Heat pipe and surface mass transfer cooling of hypersonic vehicle structures

Colwell, Gene T.; Modlin, James M.

doi:10.2514/3.387

Cited by 19 publications

(6 citation statements)

References 7 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Therefore, only the main steps will be shown. The general solution of (2.7) in cylindrical coordinates is The respective porous domain is shown in figure 2 and resembles an architecture which would be found in a porous leading edge of a hypersonic vehicle (Colwell & Modlin 1992). The porous domain extends from to , where it is terminated by an impermeable boundary in radial orientation, and the domain is symmetrical along the axis.…”

Section: Solution Of Laplace's Equationmentioning

confidence: 99%

Analytical solution of flows in porous media for transpiration cooling applications

Hermann

McGilvray

2021

J. Fluid Mech.

View full text Add to dashboard Cite

show abstract

Section: Solution Of Laplace's Equationmentioning

confidence: 99%

Analytical solution of flows in porous media for transpiration cooling applications

Hermann

McGilvray

2021

J. Fluid Mech.

View full text Add to dashboard Cite

show abstract

“…The hollow center of the wedge allows for the potential to cool the leading edge with a gas, liquid, or a higher conductivity solid. 34,35 The hollow center also decreases the mass of the leading edge compared to solid wedges. The welded wedge presented in Fig.…”

Section: Wwwceramicsorg/actmentioning

confidence: 99%

Mechanical Behavior and Applications of Plasma Arc Welded Ceramics

King

Hilmas

2015

Int J Applied Ceramic Tech

View full text Add to dashboard Cite

Zirconium diboride and zirconium carbide‐based ceramics were joined by plasma arc welding to demonstrate the versatility of this technique. A parent material composition consisting of ZrB2 with 20 vol% ZrC was hot pressed to near full density, sectioned to produce specimens for welding, and welded together to produce billets for mechanical property studies. The four‐point flexure strength of the parent material was ~660 MPa, while the strength of the welded specimens ranged from ~140 to ~250 MPa. Microstructural analysis revealed that decreased strength in the welded specimens was caused by volume flaws, microcracking of large ZrB2 grains (up to 1 mm in length), and residual tensile stresses that developed at the surface of weld pools during cooling. The versatility of plasma arc welding was demonstrated by joining of ZrC‐based ceramics and fabricating three ZrB2–ZrC components for potential applications, including a high‐temperature electrical contact, an ultra‐high‐temperature thermocouple, and a wedge that was a notional wing leading edge. These three applications demonstrated the ability to join ceramics to a refractory metal, fabricate a chemically inert high‐temperature thermocouple, and produce complex shapes for aerospace applications.

show abstract

“…The results indicate that the niobium alloy Cb-752, with lithium as the working fluid, is a feasible combination for Mach 6-8 flight with a 3 mm leading edge radius. Gene et al [10] used a verified heat pipe cooling model to analyze the thermal protection scheme combining evaporation and film cooling. The study indicates that these cooling techniques limited the maximum leading-edge surface temperatures, moderated the structural temperature gradients, and led to the conclusion that cooling leading-edge structures exposed to severe hypersonic flight environments using a combination of liquid metal heat pipe, surface transpiration, and film cooling methods appeared feasible.…”

Section: Introductionmentioning

confidence: 99%

Numerical Study on Low-Temperature Region as Heat Sink and Its Heat Dissipation Capacity for Hypersonic Vehicle

Jiang

et al. 2021

Aerospace

View full text Add to dashboard Cite

Researches have focused on the thermal protection system (TPS) of hypersonic vehicles under severe aerodynamic heat. According to the second law of thermodynamics, heat transfer needs to consume a heat sink, but the cold energy provided by the airborne heat sink is limited. Therefore, it is necessary to explore new available heat sinks during hypersonic cruise. This paper numerically calculated the wall temperature distribution of hypersonic vehicle X-51A with different Mach numbers, altitudes and angles of attack using ANSYS Fluent 19.0. A dimensionless parameter, relative temperature coefficient rt, was proposed to characterize the relative value of local wall temperature in the whole wall temperature range. The distribution regularity and influencing factors of wall temperature were summarized. The low-temperature region which is less affected by flight conditions was divided as the heat sink and its heat dissipation capacity (Q) and characteristics were studied. The angle of attack has great influence on the temperature distribution. In XY view the rear side of leeward surface is least affected by flight conditions and its rt is less than 0.2, which can be used as a low-temperature region. Taking this region as a heat sink to dissipate heat, it is found that the Q of the new heat sink is 30 kW/m2 at Ma 3, 90 kW/m2 at Ma 4 and 200 kW/m2 at Ma 5. The Q increases greatly with the increase in Mach number, and the convective heat transfer coefficient (h) also increases. At the same Q, the h decreases with the increase in Mach number. The exploration of low-temperature region as heat sink has an important reference for reducing the dependence on consumable heat sink and alleviating the energy shortage of the hypersonic vehicle.

show abstract

Heat pipe and surface mass transfer cooling of hypersonic vehicle structures

Cited by 19 publications

References 7 publications

Analytical solution of flows in porous media for transpiration cooling applications

Analytical solution of flows in porous media for transpiration cooling applications

Mechanical Behavior and Applications of Plasma Arc Welded Ceramics

Numerical Study on Low-Temperature Region as Heat Sink and Its Heat Dissipation Capacity for Hypersonic Vehicle

Contact Info

Product

Resources

About