Dual-fuel vehicle airframe and engine structural integration

Weirich, Tony; Fogarty, W J; Dry, K.; Iqbal, Azhar; Moses, Paul L.

doi:10.2514/6.1996-4594

Cited by 6 publications

(5 citation statements)

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“…An optimization analysis is often required in order to design the TPS distribution, such as performed in Ref. 26, and it was not performed in the present study.…”

Section: Conjugate Heat Transfer Analysismentioning

confidence: 98%

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Uncertainty Propagation in Integrated Airframe Propulsion System Analysis for Hypersonic Vehicles

Lamorte

Friedmann

Dalle

et al. 2011

17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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“…An optimization analysis is often required in order to design the TPS distribution, such as performed in Ref. 26, and it was not performed in the present study.…”

Section: Conjugate Heat Transfer Analysismentioning

confidence: 98%

“…35,36 IMI is also used in Ref. 26 as the main heat barrier for a long range hypersonic vehicle. The thicknesses of the TPS layers are uniform.…”

Section: Conjugate Heat Transfer Analysismentioning

confidence: 99%

Uncertainty Propagation in Integrated Airframe Propulsion System Analysis for Hypersonic Vehicles

Lamorte

Friedmann

Dalle

et al. 2011

17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

View full text Add to dashboard Cite

“…Structural components have played a major role in the development and design of hypersonic vehicles [7,[30][31][32][33][34][35][36][37]. The structure experiences high-temperature gradients and intense pressure and heat loading, which can cause local buckling or flutter.…”

Section: Structural Modelmentioning

confidence: 99%

“…This TPS system is shown to be light and efficient in [42,43]. The IMI is also used in [32] as the main heat barrier for a long-range hypersonic vehicle. The thicknesses of the TPS layers are uniform.…”

Section: Conjugate Heat Transfer Analysismentioning

confidence: 99%

See 1 more Smart Citation

Uncertainty Propagation in Integrated Airframe–Propulsion System Analysis for Hypersonic Vehicles

Lamorte

Friedmann

Dalle

et al. 2015

Journal of Propulsion and Power

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Air-breathing hypersonic vehicles are based on an airframe-integrated scramjet engine. The elongated forebody that serves as the inlet of the engine is subject to harsh aerothermodynamic loading, which causes it to deform. Unpredicted deformations may produce unstart, combustor chocking, or structural failure due to increased loads. An uncertainty quantification framework is used to propagate the effects of aerothermoelastic deformations on the performance of the scramjet engine. A loosely coupled airframe-integrated scramjet engine is considered. The aerothermoelastic deformations calculated for an assumed trajectory and angle of attack are transferred to a scramjet engine analysis. Uncertainty associated with deformation prediction is propagated through the engine performance analysis. The effects of aerodynamic heating and aerothermoelastic deformations at the cowl of the inlet are the most significant. The cowl deformation is the main contributor to the sensitivity of the propulsion system performance to aerothermoelastic effects.across thickness of skin h 1 , h 2 = thickness of thermal protection system layers h 3 = thickness of structural layer k = thermal conductivity M = Mach number m f = expected value of f _ m air = air mass flow rate _ m f = fuel mass flow rate P = pressure q aero = aerodynamic heat flux q ∞ = dynamic pressure Re = Reynolds number based on length of 1 m T = temperature T r = recovery temperature t = flight time u = axial displacement v = lateral displacement w = transverse displacement w j = weight in numerical integration x 0 ; y 0 ; z 0 = coordinate system for corrugated panel x = coordinate along vehicle, from leading edge, positive aft y = coordinate in spanwise direction, from centerline of vehicle z = coordinate normal to vehicle, from leading edge point, positive up α = angle of attack α T = thermal expansion coefficient α f = angle of attack of trajectory γ = specific heat ratio, c p ∕c v ξ 1 , ξ 2 = uncertain variables ν = Poisson ratio ϵ = emissivity ρ = density of air ρ M = density of material σ f = standard deviation of f ϕ j = interpolation function Subscripts i = initial value st = stoichiometric condition wall = at wall 0 = total condition 4 = condition at exit of combustor ∞ = freestream condition

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