RETRACTED: The laser-driven flyer system for space debris hypervelocity impact simulations

All spacecrafts in earth orbit are subject to hypervelocity impact by micro-meteoroids and space debris, which can in turn lead to significant damage and catastrophic failure of spacecraft. Porous volcano rock was adopted as one of micro-meteoroid material due to their similar physical and geometric features. Two-stage light gas gun experiments were carried out for a 6mm diameter volcano rock projectile impact on an Al-Whipple shield within the speed range from 1 km/s to 3 km/s. An ANSYS/LS-DYNA software was employed and justified by experimental results, in which a porous geometrical model was established for volcano rock projectile. The higher speed range was extended from 3 km/s to 10 km/s by numerical simulation. The results of experiments and numerical simulation indicated that major damage on rear wall of the Whipple shield impacted by volcano rock projectile is caused by the fragments of bumper of the shield, which is different from that of aluminum projectile. And 5.5km/s is the critical speed of a 6mm diameter volcano rock projectile impact on the Whipple shield investigated.

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Multifunctional load-bearing aerostructures with integrated space debris protection

MATEC Web of Conferences ◽

10.1051/matecconf/201930407003 ◽

2019 ◽

Vol 304 ◽

pp. 07003

Author(s):

Martin Schubert ◽

Anthanasios Dafnis

Keyword(s):

Composite Structures ◽

High Performance ◽

Space Debris ◽

Sandwich Panels ◽

Thermal Control ◽

Hypervelocity Impact ◽

Radiation Shielding ◽

Impact Testing ◽

Load Bearing ◽

Protection Capability

In the project multiSat multifunctional composite structures for satellite application have been developed. Functions such as protection against space debris, radiation shielding and passive thermal control have been integrated into the load-bearing composite spacecraft structure by use of suitable materials and components. Sandwich panels have been studied as representative structural parts of a conventional satellite structure. Measures for increased space debris protection include the substitution of the conventional honeycomb core by 3D-printed aluminum cellular structures and the reinforcement of the sandwich panel by integration of high performance fabrics which effectively break up and catch impacting debris particles. This paper describes the development and design of multifunctional sandwich concepts with increased impact protection capability and presents the experimental results of hypervelocity impact testing with different types of CFRP sandwich panels.

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The Experiment Study on Flash Spectrum Produced by Hypervelocity Impact

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.782.197 ◽

2015 ◽

Vol 782 ◽

pp. 197-203

Author(s):

Kai Zhang ◽

Qing Ming Zhang ◽

Ren Rong Long

Keyword(s):

Space Debris ◽

Hypervelocity Impact ◽

Spectral Lines ◽

Line Spectrum ◽

Weapon System ◽

Flash Intensity ◽

System A ◽

Flash Spectrum ◽

The Relationship ◽

Important Significance

It is an inevitable phenomenon that flash is generated in the process of hypervelocity impact. The research on impact flash is of important significance for assessing the collision between space debris and spacecraft, identifying the material properties on the surface of planet, evaluating the damage of weapon system. A measurement system was built in order to acquire flash spectrum ranging in wavelength from 200 to 1100nm. The relationship between flash intensity and impact velocity was studied. The spectrum consists of line spectrum and continuous spectrum. Line spectrum mainly concentrates in the range of 200-500nm. The spectral lines of the elements were identified. The strong flash happens within 2.2ms after beginning to impact. In addition, the electron temperature of plasma produced in hypervelocity impact is calculated by spectral method, and compared with the temperature measured by Langmuir three probes.

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Multi-layer insulation material models suitable for hypervelocity impact simulations

International Journal of Impact Engineering ◽

10.1016/j.ijimpeng.2008.07.017 ◽

2008 ◽

Vol 35 (12) ◽

pp. 1853-1860 ◽

Cited By ~ 8

Author(s):

D.M. White ◽

M. Wicklein ◽

R.A. Clegg ◽

H. Nahme

Keyword(s):

Hypervelocity Impact ◽

Insulation Material ◽

Material Models ◽

Impact Simulations

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An Experimental Study of High-Velocity Impact on Aluminum Foam Composite Shield Structure

Advanced Materials Research ◽

10.4028/www.scientific.net/amr.690-693.20 ◽

2013 ◽

Vol 690-693 ◽

pp. 20-24

Author(s):

Qing Zhen Li ◽

Zhong Hua Du ◽

Kang Kang Wang

Keyword(s):

Experimental Study ◽

High Speed ◽

Aluminum Foam ◽

Space Debris ◽

Hypervelocity Impact ◽

Protective Effects ◽

High Velocity Impact ◽

Protective Structure ◽

Velocity Impact ◽

Foam Composite

To study spacecraft shield structure against hypervelocity impact of space debris and its protective performances, 25mm ballistic gun launching 12.7mm cylindrical debris is selected against Aluminum foam composite structure at high speed. Based on the experimental results and analyze the effects of Aluminum foam protective structure with different combinations, the result is that protective effects with Aluminum foam in front of glass fiber is better.

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Investigation into Damage of Aluminum Multi-Wall Shield under Hypervelocity Projectiles Impact

Key Engineering Materials ◽

10.4028/www.scientific.net/kem.385-387.201 ◽

2008 ◽

Vol 385-387 ◽

pp. 201-204

Author(s):

Gong Shun Guan ◽

Bao Jun Pang ◽

Run Qiang Chi ◽

Nai Gang Cui

Keyword(s):

Aluminum Alloy ◽

Space Debris ◽

Hypervelocity Impact ◽

Wall Structure ◽

First Wall ◽

Experiment Data ◽

Normal Impact ◽

Advanced Method ◽

Hypervelocity Impacts ◽

Gas Gun

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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