Relevant bibliographies by topics / Hypervelocity impact

Academic literature on the topic 'Hypervelocity impact'

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Published: 4 June 2021
Last updated: 28 July 2024

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Journal articles on the topic "Hypervelocity impact"

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Williams, Andrew. "Hypervelocity Impact." Aerospace Testing International 2018, no. 4 (December 2018): 72–78. http://dx.doi.org/10.12968/s1478-2774(23)50186-1.

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Guan, Gong Shun, Bao Jun Bang, and Rui Tao Niu. "Investigation into Damage of AL-Mesh Bumper under Hypervelocity AL-Spheres Impact." Key Engineering Materials 488-489 (September 2011): 202–5. http://dx.doi.org/10.4028/www.scientific.net/kem.488-489.202.

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The aluminum mesh/plate bumper was designed by improving on AL-Whipple shield, and a series of hypervelocity impact tests were practiced with a two-stage light gas gun facility at Harbin Institute of Technology. Impact velocities of Al-spheres were varied between 3.5km/s and 5km/s. The diameters of projectiles were 3.97mm and 6.35mm respectively. The hypervelocity impact characteristics of 5052 aluminum alloy mesh bumper were studied through hypervelocity impact on aluminum mesh/plate bumpers. The fragmentation and dispersal of hypervelocity particle against mesh bumpers varying with material and specification were analyzed. It was found that the mesh wall position, diameter of wire and separation distance arrangement and mesh opening had high influence on the hypervelocity impact characteristic of aluminum mesh/plate shields. At similar impact velocity, hypervelocity impact characteristics comparison with aluminum sheet bumpers of equal areal mass was thrust. The optimized design idea of aluminum mesh/plate bumpers was suggested.
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McFarland, C., P. Papados, and M. Giltrud. "Hypervelocity impact penetration mechanics." International Journal of Impact Engineering 35, no. 12 (December 2008): 1654–60. http://dx.doi.org/10.1016/j.ijimpeng.2008.07.080.

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Drumheller, D. S. "Hypervelocity impact of mixtures." International Journal of Impact Engineering 5, no. 1-4 (January 1987): 261–68. http://dx.doi.org/10.1016/0734-743x(87)90043-1.

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Pozwolski, A. E. "Fusion by hypervelocity impact." Laser and Particle Beams 4, no. 2 (May 1986): 157–66. http://dx.doi.org/10.1017/s0263034600001725.

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The conversion of kinetic energy into heat is a possible approach to get the very high temperatures needed for controlled fusion. Various techniques leading to hypervelocities are considered. Some particular geometries and constitutions of liners allowing velocity amplification and superheating are described.
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Watson, E., H. G. Maas, F. Schäfer, and S. Hiermaier. "TRAJECTORY BASED 3D FRAGMENT TRACKING IN HYPERVELOCITY IMPACT EXPERIMENTS." ISPRS - International Archives of the Photogrammetry, Remote Sensing and Spatial Information Sciences XLII-2 (May 30, 2018): 1175–81. http://dx.doi.org/10.5194/isprs-archives-xlii-2-1175-2018.

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Collisions between space debris and satellites in Earth’s orbits are not only catastrophic to the satellite, but also create thousands of new fragments, exacerbating the space debris problem. One challenge in understanding the space debris environment is the lack of data on fragmentation and breakup caused by hypervelocity impacts. In this paper, we present an experimental measurement technique capable of recording 3D position and velocity data of fragments produced by hypervelocity impact experiments in the lab. The experimental setup uses stereo high-speed cameras to record debris fragments generated by a hypervelocity impact. Fragments are identified and tracked by searching along trajectory lines and outliers are filtered in 4D space (3D + time) with RANSAC. The method is demonstrated on a hypervelocity impact experiment at 3.2 km/s and fragment velocities and positions are measured. The results demonstrate that the method is very robust in its ability to identify and track fragments from the low resolution and noisy images typical of high-speed recording.
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Guan, Gong Shun, Bao Jun Pang, Run Qiang Chi, and Yao Zhu. "A Study of Damage in Aluminum Dual-Wall Structure by Hypervelocity Impact of AL-Spheres." Key Engineering Materials 324-325 (November 2006): 197–200. http://dx.doi.org/10.4028/www.scientific.net/kem.324-325.197.

