A Hypersonic Vehicle Model Generator for MASIV

Vick, Tyler J.; Muse, Jonathan A.; Bolender, Michael A.

doi:10.2514/6.2012-4563

Cited by 6 publications

(3 citation statements)

References 14 publications

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“…The MASIV/MASTrim model has been the subject of many previous papers [14,[17][18][19][20][21][22] and is used for this work. Figure 1 illustrates the generic hypersonic vehicle design used for the present work, and the name "MAX-1" is associated with this vehicle.…”

Section: Dual-mode Ramjet-scramjet Vehicle Modelmentioning

confidence: 99%

Design Optimization of a Scramjet Vehicle for Ascent Using Surrogate Optimization

Dalle

Driscoll

2014

52nd Aerospace Sciences Meeting

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Design optimization is performed for a scramjet-powered vehicle that ascends along a trajectory with constant dynamic pressure from Mach 7 to Mach 13. The net acceleration is free during the trajectory, and the optimum acceleration profile is dependent on the vehicle design. To perform this analysis, a new reduced-order model (MASIV) is used that can evaluate the forces and moments on the vehicle in about five seconds on a single computer while accounting for wave interactions, fuel-air mixing, finite-rate chemistry, and other complex physical phenomena. It is found that the optimum acceleration is close to the maximum acceleration that the vehicle can attain. To minimize the fuel consumed for the entire ascent trajectory, there is a trade-off between performance and robustness to variations in angle of attack.

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Section: Dual-mode Ramjet-scramjet Vehicle Modelmentioning

confidence: 99%

Design Optimization of a Scramjet Vehicle for Ascent Using Surrogate Optimization

Dalle

Driscoll

2014

52nd Aerospace Sciences Meeting

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“…The MASIV/MASTrim model has been the subject of many previous papers [16][17][18][19][20][21][22] and is used for this work. Figure 1 illustrates the generic hypersonic vehicle design used for the present work, and the name "MAX-1B" is associated with this vehicle.…”

Section: Dual-mode Ramjet-scramjet Vehicle Modelmentioning

confidence: 99%

Flight Mechanics of Ram-Scram Transition

Dalle

Driscoll

2013

AIAA Atmospheric Flight Mechanics (AFM) Conference

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Among known air-breathing propulsion systems, the system that can be operated over the widest range of flight Mach numbers is the dual-mode ramjet-scramjet. In such an engine, either subsonic combustion or supersonic combustion can occur in a shared flowpath, and the mode of operation is determined by the flight condition and control inputs. Recent research has indicated that the steadystate thrust of such an engine is discontinuous across the transition from one mode to the other. This work discusses evidence for that discontinuity and discuss conditions and strategies required to maintain control through ram-scram transition. Nomenclature a = acceleration A = duct area c p = specific heat at constant pressure C L = lift coefficient C D = drag coefficient I = impulse function K = drag polar coefficient m f = cumulative fuel consumptioṅ m = mass floẇ m f = fuel mass flow rate M = Mach number p = pressure q ∞ = freestream dynamic pressure Q f = specific fuel heat release R = normalized gas constant S = reference area t = time T = temperature u = total flow speed u = vector of control variables V = velocity of vehicle x = vector of state variables γ = ratio of specific heats, flight path angle η c = combustion efficiency ρ = density τ = temporal integration variable

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“…The focus then shifted to control-oriented modeling, where the modeling focus is to facilitate implemetation of efficient control laws. 10,16,44,57,58 The afforementioned works all consistently focus on studying the longitudinal dynamics of the vehicle, the only work that studies the impact of longitudinal, lateral, and directional dynamics is by Keshmiri et. al.…”

Section: Vehicle Dynamics Modelingmentioning

confidence: 99%

Aeroelastic Control-oriented Modeling of an Air-breathing Hypersonic Vehicle

Sudalagunta

Sultan

Kapania

et al. 2016

15th Dynamics Specialists Conference

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I would like to convey my heartfelt thanks and sincere gratitude to my advisor, Dr. Cornel Sultan, for his endless support and constant motivation over the past four years. I've grown many-fold as a researcher since he had taken me under his wing and helped hone skills that I'm sure will help me in my career going forward. I'd like to thank my co-advisor Dr. Pradeep Raj for patiently engaging me in several brain storming sessions that helped me get past numerous road blocks. His suggestion of conducting sanity checks at every juncture has helped me verify most of the results presented in my dissertation. I am grateful to Dr. Rakesh Kapania for constantly challenging me to venture into unknown territories, and for being the beacon and showing the way when I get lost. This section woiuld be incomplete without thanking Dr. Layne T. Watson, who has patiently reviewed all my publications and in the process taught me writing well rounded technical articles. Apart from being an incredible source of knowledge, my advisory committee has been a constant source of support throughout this endeavor. Most of the results published in this thesis would not have been possible without your valuable feedback. This experience has not only helped me learn how to better conduct research but myself in a professional environment. I can't thank you enough for your guidance. I will forever be indebted to my loving and caring parents for their endless support and encouragement they have given me over the years. My life in Blacksburg would be incomplete without the many friends I've made, and the memories I'll be carrying with me for the rest of my life. You've helped me make a home away from home and been that support when I needed someone to lean on. Although, we never worked together I've always had my research group with my whenever I needed their help. Last but never the least, I'd like to thank the beautiful town of Blacksburg for cradling me in it's love. v

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A Hypersonic Vehicle Model Generator for MASIV

Cited by 6 publications

References 14 publications

Design Optimization of a Scramjet Vehicle for Ascent Using Surrogate Optimization

Design Optimization of a Scramjet Vehicle for Ascent Using Surrogate Optimization

Flight Mechanics of Ram-Scram Transition

Aeroelastic Control-oriented Modeling of an Air-breathing Hypersonic Vehicle

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