Volume 34 Issue 3
Jun 2020
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WANG Mafa, HIGGINS Andrew J, JIAO Dezhi, HUANG Jie, LIU Sen. Preliminary Simulation and Experimental Study on Implosion-Driven Hypervelocity Launching Technology[J]. Chinese Journal of High Pressure Physics, 2020, 34(3): 033301. doi: 10.11858/gywlxb.20190870
Citation: WANG Mafa, HIGGINS Andrew J, JIAO Dezhi, HUANG Jie, LIU Sen. Preliminary Simulation and Experimental Study on Implosion-Driven Hypervelocity Launching Technology[J]. Chinese Journal of High Pressure Physics, 2020, 34(3): 033301. doi: 10.11858/gywlxb.20190870

Preliminary Simulation and Experimental Study on Implosion-Driven Hypervelocity Launching Technology

doi: 10.11858/gywlxb.20190870
  • Received Date: 23 Dec 2019
  • Rev Recd Date: 20 Jan 2020
  • For achieving the hypervelocity launching of about 10 km/s, an implosion-driven launcher with the caliber of 8 mm diameter was analyzed using the AUTODYN 2D software. The projectile launching velocities under typical operation condition were obtained. Based on numerical simulation results, several tests of the implosion-driven launcher with the caliber of 8 mm diameter were carried out. The driven gas of helium with the pressure of 5 MPa was filled in the compressed pipe. The experimental results show that the 0.55 g aluminum and 0.37 g magnesium projectiles could be launched to the velocity of 7.95 km/s and 10.28 km/s, respectively, and the relative deviations between the numerical and experimental results are 15.3% and 3.7%, respectively. Consequently, the designed implosion-driven launcher can realize the launching of the projectiles to 10 km/s or even higher which could provide a new ground-test method for investigating the impact features of orbital debris and corresponding shield technologies.

     

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