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In order to simulate and study the hypervelocity impact of space debris on dual-wall structure of spacecrafts, firstly a non-powder two-stage light gas gun was used to launch AL-sphere projectiles. Damage modes in rear wall of dual-wall structure were obtained, and while the law of damage in rear wall depends on projectile diameter and impact velocity were proposed. Finally, numerical simulation method was used to study the law of damage in rear wall. By experiment and numerical simulation of hypervelocity impact on the dual-wall structure by Al-spheres, and it is found that AUTODYN-2D SPH is an effective method of predicting damage in rear wall from hypervelocity impact. By numerical simulation of projectile diameter, projectile velocity and the space between bumper and back wall effect on damage in rear wall by hypervelocity impact, and fitting curves with simulation results, the law of damage in rear wall and dominant factors effect damage in rear wall by hypervelocity impact were proposed.
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Guan, Gong Shun, Bao Jun Pang, Run Qiang Chi, and Nai Gang Cui. "Investigation into Damage of Aluminum Multi-Wall Shield under Hypervelocity Projectiles Impact." Key Engineering Materials 385-387 (July 2008): 201–4. http://dx.doi.org/10.4028/www.scientific.net/kem.385-387.201.

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In order to study the hypervelocity impact of space debris on spacecraft through hypervelocity impact on aluminum alloy multi-wall structure, a two-stage light gas gun was used to launch 2017-T4 aluminum alloy sphere projectiles. The projectile diameters ranged from 2.74mm to 6.35mm and impact velocities ranged from 1.91km/s to 5.58km/s. Firstly, the advanced method of multi-wall shield resisting hypervelocity impacts from space debris was investigated, and the effect of amount and thickness of wall on shield performance was discussed. Finally, by regression analyzing of experiment data, the experience equations for forecasting the diameter of the penetration hole on the first wall and the diameter of the damaged area on the second wall of aluminum multi-wall shield under hypervelocity normal impact of Al-spheres were obtained. The results indicated that the performance of multi-wall shield with more amount of wall is excellent when area density is constant. At the same time, intensity of the first wall and protecting space play the important roles.
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Sun, Yunhou, Cuncheng Shi, Zheng Liu, and Desheng Wen. "Theoretical Research Progress in High-Velocity/Hypervelocity Impact on Semi-Infinite Targets." Shock and Vibration 2015 (2015): 1–15. http://dx.doi.org/10.1155/2015/265321.

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With the hypervelocity kinetic weapon and hypersonic cruise missiles research projects being carried out, the damage mechanism for high-velocity/hypervelocity projectile impact on semi-infinite targets has become the research keystone in impact dynamics. Theoretical research progress in high-velocity/hypervelocity impact on semi-infinite targets was reviewed in this paper. The evaluation methods for critical velocity of high-velocity and hypervelocity impact were summarized. The crater shape, crater scaling laws and empirical formulae, and simplified analysis models of crater parameters for spherical projectiles impact on semi-infinite targets were reviewed, so were the long rod penetration state differentiation, penetration depth calculation models for the semifluid, and deformed long rod projectiles. Finally, some research proposals were given for further study.
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Saboktakin, Abbasali, and Christos Spitas. "Hypervelocity launchers for satellite structures orbital debris characterization." Aeronautics and Aerospace Open Access Journal 7, no. 1 (January 17, 2023): 1–5. http://dx.doi.org/10.15406/aaoaj.2022.07.00163.

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Orbital debris poses increasing threats to the space environment because of increasing space activities, therefore on-orbit hypervelocity impact should be simulated using the experiment by launch projectile into the target. Generally, ground-based experiments include three major sectors: projectile launch, impact monitoring including shock wave and debris cloud formation imaging, and finally result processing. For ground-based hypervelocity impact tests, various acceleration techniques such as light two and three-stage gas guns, plasma accelerators, electrostatic accelerators, and shaped charge accelerators have been used. This paper will primarily focus on those that are most relevant to current research on hypervelocity tests and would improve current research in the field of hypervelocity impact tests on composite material for primary satellite structures.
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Dissertations / Theses on the topic "Hypervelocity impact"

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Gardner, David John. "Hypervelocity impact morphology." Thesis, University of Kent, 1995. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.294316.

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Thurber, Andrew. "Investigations of Hypervelocity Impact Physics." Diss., Virginia Tech, 2014. http://hdl.handle.net/10919/95298.

