Interpolation/extrapolation technique with application to hypervelocity impact of space debris

1992 ◽  
Vol 29 (1) ◽  
pp. 70-75 ◽  
Author(s):  
William Keith Rule
Keyword(s):  
Space Debris ◽  
Hypervelocity Impact ◽  
Extrapolation Technique

Experimental Investigation and Numerical Simulation of Porous Volcano Rock Hypervelocity Impact on Whipple Shield of Spacecrafts

2010 ◽  
Vol 452-453 ◽  
pp. 385-388
Author(s):  
Bin Jia ◽  
Gao Jian Liao ◽  
Hai Peng Gong ◽  
Bao Jun Pang
Keyword(s):  
Numerical Simulation ◽  
Space Debris ◽  
Geometrical Model ◽  
Hypervelocity Impact ◽  
Rear Wall ◽  
Projectile Impact ◽  
Gas Gun ◽  
Significant Damage ◽  
Speed Range ◽  
Whipple Shield

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.

scholarly journals Multifunctional load-bearing aerostructures with integrated space debris protection

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.

The Experiment Study on Flash Spectrum Produced by Hypervelocity Impact

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.

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

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.

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

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.

Meteoroids and space debris hypervelocity impact penetrations in LDEF MAP foils compared with hydrocode simulations

1996 ◽  
Vol 17 (12) ◽  
pp. 201-204
Author(s):  
W.G. Tanner ◽  
J.A.M. McDonnell ◽  
H. Yano ◽  
H.J. Fitzgerald ◽  
D.J. Gardner
Keyword(s):  
Space Debris ◽  
Hypervelocity Impact

Four-View Split-Image Fragment Tracking in Hypervelocity Impact Experiments

2019 ◽  
Author(s):  
Erkai Watson ◽  
Nico Kunert ◽  
Robin Putzar ◽  
Hans-Gerd Maas ◽  
Stefan Hiermaier
Keyword(s):  
High Speed ◽  
Particle Tracking Velocimetry ◽  
Space Debris ◽  
Particle Image ◽  
Hypervelocity Impact ◽  
Hypervelocity Impacts ◽  
Image Fragment ◽  
Image Velocimetry ◽  
The Individual ◽  
Impact Experiments

Abstract Hypervelocity impacts (HVI) often cause significant fragmentation to occur in both target and projectile materials, and is often encountered in space debris and planetary impact applications [1]–[5]. In this paper, we focus on determining the individual velocities and sizes of fragments tracked in high-speed images. Inspired by velocimetry methods such as Particle Image Velocimetry (PIV) [6] and Particle Tracking Velocimetry (PTV) [7] and building on past work [8], we describe the setup and algorithm used for measuring fragmentation data.

Investigation on Sustained Discharge of Satellite’s Power Harness Due to Plasma from Space Debris Impact

2019 ◽  
Author(s):  
Yuki Mando ◽  
Koji Tanaka ◽  
Takayuki Hirai ◽  
Shirou Kawakita ◽  
Masumi Higashide ◽  
...  
Keyword(s):  
Space Debris ◽  
Internal Resistance ◽  
Low Earth Orbit ◽  
Hypervelocity Impact ◽  
Space Environment ◽  
Earth Orbit ◽  
Large Area ◽  
Solar Arrays ◽  
Sustained Discharge ◽  
Circuit Configuration

Abstract Space debris travels at a velocity of 7-8 km/s in low Earth orbit (LEO) and at 3 km/s in geostationary Earth orbit (GEO). An impact between space debris and spacecraft will result in tremendous damage. In particular, particles less than 1mm in diameter pose a risk of causing permanent sustained discharge (PSD). PSD may affect a satellite’s power system. The effect on solar arrays has been well-studied given their large area, but the effect on the bundle of a satellite’s wire harness (called the power harness) has yet to be clarified, even though the power harness is usually exposed to the space environment without protection. We conducted hypervelocity impact experiments using a two-stage light gas gun, and investigated the risk resulting in PSD from hypervelocity impacts of particles less than 1mm in size. In addition, we compared two kinds of circuit configurations: a more realistic circuit configuration with internal resistance and a circuit configuration without it, so as to investigate whether internal resistance affects the occurrence of PSD. Stainless steel and aluminum oxide projectiles measuring from 0.3 to 1 mm in diameter were gun-accelerated up to 7.16 km/s. Targets entailed a three-layered power harness under a simulated power condition of typical satellites operating in LEO or GEO. As a result, 11 of 28 shots resulted in PSD. With the more realistic circuit configuration we could not confirm any results regarding PSD. We thus found that PSD is less likely to occur in a more realistic circuit configuration.

Simulation of Characteristics of Debris Cloud Produced by Hypervelocity Impact

2014 ◽  
Vol 940 ◽  
pp. 300-305 ◽  
Author(s):  
Wen Lai Ma ◽  
Wei Zhang ◽  
Bao Jun Pang
Keyword(s):  
Smoothed Particle Hydrodynamics ◽  
Space Debris ◽  
Normal Incidence ◽  
Hypervelocity Impact ◽  
Critical Systems ◽  
Hypervelocity Impacts ◽  
Cloud Characteristics ◽  
Particle Hydrodynamics ◽  
Smoothed Particle ◽  
Debris Cloud

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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