Journal articles: 'Hypervelocity impact'

1

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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5

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&thinsp;+&thinsp;time) with RANSAC. The method is demonstrated on a hypervelocity impact experiment at 3.2&thinsp;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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9

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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10

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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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.2023.07.00163.

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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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12

Guan, Gong Shun, Qiang Bi, and Yu Zhang. "Research of Performance about Ceramic Coating on Aluminum Bumper to Resist Hypervelocity Impact." Key Engineering Materials 577-578 (September 2013): 629–32. http://dx.doi.org/10.4028/www.scientific.net/kem.577-578.629.

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Shield structure based on ceramic coating on aluminum bumper was designed, and a series of hypervelocity impact tests were practiced with a two-stage light gas gun facility. Impact velocities were varied between1.5km/s and 5.0km/s. The diameter of projectiles were 3.97mm and 6.35mm respectively. The impact angle was 0°. The damage of the ceramic coating on aluminum bumper under hypervelocity impact was studied. It was found that the ceramic coating on aluminum bumper could help enhancing the protection performance of shield to resist hypervelocity impact. The results indicated when the ceramic coating is on the front side of aluminum bumper, it was good for comminuting projectile and weakening the kinetic energy of projectile. For a certain aluminum bumper, existing a critical thickness of ceramic coating in which capability of Whipple shield to resist hypervelocity impact is the best. On this basis, the proposal of the optimum design for ceramic coating on aluminum bumper was made.

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13

Ma, Wen Lai, Wei Zhang, and Bao Jun Pang. "Simulation of Characteristics of Debris Cloud Produced by Hypervelocity Impact." Advanced Materials Research 940 (June 2014): 300–305. http://dx.doi.org/10.4028/www.scientific.net/amr.940.300.

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All spacecraft in low orbit are subject to hypervelocity impacts by meteoroids and space debris. These impacts can damage spacecraft flight-critical systems, which can in turn lead to catastrophic failure of the spacecraft. The numerical simulations of characteristics of debris cloud produced by an aluminum sphere projectile hypervelocity impact on different material bumpers at normal incidence have been carried out by using the SPH (smoothed particle hydrodynamics) technique. The effects of impact velocity, the ratio t/d of the bumper thickness to the projectile diameter and the bumper materials on the debris cloud characteristics are presented.

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14

Tennyson, R. C., and C. Lamontagne. "Hypervelocity impact damage to composites." Composites Part A: Applied Science and Manufacturing 31, no. 8 (August 2000): 785–94. http://dx.doi.org/10.1016/s1359-835x(00)00029-4.

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15

Sil'verstrov, V. V., A. V. Plastinin, and N. N. Gorshkov. "Hypervelocity impact against glass-textolite." Combustion, Explosion, and Shock Waves 31, no. 3 (1995): 352–61. http://dx.doi.org/10.1007/bf00742682.

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16

Walker, James D., and Sidney Chocron. "Momentum enhancement in hypervelocity impact." International Journal of Impact Engineering 38, no. 6 (June 2011): A1—A7. http://dx.doi.org/10.1016/j.ijimpeng.2010.10.026.

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17

Weng, Xiaowei, and Ching H. Yew. "Hypervelocity impact of two spheres." International Journal of Impact Engineering 8, no. 3 (January 1989): 229–40. http://dx.doi.org/10.1016/0734-743x(89)90004-3.

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18

Westine, Peter S., and Scott A. Mullin. "Scale modeling of hypervelocity impact." International Journal of Impact Engineering 5, no. 1-4 (January 1987): 693–701. http://dx.doi.org/10.1016/0734-743x(87)90084-4.

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19

Rivas, J. M., S. A. Quinones, and L. E. Murr. "Hypervelocity impact cratering: Microstructural characterization." Scripta Metallurgica et Materialia 33, no. 1 (July 1995): 101–7. http://dx.doi.org/10.1016/0956-716x(95)00105-5.

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20

Kozhushko, A. A., and A. B. Sinani. "Hypervelocity impact for brittle targets." International Journal of Impact Engineering 29, no. 1-10 (December 2003): 391–96. http://dx.doi.org/10.1016/j.ijimpeng.2003.09.035.

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21

Malaspina, David M., Guillermo Stenborg, Doug Mehoke, Adel Al-Ghazwi, Mitchell M. Shen, Hsiang-Wen Hsu, Kaushik Iyer, Stuart D. Bale, and Thierry Dudok de Wit. "Clouds of Spacecraft Debris Liberated by Hypervelocity Dust Impacts on Parker Solar Probe." Astrophysical Journal 925, no. 1 (January 1, 2022): 27. http://dx.doi.org/10.3847/1538-4357/ac3bbb.