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Spacecraft and satellites in orbit are under an increasing threat of impact from orbital debris and naturally occurring meteoroids. While objects larger than 10 cm are routinely tracked and avoided, collisions inevitably occur with smaller objects at relative velocities exceeding 10 km/s. Such hypervelocity impacts (HVI) create immense shock pressures and can melt or vaporize aerospace materials, even inducing brief plasmas at higher speeds. Sacrificial shields have been developed to protect critical components from damage under these conditions, but the response of many materials in such an extreme event is still poorly understood. This work presents the summary of computational analysis methods to quantify the relevant physical mechanisms at play in a hypervelocity impact. Strain rate-dependent behavior was investigated using several models, and fluid material descriptions were used to draw parallels under high shear rate loading. The production and expansion of impact plasmas were modeled and compared to experimental evidence. Additionally, a parametric study was performed on a multitude of possible material candidates for sacrificial shield design, and new shielding configurations were proposed. A comparison of material models indicated that the Johnson-Cook and Steinberg-Cochran-Guinan-Lund metallic formulations yielded the most consistent results with the lowest deviation from experimental measures in the strain rate regime of interest. Both meshless Lagrangian and quasi-Eulerian meshed schemes approximated the qualitative and quantitative characteristics of HVI debris clouds with average measurable errors under 5%. While the meshless methods showed better resolution of interfaces and small details, the meshed methods were shown to converge faster under several metrics with fewer regions of spurious instability. Additionally, a new technique was introduced using hypothetical viscous fluids to approximate debris cloud behavior, which showed good correlation to experimental results when such models were constructed using the shear rates seen in hypervelocity impacts. Formulations using non-Newtonian fluids showed additional capability in approximating solid behavior, both quantitatively and qualitatively. Such fluid models are significant, in that they reproduced the qualitative and quantitative characteristics of evolving debris clouds with better fidelity than purely hydrodynamic models using inviscid fluids. This indicates that while inertial effects can dominate overdriven shock phenomena, neglecting shear forces invariably introduces errors; such forces can instead be simplistically approximated via viscous models. The viscous approximation also allowed for a successful scaling analysis using dimensionless Pi terms, which was unfeasible using solid constitutive relations. Attempts to model plasma dynamics saw success in the simulation of a laser ablation-driven flyer plate by using a hot gas with solid initial conditions; similar strategies were used to analyze plasma production in hypervelocity impacts with reasonable correlation to experimental measurements. Lastly, the analysis of bumper material candidates showed that metals with a low density such as beryllium and magnesium yield a higher specific energy and momentum reduction of incident projectiles with lower weight requirements than a similarly constructed bumper using aluminum. Investigations of bumpers using a combination of materials and variations in microstructure showed promise in increasing weight-normalized efficacy. Through these computational models, the parameters which influence damage and debris in hypervelocity impacts are more critically understood.
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Milner, Daniel. "Laboratory simulations of oceanic hypervelocity impact events." Thesis, University of Kent, 2007. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.445726.

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Mann, Joanna. "The hypervelocity impact related aspects of Panspermia." Thesis, University of Kent, 2002. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.269100.

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Evans, S. T. "Hypervelocity impact studies on the Giotto comet Halley mission." Thesis, University of Kent, 1988. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.233399.

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Tsembelis, Kostantinos. "Elevated temperature measurements during a hypervelocity impact process." Thesis, University of Kent, 1998. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.285978.

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Campbell, J. "Lagrangian hydrocode modelling of hypervelocity impact on spacecraft." Thesis, Cranfield University, 1998. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.266986.

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Stucky, Michael S. "Analysis of the NASA shuttle hypervelocity impact database." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2003. http://library.nps.navy.mil/uhtbin/hyperion-image/03sep%5FStucky.pdf.

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Thesis (M.S. in Space Systems Operations)--Naval Postgraduate School, September 2003.
Thesis advisor(s): Eric Christiansen, Rudy Panholzer, Dan Bursch. Includes bibliographical references (p. 75-76). Also available online.
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Ryan, Shannon, and shannon ryan@studentems rmit edu au. "Hypervelocity Impact Induced Disturbances on Composite Sandwich Panel Spacecraft Structures." RMIT University. Aerospace, Mechanical & Manufacturing Engineering, 2007. http://adt.lib.rmit.edu.au/adt/public/adt-VIT20080808.092240.

