gain. You may freely distribute both the url (https://strathprints.strath.ac.uk/) and the content of this paper for research or private study, educational, or not-for-profit purposes without prior permission or charge.Any correspondence concerning this service should be sent to the Strathprints administrator: strathprints@strath.ac.ukThe Strathprints institutional repository (https://strathprints.strath.ac.uk) is a digital archive of University of Strathclyde research outputs. It has been developed to disseminate open access research outputs, expose data about those outputs, and enable the management and persistent access to Strathclyde's intellectual output. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60 F o r P e e r R e v i e w 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 y r q h q d p T t u ! E j p s j t s r E r £ x r t ± r t s A r Ex r d d h q j x r Ç E j u r ) x t u U h s x t ) Ũ u 1 h l ! u E s ) x r Ũ x r h q x ì l P t u j 8 r E p Â Ũ £ r x t s rr H y £ h q j x y p s r q h q r r r x r E j £ r Ex r U d h q Á t u h E j r q x r u « p s f gG1 0.664 p ρ 2 e v 3 e µ * C * /ρ * 0.037v 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 ...

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“…4-7, the interest had gone into finding solutions to the hypersonic small disturbance form of the inviscid adiabatic-flow equations, since the equations of motion for hypersonic flow over slender bodies can be reduced to simpler form by incorporating the hypersonic slenderbody approximations; 21 ͑2͒ for Refs. [8][9][10][11][12][13][14][15][16][17][18][19][20], the interest has gone into considering the power-law shape as possible candidate for blunting geometries of hypersonic leading edges, such as hypersonic waverider vehicles.…”

Section: Introductionmentioning

confidence: 99%

“…A great deal of experimental and theoretical works [4][5][6][7][8][9][10][11][12][13][14][15][16][17][18][19][20] has been carried out previously on power-law forms representing blunt geometries. The major interest in these works is twofold: ͑1͒ for Refs.…”

Section: Introductionmentioning

confidence: 99%

Physical and computational aspects of shock waves over power-law leading edges

Santos

2008

Physics of Fluids

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Computations using the direct simulation Monte Carlo ͑DSMC͒ method are presented for hypersonic flow on power-law shaped leading edges. The primary aim of this paper is to examine the geometry effect of such leading edges on the shock-wave structure. The sensitivity of the shock-wave shape, shock-wave thickness, and shock-wave standoff distance to shape variations of such leading edges is investigated by using a model that classifies the molecules in three distinct classes: ͑1͒ undisturbed freestream, ͑2͒ reflected from the boundary, and ͑3͒ scattered, i.e., molecules that had been indirectly affected by the presence of the leading edge. The analysis showed that, for power-law shaped leading edge with exponent between 2 / 3 and 1, the shock wave follows the body shape. It was found that, at the vicinity of the nose, the shock-wave power-law exponent is 1 / 2. Far from the nose, calculations showed that the shock-wave shape is in surprising qualitative agreement with that predicted by the hypersonic small disturbance theory for the flow conditions considered.

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Analytical Off-Design Lift-to-Drag-Ratio Analysis for Hypersonic Waveriders

Cited by 41 publications

References 6 publications

Aero-gravity assist maneuvers: controlled dynamics modeling and optimization

Aero-gravity assist maneuvers: controlled dynamics modeling and optimization

Robust design of a re-entry unmanned space vehicle by multi-fidelity evolution control

Physical and computational aspects of shock waves over power-law leading edges

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