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Abstract Hypervelocity impacts on spacecraft surfaces produce a wide range of effects including transient plasma clouds, surface material ablation, and for some impacts, the liberation of spacecraft material as debris clouds. This study examines debris-producing impacts on the Parker Solar Probe spacecraft as it traverses the densest part of the zodiacal cloud: the inner heliosphere. Hypervelocity impacts by interplanetary dust grains on the spacecraft that produce debris clouds are identified and examined. Impact-generated plasma and debris strongly perturb the near-spacecraft environment, producing distinct signals on electric, magnetic, and imaging sensors, as well as anomolous behavior of the star tracker cameras used for attitude determination. From these data, the spatial distribution, mass, and velocity of impactors that produce debris clouds are estimated. Debris-cloud expansion velocity and debris fragment sizes are constrained by the observational data, and long-duration electric potential perturbations caused by debris clouds are reported, along with a hypothesis for their creation. Impact-generated plasma-cloud expansion velocities, as well as pickup acceleration by the solar wind and driven plasma waves are also measured. Together, these observations produce a comprehensive picture of near-spacecraft environmental perturbations in the aftermath of a hypervelocity impact.

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22

Zhou, Hao, Rui Guo, and Rongzhong Liu. "Protection properties of stuffed corrugated sandwich structures under hypervelocity impact: Numerical simulation." Journal of Sandwich Structures & Materials 21, no. 2 (March 16, 2017): 532–51. http://dx.doi.org/10.1177/1099636217697493.

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The stuffed corrugated sandwich structure was proposed for the application in the protection of the spacecraft against orbital debris. In order to investigate the protection properties of the stuffed corrugated sandwich structure under hypervelocity impact, numerical simulations were carried out to analyze the impact characteristics. The hypervelocity impact process was presented and the properties such as shock waves propagation, energy absorption, and expansion of the debris cloud were discussed; corresponding properties of mass equal Whipple structure under impact were analyzed for comparison. The results illustrate the protection mechanism of the stuffed corrugated sandwich subject to hypervelocity impact and show that it has superior protection performance to monolithic plate, which prove that the stuffed corrugated sandwich structure has potentially broad application prospect in the field of spacecraft protection against the orbital debris. The research can provide reference for the design of protection shield of the spacecraft.

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23

SHIRAKI, Kuniaki, Tetsuji ITOH, Naoki SATOH, and Yujiro SHIRAI. "The Result of Hypervelocity Impact Tests." Journal of the Japan Society for Aeronautical and Space Sciences 44, no. 512 (1996): 520–29. http://dx.doi.org/10.2322/jjsass1969.44.520.

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24

Holian, Brad Lee. "Hypervelocity-impact phenomena via molecular dynamics." Physical Review A 36, no. 8 (October 1, 1987): 3943–46. http://dx.doi.org/10.1103/physreva.36.3943.

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25

Laird, David J., and Anthony N. Palazotto. "Gouge development during hypervelocity sliding impact." International Journal of Impact Engineering 30, no. 2 (February 2004): 205–23. http://dx.doi.org/10.1016/s0734-743x(03)00059-9.

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26

Littlefield, David L. "ANEOS extensions for modeling hypervelocity impact." International Journal of Impact Engineering 20, no. 6-10 (January 1997): 533–44. http://dx.doi.org/10.1016/s0734-743x(97)87442-8.

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27

Osinski, Gordon R., Richard A. F. Grieve, Jacob E. Bleacher, Catherine D. Neish, Eric A. Pilles, and Livio L. Tornabene. "Igneous rocks formed by hypervelocity impact." Journal of Volcanology and Geothermal Research 353 (March 2018): 25–54. http://dx.doi.org/10.1016/j.jvolgeores.2018.01.015.

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28

Watson, Erkai, Max Gulde, and Stefan Hiermaier. "Fragment Tracking in Hypervelocity Impact Experiments." Procedia Engineering 204 (2017): 170–77. http://dx.doi.org/10.1016/j.proeng.2017.09.770.

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29

Sabath, D., and K. G. Paul. "Hypervelocity impact experiments on tether materials." Advances in Space Research 20, no. 8 (January 1997): 1433–36. http://dx.doi.org/10.1016/s0273-1177(97)00410-9.

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30

Bjorkman, Michael D., and Eric L. Christiansen. "Hypervelocity Impact of Explosive Transfer Lines." Procedia Engineering 58 (2013): 177–83. http://dx.doi.org/10.1016/j.proeng.2013.05.021.