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The next generation of European scientific satellites will carry extremely sensitive measurement devices that require platform stability orders of magnitude higher than current missions. It is considered that the meteoroid and space debris (M/SD) environment poses a risk to the success of these missions as disturbances induced by the impact of these particles at hypervelocity may degrade the platform stability below operational requirements. In this thesis, disturbances induced by the impact of M/SD particles at hypervelocity on a representative scientific satellite platform have been investigated. An extensive experimental impact test program has been performed, from which an empirical ballistic limit equation (BLE) which defines the conditions of structural perforation for composite sandwich panel structures with CFRP facesheets and aluminium honeycomb cores (CFRP/Al HC SP) has been defined. The BLE is used to predict impact conditions capable of inducing the different excitation modes relevant for a SP sandwich panel structure, enabling a significant reduction in the time and expense usually required for calibrating the protective capability of a new structural configuration. As experimental acceleration facilities are unable to cover the complete range of possible in-orbit impact conditions relevant for M/SD impact risk assessment, a Hydrocode model of the representative CFRP/Al HC SP has been constructed. A series of impact simulations have been performed during which the local impact-induced disturbance has been measured. The numerical disturbance signals have been validated via comparison with experimental disturbance measurements, and subsequently subject to a characterisation campaign to define the local elastic excitation of the SP structure equivalent to that induced by impact of a M/SD particle at hypervelocity. The disturbance characterisation is made such that it is applicable as an excitation force on a global satellite Finite Element (FE) model, allowing propagation of impact-induced disturbances throughout the complete satellite body to regions of critical stability (i.e. measurement devices). The disturbance induced upon measurement devices by M/SD impacts at both near- and far-body locations can then be made, allowing the threat to mission objectives to be assessed.
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Pasini, Luna. "Panspermia : the survival of micro-organisms during hypervelocity impact events." Thesis, University of Kent, 2017. https://kar.kent.ac.uk/67564/.

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The possible spread of life between planetary bodies has significant implications for any future discoveries of life elsewhere in the solar system, and for the origin of life on Earth itself. Litho-Panspermia proposes that life can survive the shock pressures associated with giant impacts which are sufficiently energetic to eject life into space. As well as this initial ejection, life must also survive the impact onto another planetary surface. The research presented shows that the micro-organisms Nannochloropsis oculata phytoplankton and tardigrade Hypsibius dujardini can be considered as viable candidates for panspermia. Using a Two-Stage Light Gas Gun, shot programmes were undertaken to impact frozen organisms at different velocities to simulate oceanic impacts from space. It is demonstrated that the organisms can survive a range of impact velocities, although survival rates decrease significantly at higher velocities. These results are explained in the context of a general model for survival after extreme shock, showing a two-regime survival with increasing shock pressure which closely follows the pattern observed in previous work on the survival of microbial life and spores exposed to extreme shock loading, where there is reasonable survival at low shock pressures, but a more severe lethality above a critical threshold pressure (a few GPa). Hydrocode modelling is then used to explore a variety of impact scenarios, and the results are compared with the experimental data during a thorough analysis of potential panspermia scenarios across the universe. These results are relevant to the panspermia hypothesis, showing that extreme shocks experienced during the transfer across space are not necessarily sterilising, and that life, could survive impacts onto other planetary bodies, thus giving a foothold to life on another world.
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Books on the topic "Hypervelocity impact"

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J, Bean Alan, Darzi Kent, University of Alabama in Huntsville. Dept. of Mechanical Engineering., George C. Marshall Space Flight Center., and United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., eds. Hypervelocity impact physics. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1991.

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Hypervelocity gouging impacts. Reston, Va: American Institute of Aeronautics and Astronautics, 2009.

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Wilbeck, J. S. Experience with techniques for characterizing debris generated during hypervelocity impact testing. Washington, D. C: American Institute of Aeronautics and Astronautics, 1992.

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K, Nahra Henry, and Lewis Research Center, eds. Hypervelocity impact testing of nickel hydrogen battery cells. [Cleveland, Ohio]: National Aeronautics and Space Administration, [Lewis Research Center, 1996.

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Piekutowski, A. J. Formation and description of debris clouds produced by hypervelocity impact. Huntsville, Ala: George C. Marshall Space Flight Center, 1996.

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Elfer, N. C. Structural damage prediction and analysis for hypervelocity impacts - handbook. Huntsville, Ala: George C. Marshall Space Flight Center, 1996.

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Stellingwerf, Robert Francis. Impact modeling with smooth particle hydrodynamics. Loa Alamos, NM: Los Alamos National Laboratory, 1993.

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Elfer, N. C. User's manual for space debris surfaces (SD_SURF). Huntsville, Alabama: George C. Marshall Space Flight Center, 1996.

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Manuelpillai, Gerald N. Space hypervelocity microparticle impact damage in polymer matrix composites. Ottawa: National Library of Canada, 1993.

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M, Curry Donald, and Lyndon B. Johnson Space Center., eds. Oxidation of reinforced carbon-carbon subjected to hypervelocity impact. Houston, Tex: National Aeronautics and Space Administration, Lyndon B. Johnson Space Center, 2000.

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Book chapters on the topic "Hypervelocity impact"

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Murr, Lawrence E. "Ballistic and Hypervelocity Impact and Penetration." In Handbook of Materials Structures, Properties, Processing and Performance, 801–62. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-01815-7_49.

