Liquid Metals Heat-Pipe solution for hypersonic air-intake leading edge: Conceptual design, numerical analysis and verification

Fusaro, Roberta; Ferretto, Davide; Viola, Nicole; Scigliano, Roberto; Simone, Valeria De; Marini, Marco

doi:10.1016/j.actaastro.2022.05.034

Cited by 9 publications

(5 citation statements)

References 16 publications

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“…Finally, it is worth noting that the rear part of the condenser region shall be properly interfaced with the tankʹs external structure to guarantee the required heat rejection. Figure 6 also shows that the most promising pipe for our case would be a nickel-potassium one [37]. The numerical APDL model has been verified numerically by comparing the results in terms of heat pipe predicted subtractive heat flux w.r.t the results obtained by several parametric finite element models introduced hereafter.…”

Section: Case Study No 1: Stratofly Mr3 Hypersonic Vehiclementioning

confidence: 81%

“…Finally, it is worth noting that the rear part of the condenser region shall be properly interfaced with the tank's external structure to guarantee the required heat rejection. Figure 6 also shows that the most promising pipe for our case would be a nickel-potassium one [37].…”

Section: Case Study No 1: Stratofly Mr3 Hypersonic Vehiclementioning

confidence: 95%

“…In order to predict a generic heat pipe thermal performance, a numerical Ansys Parametric Design Language (APDL) code [37] has been set up to verify the effective subtractive heat flux guaranteed by the selected heat pipe arrangement. The heat pipe operations can be described by a lumped parametric model based on the electrical analogy [38][39][40].…”

Section: Development Of the Numerical Toolmentioning

confidence: 99%

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Numerical Simulation of Heat Pipe Thermal Performance for Aerospace Cooling System Applications

Scigliano,

De Simone,

Fusaro

et al. 2024

Aerospace

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The design of integrated and highly efficient solutions for thermal management is a key capability for different aerospace products, ranging from civil aircraft using hydrogen on board to miniaturized satellites. In particular, this paper discloses a novel numerical tool for the design and thermal performance assessment of heat pipes. To achieve this goal, a numerical Ansys Parametric Design Language code is set up to verify the effective subtractive heat flux guaranteed by the selected heat pipe arrangement. The methodology and related tool show their ability to provide good thermal performance estimates for different heat pipe designs and operating conditions. Specifically, the paper reports two very different test cases: (1) solid metal heat pipes to cool down the crotch leading-edge area of the air intake of a Mach 8 civil passenger aircraft, and (2) a copper-water heat pipe to cool down a Printed Circuit Board of a generic small LEO satellite. The successful application of the methodology and numerical code confirms the achievement of the ambitious goal of developing in-house tools to support heat pipe thermal performance prediction for the entire aerospace domain.

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Section: Case Study No 1: Stratofly Mr3 Hypersonic Vehiclementioning

confidence: 81%

Section: Case Study No 1: Stratofly Mr3 Hypersonic Vehiclementioning

confidence: 95%

Section: Development Of the Numerical Toolmentioning

confidence: 99%

See 1 more Smart Citation

Numerical Simulation of Heat Pipe Thermal Performance for Aerospace Cooling System Applications

Scigliano,

De Simone,

Fusaro

et al. 2024

Aerospace

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“…Semi-passive systems are implemented for high heat fluxes that persist for long durations, and encompass: (i) reusable heat pipes that transfer and radiate thermal energy via evaporative cooling and capillary wicking (e.g. liquid lithium or potassium 23 ); or (ii) single-use ablatives materials that absorbed energy via pyrolysis or charring of a reinforced polymer/resin (used in the early atmosphericre-entry capsules such as Apollo, Fig. 1h).…”

Section: Thermal Protection Systemmentioning

confidence: 99%

“…Other refractory metals, such as the TaWHf alloys T111 and T222 (Box 1) exhibit favorable creep-resistant materials properties and are ideal for the extended containment of heated liquid alkali-metal working fluids (1000-1300 °C) for heat pipe type leading edge designs 52 . T111/Li and niobium-based C-103/Na designs have been assessed to satisfy the requirements for Mach 8 and Mach 10 flights respectively 23 .…”

Section: Metallic Materials For Hypersonicsmentioning

confidence: 99%

Materials design for hypersonics

Peters,

Zhang,

Chen

et al. 2024

Nat Commun

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Hypersonic vehicles must withstand extreme conditions during flights that exceed five times the speed of sound. These systems have the potential to facilitate rapid access to space, bolster defense capabilities, and create a new paradigm for transcontinental earth-to-earth travel. However, extreme aerothermal environments create significant challenges for vehicle materials and structures. This work addresses the critical need to develop resilient refractory alloys, composites, and ceramics. We will highlight key design principles for critical vehicle areas such as primary structures, thermal protection, and propulsion systems; the role of theory and computation; and strategies for advancing laboratory-scale materials to manufacturable flight-ready components.

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