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Transpiration Cooling Using Porous Material for Hypersonic Applications
Published in Yasser Mahmoudi, Kamel Hooman, Kambiz Vafai, Convective Heat Transfer in Porous Media, 2019
Adriano Cerminara, Ralf Deiterding, Neil D. Sandham
Hypersonic flight is characterized by very high values of temperature and heat flux reached at the wall, which can compromise the structural integrity of the vehicle. This is due to the large amount of kinetic energy converted into thermal energy by the shock forming in front of the body and by viscous effects inside the boundary layer. This produces high temperature peaks inside the boundary layer at small normal distances from the wall, which results in a high wall heat flux. Aerodynamic heating due to viscous effects inside the boundary layer is the main source of wall heating over most of the surface of slender bodies (e.g., cruise vehicles) flying at hypersonic speeds. The leading-edge region near the stagnation point is, in contrast, linked to the high temperatures reached at the edge of the boundary layer due to the front shock. This is the primary form of heating in the case of blunt bodies, such as the reentry capsules. For a reentry vehicle flying at a Mach number of 36, for example, as in the case of the Apollo reentry capsule, the temperature in the shock layer in front of the nose can reach values as high as 11,000 K (Anderson Jr., 2006).
Satellites
Published in Michael M. A. Mirabito, Barbara L. Morgenstern, Mitchell Kapor, The New Communications Technologies, 2004
Michael M. A. Mirabito, Barbara L. Morgenstern, Mitchell Kapor
The X-30 is also a hypersonic flight vehicle, as are other, more recent NASA technology and flight demonstrators, including the Hyper-X series. As envisioned, this new generation of vehicle would “routinely fly about 100,000 feet above Earth’s surface and reach sustained travel speeds in excess of Mach 5, or 3750mph—the point which ‘supersonic’ flight becomes ‘hypersonic’ flight.”28 Projected applications for such vehicles, if and when operational, could include retrieving low orbit satellites and servicing the space station.29 Another spinoff is more down to Earth. New airliners based on this concept could carry passengers between cities faster, for example, in one route from Los Angeles to Sydney, Australia, in 2.5 rather than 13.5 hours.30
Ceramics and Composites
Published in Yip-Wah Chung, Monica Kapoor, Introduction to Materials Science and Engineering, 2022
Refractory ceramics such as HfC, TaC, and their respective carbo-nitrides were recently shown to have the highest melting points of any compound, approximately 4000°C. Even though these ceramics were discovered almost 50 years ago, techniques to reliably measure their high melting points were only recently developed. These high-melting-point ceramic materials are potentially enablers of hypersonic flight, as current heat-shield materials cannot withstand temperatures generated due to the friction between the hypersonic vehicle surface and the atmosphere.
HALO3D: An All-Mach Approach to Hypersonic Flows Simulation
Published in International Journal of Computational Fluid Dynamics, 2022
Vincent Casseau, Wenbo Zhang, Shrutakeerti Mallikarjun, Wagdi G. Habashi, Song Gao, Abolfazl Karchani
A several-fold increase in air-space transportation speed would enable a whole new ecosystem to develop around the idea that distance and time are no longer constraining factors to point-to-point travel on Earth. This is the prospect brought by the re-emergence of higher-speed technology programmes with space agencies and companies strenuously pushing new boundaries to be leaders in this billion-dollar market. Defined as travel at speeds greater than Mach 5 below the Kármán line, hypersonic flight is of benefit to space exploration, exploitation, tourism, and civilian and cargo transportation, whose economical sustainability heavily relies upon reliability, operational efficiency, and re-usability (Erbland 2004): Space X's Falcon 9 rocket being the first of such transportation systems to be profitable – although being only partially-reusable. These three pillars are now part of the specifications adopted by most planned launch vehicles and spaceplanes, as exemplified by Space X's Starship, Blue Origin's New Glenn, Hermeus’ Quarterhorse Mach 5 jet, NASA–Lockheed Martin's X-59 QueSST demonstrator, JAXA's Sky Frontier hypersonic research programme, and numerous supersonic vehicles from companies such as Aerion, Boom Supersonic, Spike Aerospace, and Virgin Galactic, to name a few.
Computational Study of Hypersonic Rarefied Gas Flow over Re-Entry Vehicles Using the Second-Order Boltzmann-Curtiss Constitutive Model
Published in International Journal of Computational Fluid Dynamics, 2021
Tushar Chourushi, Satyvir Singh, Vishnu Asokakumar Sreekala, Rho Shin Myong
With the introduction of commercial space operations, rapid advances are occurring in space flight, space exploration, and the development of recyclable spacecraft re-entry vehicles. The growing interest in hypersonic re-entry flight has motivated several research groups around the world to investigate the physics of hypersonic gas flows. Compared to traditional flight vehicles, hypersonic flight vehicles have a much larger flight envelope and undergo drastic changes in aerothermodynamic forces as they descend through atmospheric layers. Accordingly, understanding near- and highly non-equilibrium gas flows around the vehicle is crucial to designing high-performance hypersonic re-entry vehicles, and for risk management of mission failure. To date, accurately predicting aerothermodynamic loads on hypersonic vehicles has been one of the most challenging tasks, due to the poor understanding of high-temperature non-equilibrium flow physics and limited ground test facilities (Tsai et al. 2009; Schwartzentruber and Boyd 2015; Schouler, Prévereaud, and Mieussens 2020). Numerical modeling and simulation have subsequently become effective tools for studying the flow characteristics in hypersonic regimes (Hash et al. 2007; Li and Zhang 2009; Peng et al. 2016; Liang et al. 2018; Chinnappan, Malaikannan, and Kumar 2017; Chae et al. 2020; Mankodi, Bhandarkar, and Myong 2020; de Góes Maciel 2015; Noori and Karimian 2008; Sawley and Wüthrich 1995).
Fault diagnosis and accommodation with flight control applications
Published in Journal of Control and Decision, 2020
Bin Jiang, Ke Zhang, Chun Liu, Hao Yang
Fault diagnosis and accommodation has been widely applied in flight control systems, especially in the control fields of hypersonic vehicles, spacecrafts and helicopters. Hypersonic flight vehicles are new kinds of aircrafts that are able to attain a supersonic speed cruising for some specific missions, and they have significant value in both military and civil applications. Spacecraft has been widely used in accomplishing modern space missions, such as earth monitoring and in-orbit servicing. Helicopters have a distinct advantage over fixed-wing aircrafts, especially in supervision and reconnaissance, search and rescue, and wildlife observation. Because of these clear benefits, the flight control of hypersonic vehicle, spacecraft and helicopter has received considerable attention, and many effective methods have been proposed in the past few years. A classification diagram of fault diagnosis and FA with flight control applications is illustrated in Figure 4.