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Murr, Lawrence E. "Ballistic and Hypervelocity Impact and Penetration." In Handbook of Materials Structures, Properties, Processing and Performance, 1–54. Cham: Springer International Publishing, 2014. http://dx.doi.org/10.1007/978-3-319-01905-5_49-1.

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Murr, Lawrence E. "Ballistic and Hypervelocity Impact and Penetration." In Handbook of Materials Structures, Properties, Processing and Performance, 1–53. Cham: Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-01905-5_49-2.

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Ando, H., H. Inoue, Y. Akahoshi, and S. Harada. "Molecular Dynamics Simulation of Hypervelocity Impact Problem." In Computational Mechanics ’95, 1870–75. Berlin, Heidelberg: Springer Berlin Heidelberg, 1995. http://dx.doi.org/10.1007/978-3-642-79654-8_312.

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Rein, Martin. "Maximum Pressures During Hypervelocity Liquid-Liquid Impact." In IUTAM Symposium on Waves in Liquid/Gas and Liquid/Vapour Two-Phase Systems, 191–200. Dordrecht: Springer Netherlands, 1995. http://dx.doi.org/10.1007/978-94-011-0057-1_15.

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Ren, Zoran, Matej Vesenjak, and Andreas Öchsner. "Behaviour of Cellular Structures under Impact Loading a Computational Study." In Explosion, Shock Wave and Hypervelocity Phenomena, 53–60. Stafa: Trans Tech Publications Ltd., 2007. http://dx.doi.org/10.4028/0-87849-465-0.53.

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Fang, H. Eliot. "Simulation of Hypervelocity Impact on Massively Parallel Supercomputer." In Computational Mechanics ’95, 1727–32. Berlin, Heidelberg: Springer Berlin Heidelberg, 1995. http://dx.doi.org/10.1007/978-3-642-79654-8_281.

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Hasebe, Tadashi, and Yutaka Imaida. "New Impact Testing Methods for Sheet Metals Based on SHPB Technique." In Explosion, Shock Wave and Hypervelocity Phenomena, 255–60. Stafa: Trans Tech Publications Ltd., 2007. http://dx.doi.org/10.4028/0-87849-465-0.255.

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Yamashita, Minoru, Tomohito Okuyama, Naoya Nishimura, and Toshio Hattori. "Control of Onset of Buckling Lobe in Axial Impact of Square Tube." In Explosion, Shock Wave and Hypervelocity Phenomena, 173–78. Stafa: Trans Tech Publications Ltd., 2007. http://dx.doi.org/10.4028/0-87849-465-0.173.

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Hiermaier, Stefan. "Hypervelocity Impact Induced ShockWaves and Related Equations of State." In Predictive Modeling of Dynamic Processes, 333–48. Boston, MA: Springer US, 2009. http://dx.doi.org/10.1007/978-1-4419-0727-1_18.

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Conference papers on the topic "Hypervelocity impact"

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Walker, James D., Sidney Chocron, and Donald J. Grosch. "Size scaling of crater size, ejecta mass, and momentum enhancement due to hypervelocity impacts into 2024-T4 and 2024-T351 aluminum." In 2019 15th Hypervelocity Impact Symposium. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/hvis2019-049.

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Abstract Momentum enhancement occurs when impactors strike objects at hypervelocities due to the formation of crater ejecta whose departure from the impact body impart more momentum to the impacted body. In previous work the momentum enhancement caused when metals, rock, and pumice were impacted have been examined [1-7]. Momentum enhancement is quantified by β, which is the ratio of the resulting target momentum by the impactor momentum. By quantifying momentum enhancement it is possible to make informed decisions about the use of hypervelocity impactors to deflect celestial bodies such as asteroids or comet nuclei.
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"HVIS2022 Front Matter." In 2022 16th Hypervelocity Impact Symposium. American Society of Mechanical Engineers, 2023. http://dx.doi.org/10.1115/hvis2022-fm1.

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Abstract This proceedings contains papers and extended abstracts from the 2022 Hypervelocity Impact Symposium (HVIS 2022) held in Alexandria, Virginia on September 18–22, 2012. This was the sixteenth symposium since the re-initiation of symposia related to hypervelocity impact in 1986. The proceedings for the previous fifteen symposia have been published as separate volumes of the International Journal of Impact Engineering and Procedia Engineering. Papers in this proceedings address advancements in the basic understanding of hypervelocity impact physics, related phenomenology, and engineering applications.
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Neel, Christopher, Peter Sable, Philip Flater, and David Lacina. "Conical impact fragmentation test (CIFT)." In 2019 15th Hypervelocity Impact Symposium. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/hvis2019-120.

