A multidisciplinary performance analysis of a lifting-body single-stage-to-orbit vehicle

Tartabini, Paul V.; Lepsch, Roger A.; Korte, John J.; Wurster, Kathryn E.

doi:10.2514/6.2000-1045

Cited by 22 publications

(12 citation statements)

References 12 publications

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“…TETRUSS (ref 15), NASALaRC's unstructured gridNavier Stokes flow solver, was utilized sparingly in this regime for significant configuration changes where the magnitude (c)2000 American Institute of Aeronautics & Astronautics or published with permission of author(s) and/or author(s)' sponsoring organization. 5 American Institute of Aeronautics and Astronautics of the viscous contribution was uncertain, and an understanding of the flow features was required. (Figure 17 below shows an example comparison of FELISA, TETRUSS and MSFC Trisonic wind tunnel data in the transonic regime for a configuration trade.)…”

Section: Analysis Methodsmentioning

confidence: 99%

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Overview of conceptual design of early VentureStar configurations

Lockwood

2000

38th Aerospace Sciences Meeting and Exhibit

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One of NASA's goals is to enable commercial access to space at a cost of $lOOO/lb (an order of magnitude less than today's cost) by approximately 2010. Based on results from the 1994 Congressionally mandated, NASA led, Access-to-Space Study, an all rocket-powered single-stage-to-orbit reusable launch vehicle was selected as the best option for meeting the goal. To address the technology development issues and the followon development of an operational vehicle, NASA initiated the X-33 program.

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Section: Analysis Methodsmentioning

confidence: 99%

“…(ref 5) In other words, the ratio of LOX to LH2, and the corresponding tank sizes, packaged in the vehicle can be optimized to achieve a maximum payload to orbit for a given vehicle size. The baseline VentureStarTM concepts have a ratio of LOX to LH2 of 6 based on weight.…”

Section: Early Venturestartm Reference Vehiclementioning

confidence: 99%

Overview of conceptual design of early VentureStar configurations

Lockwood

2000

38th Aerospace Sciences Meeting and Exhibit

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“…Laminar-turbulent transition leads to substantial increase of the aerodynamic drag and surface heating of hypersonic vehicles [1,2]. Transition also affects engine performance and aerodynamic control.…”

Section: Introductionmentioning

confidence: 99%

Experimental study of compressible boundary layer on a cone at angles of attack

et al. 2009

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Experimental study was conducted for boundarylayers on a sharp 5 • half-angle cone of 400 mm length at angles of attack. The model was tested in the T-326 hypersonic wind tunnel (ITAM) at freestream Mach number M = 5.95. Mean and fluctuation wall characteristics of the boundary layer are measured at 0 • , 2 • , 3 • and 4 • angles of attack for different stagnation pressures. Pulsation measurements are carried out by means of ALTP sensor. Pressure and temperature distributions along the model are obtained, and transition beginning and end locations have been found. Boundary layer stabilization with the increase of angle of attack and the decrease of stagnation pressure is observed. High frequency pulsations inherent to hypersonic boundary layer (second mode) have been detected.

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“…The disciplines which must be accounted for and integrated during the design are: trajectory optimization [4-6], guidance, navigation, and control (GN&C) technology [7,8], aerodynamics and aerothermodynamics [9][10][11], thermal-structural analysis [12][13][14], and thermal protection system (TPS) development [15][16][17][18][19]. Efforts have been made in developing a collaborative or a multidisciplinary optimization process that considers some of the disciplines of interest during an integrated design [20][21][22][23]. Further, it is important to capture in the decision making process how uncertainty in the atmospheric conditions, in the entry parameters of the vehicle, in the condition of the vehicle during entry, and in the performance of the TPS will influence the design and provide a risk assessment for a mission.…”

Section: Introductionmentioning

confidence: 99%

Multidisciplinary Design under Uncertainty for a Hypersonic Vehicle

Zhang¹,

He²,

Vlahopoulos

2010

13th AIAA/ISSMO Multidisciplinary Analysis Optimization Conference

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An integration environment has been developed for conducting multidiscipline design optimization analysis under uncertainty. It facilitates solution of multiple optimization problems in parallel with multiple sets of objectives and constraints originating from different design disciplines while simultaneously accounting for uncertainty during the optimization process.A seamless general purpose integration capability facilitates exchanging data between the optimization processes and the solvers which are used for evaluating the objective functions and the constraints. Metamodels can be developed and used instead of the actual solvers during the highly iterative optimization process in order to expedite the computations. Uncertainties are introduced in the optimization by considering the constraints which depend on any random variables and any random parameters as probabilistic. Satisfying the probabilistic constraints in the presence of uncertainty introduces sufficient conservatism in the solution and eliminates the need for further application of safety factors. The work presented in this paper considers trajectory, aerothermal, aerodynamic, thermal, and structural computations when performing the design optimization for the Thermal Protection System (TPS) and for the structure of a TSTO upper stage vehicle. Sixteen different sections are considered on the vehicle when designing the TPS. The trajectory bank angle schedule, the angle of attack schedule, the thickness of the sixteen different TPS sections, and twenty seven thicknesses associated with the structure are considered when reducing the overall weight of the vehicle while satisfying the imposed constraints. Uncertainties are considered in three control angles of the trajectory, in the material strength, the thrust load and the 2.5G loads. The results from the multi-discipline optimization without and with uncertainty are discussed, and a comparison between the deterministic and the probabilistic optimum is made.

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A multidisciplinary performance analysis of a lifting-body single-stage-to-orbit vehicle

Cited by 22 publications

References 12 publications

Overview of conceptual design of early VentureStar configurations

Overview of conceptual design of early VentureStar configurations

Experimental study of compressible boundary layer on a cone at angles of attack

Multidisciplinary Design under Uncertainty for a Hypersonic Vehicle

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