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31

Lawrence, R. J., W. D. Reinhart, L. C. Chhabildas, and T. F. Thornhill. "Spectral measurements of hypervelocity impact flash." International Journal of Impact Engineering 33, no. 1-12 (December 2006): 353–63. http://dx.doi.org/10.1016/j.ijimpeng.2006.09.010.

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32

Higashide, M., M. Tanaka, Y. Akahoshi, S. Harada, and F. Tohyama. "Hypervelocity impact tests against metallic meshes." International Journal of Impact Engineering 33, no. 1-12 (December 2006): 335–42. http://dx.doi.org/10.1016/j.ijimpeng.2006.09.071.

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33

Klopp, R. W., D. A. Shockey, J. E. Osher, and H. H. Chau. "Characteristics of hypervelocity impact debris clouds." International Journal of Impact Engineering 10, no. 1-4 (January 1990): 323–35. http://dx.doi.org/10.1016/0734-743x(90)90069-8.

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34

Ang, J. A., B. D. Hansche, C. H. Konrad, W. C. Sweatt, S. M. Gosling, and R. J. Hickman. "Pulsed holography for hypervelocity impact diagnostics." International Journal of Impact Engineering 14, no. 1-4 (January 1993): 13–24. http://dx.doi.org/10.1016/0734-743x(93)90005-r.

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35

Holssaple, K. A. "Hypervelocity impact experiments in surrogate materials." International Journal of Impact Engineering 14, no. 1-4 (January 1993): 335–45. http://dx.doi.org/10.1016/0734-743x(93)90032-3.

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36

Fahrenthold, E. P., and C. H. Yew. "Hydrocode simulation of hypervelocity impact fragmentation." International Journal of Impact Engineering 17, no. 1-3 (January 1995): 303–10. http://dx.doi.org/10.1016/0734-743x(95)99856-m.

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37

Fortov, V. E., T. P. Novikova, A. N. Lebedev, G. S. Romanov, V. A. Skvortsov, and A. V. Teterev. "Hypervelocity impact fusion of heavy clusters." International Journal of Impact Engineering 17, no. 1-3 (January 1995): 323–28. http://dx.doi.org/10.1016/0734-743x(95)99858-o.

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38

Silvestrov, V. V., A. V. Plastinin, and N. N. Gorshkov. "Hypervelocity impact on laminate composite panels." International Journal of Impact Engineering 17, no. 4-6 (January 1995): 751–62. http://dx.doi.org/10.1016/0734-743x(95)99897-z.

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39

Browning, J. A. "Hypervelocity impact fusion—a technical note." Journal of Thermal Spray Technology 1, no. 4 (December 1992): 289–92. http://dx.doi.org/10.1007/bf02647155.

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40

Stilp, A. J. "Review of modern hypervelocity impact facilities." International Journal of Impact Engineering 5, no. 1-4 (January 1987): 613–21. http://dx.doi.org/10.1016/0734-743x(87)90076-5.

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41

NISHIDA, Masahiro. "Ejecta Size Distribution by Hypervelocity Impact." Review of High Pressure Science and Technology 24, no. 1 (2014): 29–34. http://dx.doi.org/10.4131/jshpreview.24.29.

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42

KAWAI, Nobuaki. "Hypervelocity-Impact Damage of Ceramic Materials." Review of High Pressure Science and Technology 24, no. 1 (2014): 4–12. http://dx.doi.org/10.4131/jshpreview.24.4.

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43

Burchell, M. J., W. Brooke-Thomas, J. Leliwa-Kopystynski, and J. C. Zarnecki. "Hypervelocity Impact Experiments on Solid CO2Targets." Icarus 131, no. 1 (January 1998): 210–22. http://dx.doi.org/10.1006/icar.1997.5857.

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44

Burchell, M. "Survivability of Bacteria in Hypervelocity Impact." Icarus 154, no. 2 (December 2001): 545–47. http://dx.doi.org/10.1006/icar.2001.6738.

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45

Lin, Min, Bao Jun Pang, and Jin Cheng. "Experimental and Numerical Study on the Mesh Bumper by Hypervelocity Impact." Advanced Materials Research 457-458 (January 2012): 108–12. http://dx.doi.org/10.4028/www.scientific.net/amr.457-458.108.

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In order to systematically explore the properties of the mesh bumper under hypervelocity impact, the quantitative research of protect characteristics was carried out with the numerical simulation. The experiments, in which the projectile impacted the multi-layers mesh bumper at hypervelocity, were simulated using the Ls-Dyna hydro-codes. The results for simulations and experiments were compared and analyzed. The effectiveness and accuracy of the simulation model is proved. It is shown that the morphologies of debris cloud were obviously varied with the change of impact position.