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Abstract Conical impact fragmentation tests (CIFT) were conducted to develop and demonstrate an experimental capability for uniformly inducing controlled fragmentation in structural metals. The setup involves a conical specimen impacting a mating conical target (similar in geometry to a funnel) at nominal velocities of 1 - 2 km/s. Three experiments were conducted as proof of concept to characterize the fragmentation behavior of 1018 steel. Photonic Doppler velocimetry probes on the free outer surface of the target cone allow for validating simulations that can indicate strain uniformity in the target cone. Overall, experimental results demonstrate CIFT to be a feasible method to evaluate fragmentation behavior. The conical geometry produces consistent and bounded strain rates that are maintained for at least 10 microseconds. Furthermore, when compared with other laboratory techniques, the CIFT technique is shown to be more ideal than sphere-on-plate impact (SPI) and more tunable than cylinder expansion (CYLEX), and so is a promising fragmentation characterization tool.
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Tandy, Jon, Vassilia Spathis, and Luke Alesbrook. "Cryogenic Capture of Hypervelocity Impact Ejecta." In 2022 16th Hypervelocity Impact Symposium. American Society of Mechanical Engineers, 2022. http://dx.doi.org/10.1115/hvis2022-51.

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Abstract The capture of impact ejecta is an important tool for the evaluation of chemical modification caused by hypervelocity impact events. Traditional systems typically employ foils, foams or aerogel to capture fast moving ejecta for elemental analyses. These devices are less appropriate for the examination of more volatile components within impact ejecta and may even cause additional chemical reactions on their surface leading to uncertainties in the subsequent analyses. This is particularly disadvantageous for capture systems onboard spacecraft searching for biologically relevant molecules like amino acids. The preliminary design and testing of a cooled capture plate system utilizing a cryogenic cold finger for incorporation with the University of Kent’s two-stage light gas gun is outlined. Experiments using solid nylon sabots at a range of impact speeds were carried out with the majority of targets composed of a glycine-water ice mixture. A minimum capture plate temperature of -71 °C was achieved with an impact chamber pressure of 0.2 mbar but was observed to be closer to -30 oC during vacuum chamber evacuation using frozen targets due to sublimation of the ice’s surface. Shots at impact speeds greater than 6.3 km s-1 showed effective capture of small concentrations of glycine after derivatization and subsequent GC-MS analysis. The additional detection of glycolic acid within the captured material also suggests the potential for significant chemical modification within impact ejecta, which has important implications for the sampling of solar system plumes and surface material transferred across planetary bodies by hypervelocity impacts.
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Uhlig, W. Casey, Paul R. Berning, Peter T. Bartkowski, and Matthew J. Coppinger. "Electrically-Launched mm-sized Hypervelocity Projectiles." In 2019 15th Hypervelocity Impact Symposium. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/hvis2019-016.

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Abstract A series of experiments and simulations were performed as proof of concept that an electrically powered research gun could propel small cylindrical projectiles to hypervelocities. Although small-caliber electrothermal accelerators and other electromagnetic launch systems have been utilized for some years for laboratory hypervelocity impact and other studies [1-5], we developed a simple, reproducible device that allows impact studies and direct comparison to magnetohydrodynamic (MHD) simulations for design considerations, efficiency improvements, and validation studies. This work focusses on 4.8 mm cylindrical 7075-T6 aluminum projectiles with a length to diameter ratio of one (nominally a mass of 0.24 grams) and a 150-mm long, 25-mm outer-diameter 4043 steel barrel with a 4.8-mm diameter bore and 9.5-mm chamber that acts as the electrical cathode. The anode consists of a 6.3-mm diameter copper rod that is reduced to 2.9 mm then tapered to a point with the tip length over diameter ratio (L/D) varying from 2 to 5. The tip is placed at the chamber/bore junction. The copper anode is insulated by a polyethylene sleeve and epoxy surrounding the electrode such that the arc initiates only at the very tip. A 191 μF capacitor was used as the power source for all experiments. The applied voltage was varied from 10 kV to 20 kV, and the resulting inductance of the system varied from approximately 320 nH to 450 nH (due to varying separation in the copper transmission lines). Fits to the current pulse using an LRC circuit resulted in resistance on the order of 10 mΩ to 15 mΩ. Typically the portion of the electrical pulse responsible for the bulk of the acceleration of the projectile occurs within the first 15 μs; however, the projectile is accelerated during the entirety of the time it remains in the barrel, which is on the order of 40 μs to 50 μs.
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Crawford, David A. "Coils, Codes and Comets: My Attempts to Partially Understand Some Particular Aspects of Hypervelocity Impacts." In 2019 15th Hypervelocity Impact Symposium. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/hvis2019-dsa2017.

