HSCT configuration design space exploration using aerodynamic response surface approximations

Chuck, A Baker; Grossman, Bernard; Raphael, Thomas; William, H Mason; Layne, T Watson

doi:10.2514/6.1998-4803

Cited by 8 publications

(9 citation statements)

References 10 publications

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“…The resulting optimum HSCT design configuration is plotted in Figure 6. The optimum design had a TOGW of 753,900 lbs and was similar to designs found in an earlier study [1] using a local optimizer. While more computational time was spent finding essentially the same design using the global optimizer as the local optimizer, an assurance was gained that the optimum found was the global optimum.…”

Section: Optimization Results and Parallel Performancesupporting

confidence: 63%

“…The methods used to calculate the drag components used in the drag calculation and their corresponding ranges are described in [6], [7]. The aerodynamics calculations are based on the Mach box method [4], [3], and the Harris wave drag In previous work [1], it was observed that multiple optima exist within the design space. A visualization technique was needed to view the topology of the design space to understand the cause of the local optima, however the dimensionality of the design prevents traditional techniques from being used.…”

Section: Hsct Design Problemmentioning

confidence: 99%

“…Previous work [1] has shown that the design space of the HSCT configuration is complex. Local minima occur in many nonconvex, disconnected feasible islands present in the design space.…”

Section: Introductionmentioning

confidence: 99%

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Study of a global design space exploration method for aerospace vehicles

Baker

Watson²,

Grossman³

et al. 2000

8th Symposium on Multidisciplinary Analysis and Optimization

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In the early stages of the design process of aerospace vehicles, the search for optimal configurations encompasses a broad range of possibilities, and the use of local optimization tools may risk missing the best designs. Therefore, global optimization methods are attractive for the early design stage. Unfortunately, global design optimization usually requires the evaluation of a very large number of designs, a formidable computational challenge. The present work uses a highly effective Lipschitzian global optimization algorithm in the multidisciplinary optimization of a High Speed Civil Transport (HSCT). The use of massively parallel computers to handle this computational challenge is also demonstrated. A variety of load balancing methods are evaluated to assess the utilization of the computer nodes.

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Section: Optimization Results and Parallel Performancesupporting

confidence: 63%

Section: Hsct Design Problemmentioning

confidence: 99%

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Study of a global design space exploration method for aerospace vehicles

Baker

Watson²,

Grossman³

et al. 2000

8th Symposium on Multidisciplinary Analysis and Optimization

Self Cite

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“…For present HCV concept, high aeroheating areas were stagnation point, wing leading edges and scramjet engine leading edges. Al-Garni et al 52 considered that, if K T w 1500 ≤ , all the heat would be radiated, so no active cooling was needed. We conduct a more severe constraint on aeroheating that surface temperature should be lower than K 1300 .…”

Section: Aeroheating Modelmentioning

confidence: 99%

Application of Taguchi Design Methods and Uniform Design Methods to Scramjet Propulsion System Optimization for Hypersonic Cruise Vehicle

Luo

Lin

et al. 2003

39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit

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Hypersonic Cruise Vehicle (HCV) is defined as one kind of vehicle which mission is cruising in atmosphere, and generally with cruising velocity between Mach number 6 and 12. HCV generally utilizes scramjet as high-speed propulsion system, which is highly integrated with airframe. Due to the intense interactions between engine and airframe, the preliminary design of HCV is needed to be considered as a multidisciplinary design and optimization process in which aerodynamics, aeroheating, propulsion, weight and sizing, trajectory and control, performance and cost must be accounted simultaneously. This paper presents the results of an effort to multidisciplinary preliminary design and optimization of HCV with the highly scramjet engine/airframe integration using parameter methods. Disciplinary analysis models including propulsion performance, aerodynamic force accounting, aeroheating performance, weights and sizing, and life cycle cost are set up before implementing optimization process. Response surface models for aerodynamic performance and scramjet performance are constructed with variable-complexity modeling (VCM) techniques. The goal is to optimize a HCV to minimize gross take-off weight (GTOW) or life cycle cost (LCC) under a reference mission. Taguchi design method, uniform design method and D-optimal design method are used to evaluate the effects of changing 10 design parameters of scramjet/airframe in an integration methodology. The optimal result suggests a vehicle with GTOW 11.16% lighter and LCC 4.02% cheaper than the initial design with baseline configuration. Nomenclature exp − aft Ang = afterbody lower surface expansion angle exp − com Ang = combustor divergence duct expansion angle 1 inlet Ang = the first compression angle 2 inlet Ang = the second compression angle = the third compression angle D C = drag coefficient L C = lift coefficient max T C = maximum thrust coefficient PB xmc C = flat plate friction coefficient in low velocity flow xlw C = wing drag coefficient due to lift xw C = wing drag coefficient w x C 0 = wing zero-lift drag coefficient α yw C = wing lift curve slope D = drag com F = thrust due to combustor w g = ratio of wall enthalpy to total enthalpy h = altitude cruise H = cruise altitude w h = wall enthalpy s h = total enthalpy sp I = specific impulse L = lift m = mass M = constant Ma = Mach Number design Ma = inlet design Mach number trans Ma = transition Mach number f m & = fuel mass flow rate N = constant q = dynamic pressure cyl q & = heating rate of infinite swept cylinder fp q & = heating rate of inclined flat plate le q & = heating rate of leading edge axis s q , & = heating rate of stagnation point of an axisymmetric body base R = ratio of base height to fuselage height con com R − = ratio of combustor constant area duct length to combustor total length engine R = ratio of combustor length to vehicle length forebody R = ratio of forebody length to vehicle length N R = radius of nose s = throttle setting ref S = reference area t = time T = thrust V = velocity X = matrix plume X...

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“…The choice of gross weight as the objective function directly incorporates both aerodynamic and structural considerations, in that the structural design directly affects aircraft empty weight and drag, while aerodynamic performance dictates drag and thus the required fuel weight. This HSCT design problem is described in detail elsewhere (Baker et al (1998), Golovidov (1997, Hutchison et al (1993), Hutchison et al (1994), MacMillin et al (1996), MacMillin et al (1997)), and thus only a few pertinent details will be repeated here.…”

Section: Hsct Configuration Design Applicationmentioning

confidence: 99%

A fully‐distributed parallel global search algorithm

Watson

Baker²

2001

Engineering Computations

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The n-dimensional direct search algorithm DIRECT of Jones, Perttunen, and Stuckman has attracted recent attention from the multidisciplinary design optimization community. Since DIRECT only requires function values (or ranking) and balances global exploration with local refinement better than n-dimensional bisection, it is well suited to the noisy function values typical of realistic simulations. While not efficient for high accuracy optimization, DIRECT is appropriate for the sort of global design space exploration done in large scale engineering design. Direct and pattern search schemes have the potential to exploit massive parallelism, but efficient use of massively parallel machines is nontrivial to achieve. This paper presents a fully distributed control version of DIRECT that is designed for massively parallel (distributed memory) architectures. Parallel results are presented for a multidisciplinary design optimization problem-configuration design of a high speed civil transport.

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HSCT configuration design space exploration using aerodynamic response surface approximations

Cited by 8 publications

References 10 publications

Study of a global design space exploration method for aerospace vehicles

Study of a global design space exploration method for aerospace vehicles

Application of Taguchi Design Methods and Uniform Design Methods to Scramjet Propulsion System Optimization for Hypersonic Cruise Vehicle

A fully‐distributed parallel global search algorithm

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