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46

Zhou, Hui Lin, Hui Yong Yu, and Ming Hua Pang. "The Theories and Application of Numerical Simulation with Smoothed Particle Hydrodynamics Method." Key Engineering Materials 531-532 (December 2012): 695–98. http://dx.doi.org/10.4028/www.scientific.net/kem.531-532.695.

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The Smoothed Particle Hydrodynamics (SPH) method is a very important method to resolve hypervelocity problems and the basic theory of SPH method is introduced here. Then the three dimensional hypervelocity impact problems are simulated by using the model of chair. The results of SPH analysis show that (SPH) method is a numerical calculation method to resolve hypervelocity problems without mesh model but the particle model must be getting to calculate and the program code is less than other method. By analysis the results of the simulation is reasonable and very similar to the test result. It can be concluded that the advantages of SPH demonstrated make it a good and an ideal method to simulate the impact problem and other problems.

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47

Guan, Gong Shun, Dong Dong Pu, and Yue Ha. "Investigation into Damage of Stainless Steel Mesh/ALPlate Multi-Shock Shield under Hypervelocity AL-Spheres Impact." Key Engineering Materials 525-526 (November 2012): 397–400. http://dx.doi.org/10.4028/www.scientific.net/kem.525-526.397.

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A series of hypervelocity impact tests on stainless steel mesh/aluminum plate multi-shock shield were practiced with a two-stage light gas gun facility. Impact velocity was approximately 4km/s. The diameter of projectiles was 6.4mm. The impact angle was 0°. The fragmentation and dispersal of hypervelocity particle against stainless steel mesh bumper varying with mesh opening size and the wire diameter were investigated. It was found that the mesh wall position, diameter of wire, separation distance arrangement and mesh opening had high influence on the hypervelocity impact characteristic of stainless steel mesh/aluminum plate multi-shock shields. When the stainless steel mesh wall was located in the first wall site of the bumper it did not help comminuting and decelerating projectile. When the stainless steel mesh wall was located in the last wall site of the bumper, it could help dispersing debris clouds, reducing the damage of the rear wall. Optimized design idea of stainless steel mesh/aluminum plate multi-shock shields was suggested.

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48

Zhang, Q. D., H. D. Yan, Z. Z. Xie, and Y. F. Yu. "Experimental study on Hugoniot parameters of U71Mn steel under high pressure." Journal of Physics: Conference Series 2478, no. 8 (June 1, 2023): 082010. http://dx.doi.org/10.1088/1742-6596/2478/8/082010.

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Abstract The Hugoniot parameters of U71Mn steel under high pressure were studied by hypervelocity impact test of U71Mn steel with two-stage light gas gun. The plate impact test of U71Mn steel sample was carried out by means of symmetrical impact. The minimum impact speed was 1.843km/s and the maximum impact speed was 5.018km/s. The Hugoniot relation and Hugoniot parameter C and λ, then the accuracy of Hugoniot parameters of U71Mn steel under high pressure is verified according to Hugoniot equation of state (the relationship curve between impact pressure and density). The research results can provide reference for the application of U71Mn steel in the field of hypervelocity impact.

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49

Добрица, Д. Б., Б. Ю. Ященко, Ю. Ф. Христенко, and С. В. Пашков. "Experimental study of the resistance of corrugated mesh micrometeoroid/orbital debris shields." Вестник НПО им. С.А. Лавочкина, no. 1(51) (March 25, 2021): 24–32. http://dx.doi.org/10.26162/ls.2021.51.1.004.

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50

Yin, Jun, Yu Wang Yang, Xia Yun Hu, and Cheng Cheng Yong. "A Hypervelocity Impact Facilities Based on Double-Barreled Two-Stage Light Gas Gun." Advanced Materials Research 834-836 (October 2013): 825–28. http://dx.doi.org/10.4028/www.scientific.net/amr.834-836.825.

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For almost all materials the hypervelocity regime has been reached when the impact speed above 2 km/s. A double-barreled two-stage light gas gun (TSLGG) system used for the hypervelocity impact tests is described. The proposed TSLGG can accelerate 50 g projectile masses up to velocities of 2.2 km/s. The craters produced with this equipment reach a diameter of up to 20 cm, a size unique in laboratory cratering research. The experiment results show our TSLGG system work effectively, velocity of the projectile mass is measured highly accurate by means of the proposed optical method.

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Journal articles on the topic 'Hypervelocity impact'

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