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Abstract At the time of this writing in 2019, I have been studying hypervelocity impacts for about 34 years. I attended my first Hypervelocity Impact Symposium in 1992. In this paper, I attempt to show what I’ve been up to all this time but also show some of the things I’ve learned along the way. I’ve singled out three topics that stand out in my mind as milestones in my career: the impact of Comet Shoemaker-Levy 9 on Jupiter in 1994, the development of adaptive mesh refinement for the CTH hydrocode in 1998-2001 and my ongoing studies of hypervelocity impact-generated magnetic fields from 1985 to the present day.
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Daly, R. Terik, Olivier S. Barnouin, Andrew M. Lennon, Angela M. Stickle, Emma S. Rainey, Carolyn M. Ernst, and Andrew A. Knuth. "The JHUAPL Planetary Impact Lab (PIL): Capabilities and initial results." In 2019 15th Hypervelocity Impact Symposium. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/hvis2019-084.

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Abstract The Planetary Impact Lab (PIL) at the Johns Hopkins University Applied Physics Laboratory (JHUAPL) includes a single-stage, compressed inert gas gun that can be used for impact experiments. The impact angle can be varied from 15° to 90° with respect to horizontal, a capability which enables oblique impacts into unconsolidated or granular materials (e.g., regolith analogs). The gun currently achieves impact velocities up to 400 m/s, although future enhancements could increase the maximum projectile velocity. Experiments can be done with atmospheric pressures ranging from ambient pressure down to ~75 Pa. The gun uses sabots produced with state-of-the-art additive manufacturing techniques (AM). Several engineering challenges had to be overcome to create a reliable AM sabot; however, AM sabots are ~45% lighter than and provide substantial cost savings over machined sabots. The PIL gun is currently being used to investigate impact processes on sloped coarse-grained surfaces, with application to planetary science and, specifically, rubble-pile asteroids. In contrast to previous studies of impacts onto slopes, we kept the projectile trajectory perpendicular to the target surface, thereby disentangling the effects of oblique impacts from the effects caused by a sloped surface. Initial results show enhanced crater collapse in the sloped target, with most of the collapse occurring in the direction parallel to the surface gradient. Consequently, final craters on sloped targets have smaller volumes and reduced depth-to-diameter ratios.
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XING, Boyang, Yunhui HOU, Zhenyan GUO, Dongjiang ZHANG, Liang CHEN, Yongliang Yang, Jianhua Luo, Rongzhong LIU, and Rui GUO. "Analysis of the distribution of BAD generated during the normal penetration of a variable cross-section EFP on RHA." In 2019 15th Hypervelocity Impact Symposium. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/hvis2019-003.

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Abstract The purpose of this study is to analyse how the thickness of Rolled Homogeneous Armor (RHA) and impact velocity of an Explosively Formed Projectile (EFP) influence the middle mass behind-armor debris (BAD) when a variable cross-section EFP penetrates RHA normally. Numerical simulation is adopted, the thickness of RHA varies from 10mm to 70mm, and the impact velocity of the EFP varies from 1650m/s to 1860m/s. The results indicate that: (1) when the impact velocity of the EFP is 1650m/s and the thickness of RHA varies from 10mm to 70mm, p1g of the RHA and EFP decreases with increasing H0. The thin target could be used to produce a large proportion of the middle mass BAD from RHA (including BAD from the EFP and BAD from the RHA and EFP). (2) When the impact velocity of the EFP varies from 1650m/s to 1860m/s and the thickness of the RHA is 40mm, p1g of the RHA is less than 50%, p1g of the EFP is more than 70%, and p1g of the RHA and EFP is more than 50%.
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Sweitzer, Justin C., Nicholas Peterson, and Scott Hill. "Calculation of jet characteristics from hydrocode analysis." In 2019 15th Hypervelocity Impact Symposium. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/hvis2019-004.

