Hypersonic waveriders for planetary atmospheres

Anderson, J. D.; Lewis, Mark J.; Kothari, Ajay P.; Corda, Stephen

doi:10.2514/6.1990-538

Cited by 12 publications

(6 citation statements)

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“…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: 74%

“…An optimized vehicle shape is here assumed with (L/D) * = (L/D) max = 3.7 according to Anderson et al 1991b; an aerodynamic performance degradation is considered: performance degradation is caused by the leading edge bluntness aimed to contain the heating rate, and by the Reynolds numbers experienced during the atmospheric passage simulated in this work, which are lower than the optimal design flight conditions. Moreover, a C * l = 0.0848 (the value of the lift coefficient that maximizes L/D) has been extrapolated from data given in Anderson et al (1991a and1991b) and n = 1.75 is posted. It is worth noting that, due to atmosphere rarefaction, a substantial decrease in (L/D) * occurs during the atmospheric descent and breakaway phases.…”

Section: Waverider Aerodynamic Modelmentioning

confidence: 99%

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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: 74%

Section: Waverider Aerodynamic Modelmentioning

confidence: 99%

Aero-gravity assist maneuvers: controlled dynamics modeling and optimization

Armellín

Lavagna

Ercoli-Finzi

2006

Celestial Mech Dyn Astr

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“…These works appear in the form of journal articles, book series, NASA monographs, Air Force reports, textbooks, and periodicals. For example, a limited list of resources examined includes studies attributed to: Hallion, 1-5 Launius, [6][7][8] Bertin, [9][10][11][12][13][14][15] Curran, 16,17 Murthy, 18,19 Jenkins, 20,21 Billig, [22][23][24][25][26][27] Jacobsen, 28 Walker, [29][30][31][32][33] Lewis, [34][35][36][37][38][39] Starkey, 40 Blankson, [41][42][43][44][45] Marren, 46,47 Paull, 48,49 Anderson, [50][51][52][53][54]…”

Section: Ahimentioning

confidence: 99%

Current State of High Speed Propulsion: Gaps, Obstacles and Technological Challenges in Hypersonic Applications

Barber

Maicke

Majdalani

2009

45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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The object of this study is to canvas the literature for the purpose of identifying and compiling a list of Gaps, Obstacles, and Technological Challenges in Hypersonic Applications (GOTCHA). The significance of GOTCHA related deficiencies is discussed along with potential solutions, promising approaches, and feasible remedies that may be considered by engineers in pursuit of next generation hypersonic vehicle designs and optimizations. Based on the synthesis of several modern surveys and public reports, a cohesive list is formed consisting of widely accepted areas needing improvement that fall under several general categories. These include: aerodynamics, propulsion, materials, analytical modeling, CFD modeling, and education in high speed flow physics. New methods and lines of research inquiries are suggested such as the homotopy-based analysis (HAM) for the treatment of strong nonlinearities, the use of improved turbulence models and unstructured grids in numerical simulations, the need for accessible validation data, and the refinement of mission objectives for Hypersonic Airbreathing Propulsion (HAP).

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“…However, the problem has been often studied: starting from the sixties, the advantage of AGAM whenever large plane changes are asked for has been highlighted [1]. Thanks to studies related to the definition of very high efficiency shapes in a hypersonic environment, the AGAM applicability became more real [2]. Based on those results, McRonald and Randolph proposed an AGAM solution for very demanding missions towards the Sun and Pluto, demonstrating that by applying a Mars AGAM the C3, the transfer time are significantly reduced and the radiation problem related to a Jupiter GAM (representing the default strategy) is avoided [3,4].…”

Section: Introductionmentioning

confidence: 98%