Measurement of Aerothermal Heating on HIFiRE-0

Neely, Andrew J.; Choudhury, Rishabh; Riesen, Hans; Paukner, Daniel; Odam, Judy

doi:10.2514/6.2011-2356

Cited by 9 publications

(4 citation statements)

References 10 publications

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“…However, in some cases the peak temperature distribution is enough, for example to give a warning if the surface temperature exceeds the designed value. In addition, since optical access is not needed, it is suitable for industrial applications with harsh environments, e.g., temperature measurements of gas turbine walls [111], aero engine blades [112] turbine blades [113,114], and components of rockets [115,116]. [117].…”

Section: Temperature-indicating Paintmentioning

confidence: 99%

Review of Development and Comparison of Surface Thermometry Methods in Combustion Environments: Principles, Current State of the Art, and Applications

Liu

Huang

et al. 2022

Processes

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Temperature is one of the most important parameters in the combustion processes. Accurate surface temperature can help to gain insight into the combustion characteristics of various solid or liquid fuels, as well as to evaluate the operating status of combustion power facilities such as internal combustion engines and gas turbines. This paper mainly summarizes and compares the main surface thermometry techniques, from the aspects of their principles, current state of development, and specific applications. These techniques are divided into two categories: contact-based thermometry and non-intrusive thermometry. In contact-based thermometry, conventional thermocouples as well as thin-film thermocouples are introduced. These methods have been developed for a long time and are simple and economical. However, such methods have disadvantages such as interference to flow and temperature field and poor dynamic performance. Furthermore, this paper reviews the latest non-intrusive thermometry methods, which have gained more interest in recent years, including radiation thermometry, laser-induced phosphorescence, liquid crystal thermography, the temperature-sensitive paint technique, and the temperature-indicating paint technique. Among them, we highlighted radiation thermometry, which has the widest measurement ranges and is easy to acquire results with spatial resolution, as well as laser-induced phosphorescence thermometry, which is not interfered with by the emissivity and surrounding environment, and has the advantages of fast response, high sensitivity, and small errors. Particularly, laser-induced phosphoresce has attracted a great deal of attention, as it gets rid of the influence of emissivity. In recent years, it has been widely used in the thermometry of various combustion devices and fuels. At the end of this paper, the research progress of the above-mentioned laser-induced phosphorescence and other techniques in recent years for the surface thermometry of various solid or liquid fuels is summarized, as well as applications of combustion facilities such as internal combustion engines, gas turbines, and aero engines, which reveal the great development potential of laser-induced phosphorescence technology in the field of surface thermometry.

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Section: Temperature-indicating Paintmentioning

confidence: 99%

Review of Development and Comparison of Surface Thermometry Methods in Combustion Environments: Principles, Current State of the Art, and Applications

Liu

Huang

et al. 2022

Processes

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“…Complicating this thermal management method was the extensive use of 5 mm thick anodized aluminum as the main external shell of the vehicle that was unshrouded through the ascent phase. Furthermore, thermal-structural analysis of the HIFiRE-0 vehicle, another axisymmetric vehicle flying a similar trajectory to SCRAMSPACE, demonstrated that peak surface temperature on the vehicle occurs during the ascent phase of the flight [9]. Although the HiFIRE-0 vehicle incorporated an ogive fore section of roughly the same length as SCRAMSPACE, the material choice was different.…”

mentioning

confidence: 96%

“…Although the HiFIRE-0 vehicle incorporated an ogive fore section of roughly the same length as SCRAMSPACE, the material choice was different. For thermal management, HIFiRE-0 used a 135 mm long solid stainless-steel cone and a 1 mm thick stainless-steel ogive section that attached to a 5 mm thick aluminum cylindrical back can [9]. This design proved effective for thermal protection, although the question of the suitability of using only a 5 mm thick aluminum external shell for all vehicle locations remains.…”

mentioning

confidence: 97%

“…A number of methods to mitigate thermal loads and stresses on hypersonic vehicles exist, the most common of which are the use of exotic materials for thermal protection such as those on NASA's X34 [2] and Space Shuttle [3] vehicles and active cooling technologies [4][5][6]. Incorporating these, however, often comes at significant economic and packaging expense, and thus a third mechanism of passive cooling is becoming a more popular method of thermal management on hypersonic flight-test vehicles [7][8][9]. Passive cooling is an efficient thermal management system that can be used effectively on ballistic flight trajectories such as the fundamental science scramjet flight experiment SCRAMSPACE [10] and involves the selection and specification of common materials for airframe construction such that the thermal capacity of the vehicle itself is used as the thermal protection system [8].…”

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confidence: 99%

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Aerothermal–Structural Analysis of a Rocket-Launched Mach 8 Scramjet Experiment: Ascent

Capra

Brown

Boyce

et al. 2015

Journal of Spacecraft and Rockets

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This paper reports on the methodology and results of a weak-coupled aerothermal-structural analysis on the ascent phase of the SCRAMSPACE Mach 8 scramjet flight experiment. This vehicle was essentially unshrouded during the flight trajectory, relying on the thin, 5 mm thick aluminum external shell of the payload to maintain structural integrity and protect the flight experiment. As such, understanding the thermal-structural response of the vehicle was imperative to mission success. Using two-and three-dimensional models, an iterative procedure was employed to compute the flowfield, convective heating, wall temperatures and structural coupling at flight times covering both peak heating and peak surface temperature. Accounting for such coupling resulted in a 150 K reduction in wall temperature compared to the more conservative cold wall assumption. Despite this, peak temperatures remained of the order of 550 K. Further, thermally induced stresses within these regions were in excess of four times the material failure limits. Irreversible material failure during ascent was therefore concluded likely to occur on the external shell. Two alternate materials, steel 1006 and copper, were therefore assessed with the results indicating that steel sections on the external shell resulted in the best thermal-structural response of the payload. NomenclatureSubscripts amb = ambient r = radiative m = melting y = yield T = tensile 0 = initial

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Numerical tool for quantifying energy deposition effects on representative hypersonic vehicle structures

Moran

Capra

Neely

2021

Aerospace Science and Technology

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Measurement of Aerothermal Heating on HIFiRE-0

Cited by 9 publications

References 10 publications

Review of Development and Comparison of Surface Thermometry Methods in Combustion Environments: Principles, Current State of the Art, and Applications

Review of Development and Comparison of Surface Thermometry Methods in Combustion Environments: Principles, Current State of the Art, and Applications

Aerothermal–Structural Analysis of a Rocket-Launched Mach 8 Scramjet Experiment: Ascent

Numerical tool for quantifying energy deposition effects on representative hypersonic vehicle structures

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