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Abstract The penetration performance of a shaped charge jet is affected strongly by factors such as straightness, stretch rate, and breakup time. Straightness is related to manufacturing tolerances, assembly techniques, and system integration features. Stretch rate and breakup time are controllable features of charge design. A higher stretch rate is desirable for short standoff performance. The stretch rate is easily altered by a change of explosive or modification of the angle with which the detonation wave sweeps the liner surface, however, an increased stretch rate generally results in a decreased breakup time. Many of the recent gains in shaped charge performance have been made possible by increasing the effective breakup time of the jet. Several models exist for calculating breakup time. They include analytic models, such as Chou & Carleone’s dimensionless strain rate model, and empirical or semi-empirical models such as Walsh’s theory and those proposed by Pearson, et al. These models can be applied to raw hydrocode calculation data and used to determine a Jet Characterization (JC) file. The JC file can then be used to perform further calculations, such as Penetration Versus Stand Off (PVSO) curves. This paper details adaptation of the Chou & Carleone model for predicting breakup time using hydrocode data. The hydrocode is used to determine the physical parameters of the jet which are then extrapolated back to a virtual origin for breakup time calculation. This results in a model that is design independent, relying on hydrocode determination of jet variables. The model implementation will be discussed, and comparisons of predicted jet characteristics will be made to test data for several charge geometries.
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Thomas, Sarah A., Robert S. Hixson, M. Cameron Hawkins, and Oliver T. Strand. "Wave speeds in single-crystal and polycrystalline copper." In 2019 15th Hypervelocity Impact Symposium. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/hvis2019-007.

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Abstract While the equation of state for copper has been fairly well studied, wave speeds at low stress are not as well known. Systematic errors may be present in the lowest stress data presented in the Marsh [1] compendium due to the use of the flash gap method to collect the data. Additionally, little data has been gathered on the wave speeds in single-crystal copper, which may vary from polycrystalline due to the different longitudinal and shear sound speeds. Hugoniot information at low pressures is useful in constraining and improving predictive hydrodynamic codes. Knowledge of single-crystal behavior provides input for mesoscale computer models that use tens-of-micron-sized grains of single crystals to build a model of polycrystalline systems. We undertook experiments to measure wave speeds in polycrystalline and single-crystal copper at low pressures using a novel technique to limit error, and to determine if single-crystal shock velocities are systematically different than polycrystalline shock velocities at the same stress. The best previous research on this topic is from Chau et al. [2] at relatively high shock stress; they reported no observed difference between orientations. It is of interest to do careful measurements at low stress, and that is the principal goal of this work.
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Reports on the topic "Hypervelocity impact"

1

Elschot, Sigrid, and Nicolas Lee. Simulations of Hypervelocity Impact Plasmas. Office of Scientific and Technical Information (OSTI), August 2023. http://dx.doi.org/10.2172/1996424.

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Reinhart, William Dodd, and Lalit C. Chhabildas. Hypervelocity impact technology and applications: 2007. Office of Scientific and Technical Information (OSTI), July 2008. http://dx.doi.org/10.2172/942194.

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Canavan, G. H. Analysis of hypervelocity impact test data. Office of Scientific and Technical Information (OSTI), January 1998. http://dx.doi.org/10.2172/663194.

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Chhabildas, Lalit Chandra, and Dennis L. Orphal. Survey of the hypervelocity impact technology and applications. Office of Scientific and Technical Information (OSTI), May 2006. http://dx.doi.org/10.2172/887254.

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Brewer, E. D., W. R. Hendrich, D. G. Thomas, and J. E. Smith. Effects of oblique impact on hypervelocity shield performance. Office of Scientific and Technical Information (OSTI), January 1990. http://dx.doi.org/10.2172/5041143.

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Sheaffer, Patti M., Paul M. Adams, Naoki Hemmi, and Christopher Hartney. DebrisLV Hypervelocity Impact Post-Shot Physical Results Summary. Fort Belvoir, VA: Defense Technical Information Center, February 2015. http://dx.doi.org/10.21236/ada625015.

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Lu, Ping, David B. Doman, and John D. Schierman. Adaptive Terminal Guidance for Hypervelocity Impact in Specified Direction. Fort Belvoir, VA: Defense Technical Information Center, January 2006. http://dx.doi.org/10.21236/ada445166.

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Orlov, Dmitri. Hypervelocity impact in stellar media: heat shielding, shock fronts and ablation clouds. Office of Scientific and Technical Information (OSTI), October 2023. http://dx.doi.org/10.2172/2203698.

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Thornhill, Tom Finley, III, William Dodd Reinhart, Raymond Jeffery Jr Lawrence, Lalit Chandra Chhabildas, and Daniel P. Kelly. Hypervelocity impact flash for missile-defense kill assessment and engagement analysis : experiments on Z. Office of Scientific and Technical Information (OSTI), July 2005. http://dx.doi.org/10.2172/923158.

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Zielinski, Alexander E., and Graham F. Silsby. Hypervelocity Penetration Impacts in Concrete Targets. Fort Belvoir, VA: Defense Technical Information Center, September 1999. http://dx.doi.org/10.21236/ada368858.

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