Hypervelocity impact of a pressurized vessel: Comparison of ballistic limit equation predictions with test data and rupture limit equation development

2015 ◽  
Vol 115 ◽  
pp. 400-406 ◽  
Author(s):  
William P. Schonberg ◽  
J.Martin Ratliff
Keyword(s):  
Test Data ◽  
Hypervelocity Impact ◽  
Limit Equation ◽  
Ballistic Limit

A Predictive Non-Dimensional Scaling Law for the Plate Perforation of Several Aluminum Alloys by Fragment-Simulating Projectiles

2019 ◽  
Author(s):  
Weinong Chen ◽  
Zherui Guo
Keyword(s):  
Aluminum Alloys ◽  
Scaling Law ◽  
Limit Equation ◽  
Ballistic Limit ◽  
Limit Velocity ◽  
Dimensional Scaling ◽  
Material Problem ◽  
Plate Perforation ◽  
Ballistic Limit Velocity ◽  
Aluminum Armor Plates

Abstract An equation was previously-presented to predict the ballistic-limit velocity for the perforation of aluminum armor plates by fragment-simulating projectiles (FSP). The ballistic-limit equation was presented in terms of dimensionless parameters so that the geometric and material problem scales are identified. Previously published predictions and data for two different FSP projectile calibers (12.7 mm and 20 mm) and two different strength aluminum alloys show the scaling law to be accurate. In this paper we extend the same concept to several other alloys and show that this scaling law is predictive.

scholarly journals A rupture limit equation for COPVs following a perforating MMOD impact

2019 ◽  
Author(s):  
William P. Schonberg
Keyword(s):  
Pressure Vessel ◽  
High Speed ◽  
Pressure Vessels ◽  
Hypervelocity Impact ◽  
Operating Conditions ◽  
Design Parameters ◽  
Particle Impact ◽  
Catastrophic Failure ◽  
Limit Equation ◽  
Loss Of Life

Abstract Most spacecraft have at least one pressurized vessel on board. One of the primary design considerations for earth-orbiting spacecraft is the anticipation and mitigation of the possible damage that might occur in the event of a micrometeoroid or orbital debris (MMOD) particle impact. To prevent mission failure and possibly loss of life, protection against perforation by such high-speed impacts must be included. In addition to a hole, it is possible that, for certain pressure vessel designs, materials, impact parameters, and operating conditions, a pressure vessel may experience catastrophic failure (i.e. rupture) as a result of a hypervelocity impact. If such a tank rupture were to occur on-orbit following an MMOD impact, not only could it lead to loss of spacecraft, but quite possibly, for human missions, it could also result in loss of life. In this paper we present an update to a Rupture Limit Equation, or RLE, for composite overwrapped pressure vessels (COPVs) that was presented previously. The update consists of modified RLE parameters and coefficients that were obtained after the RLE was re-derived using new / additional data. The updated RLE functions in a manner similar to that of a ballistic limit equation, or BLE, that is, it differentiates between regions of operating and impact conditions that, given a tank wall perforation, would result in either tank rupture or only a relatively small hole or crack. This is an important consideration in the design of a COPV pressurized tank – if possible, design parameters and operating conditions should be chosen such that additional sizable debris (such as that which would be created in the event of tank rupture or catastrophic failure) is not created as a result of an on-orbit MMOD particle impact.

Hypervelocity impact on spacecraft carbon fibre reinforced plastic/aluminium honeycomb

1997 ◽  
Vol 211 (5) ◽  
pp. 355-363 ◽  
Author(s):  
E A Taylor ◽  
M K Herbert ◽  
D J Gardner ◽  
L Kay ◽  
R Thomson ◽  
...  
Keyword(s):  
Carbon Fibre ◽  
Impact Energy ◽  
Strong Dependence ◽  
Rear Surface ◽  
Hypervelocity Impact ◽  
Ballistic Limit ◽  
Strong Function ◽  
Reinforced Plastic ◽  
Carbon Fibre Reinforced Plastic ◽  
The Impact

Samples of a spacecraft primary external wall structure, as used in a low earth orbit remote sensing platform, have been tested to determine the response to the hypervelocity impact and ballistic limit (for mm-sized impactors) of the 47 mm thick structure at 5 km/s. A strong dependence of the ballistic limit on projectile density was identified. This programme was carried out using the two-stage light gas gun at the University of Kent at Canterbury. The equivalent diameters of the front and rear holes for each impact were analysed as a function of the impactor parameters. Damage equations derived by other experimenters were compared to the experimental results. X-ray non-destructive testing was used to determine the level of internal honeycomb damage for a sample. The dependence of the witness plate damage (placed behind the target to capture any ejecta from the rear surface) on the impactor parameters was recorded. It was found that the use of ‘equivalent thicknesses’ of aluminium may not be appropriate as a general conversion factor for carbon fibre reinforced plastic (CFRP) facesheets. A simple damage equation is presented, based on the total hole size as a function of the impact energy. The ballistic limit cannot be defined solely in terms of impact energy and shows an additional dependence with projectile density. The amount and type of ejecta produced is a strong function of density and a less strong function of projectile diameter, and its production cannot be linked with the rear hole diameter.

Investigation on Response of an Aluminum Honeycomb Subjected to Hypervelocity Impacts using Lagrange and SPH for Numerical Modeling

2019 ◽  
Author(s):  
Kumi Nitta ◽  
Masumi Higashide ◽  
Mirai Sueki ◽  
Atushi Takeba
Keyword(s):  
Numerical Modeling ◽  
High Strain ◽  
Hypervelocity Impact ◽  
Numerical Results ◽  
Experimental Results ◽  
Ballistic Limit ◽  
Limit Curve ◽  
Material Models ◽  
Hypervelocity Impacts ◽  
Aluminum Honeycomb

Abstract Numerical modeling has been conducted with the commercial code AUTODYN 2D, using the Lagrange and Smooth Particle Hydrodynamics (SPH) processors. The numerical results are compared and discussed with the corresponding experimental results from the standpoint of assessing the protection of satellites against M/OD hypervelocity impacts. The material models used in the numerical simulation are also discussed, as well as a wide range of impact velocities, including shock-induced vaporization. The projectiles used to simulate M/OD consist of 100 μm to 1 mm diameter alumina with impact velocities of 2–15 km/s. In order to assess the structural integrity of unmanned spacecraft subjected to the threat of hypervelocity impact by space debris, the numerical method was proposed mainly from the standpoint of material modeling suitable for extremely severe physical conditions such as high pressure, high temperature, high strain, and high strain rate, sometimes accompanied by shock-induced vaporization. The numerical results adopting these material models were compared with the corresponding hypervelocity impact tests by using the two-stage light-gas gun at ISAS/JAXA. Although examples of the impacts on the aluminum honeycomb can be shown, it has been demonstrated that the numerical analysis can effectively simulate the overall corresponding experimental results. We show the response of an aluminum honeycomb as derived from analysis of hypervelocity impact at 2 km/s to 15 km/s using the Lagrange and SPH processors. We also verified that the ballistic limit curve of an aluminum honeycomb panel is shown as a downward line using both processors, which is unlike the up and down ballistic limit curve of a Whipple shield.

Simulation study of non-spherical, graphite-epoxy projectiles

2019 ◽  
Author(s):  
Joshua E. Miller
Keyword(s):  
Large Fraction ◽  
Space Station ◽  
Current Approach ◽  
Hypervelocity Impact ◽  
Ballistic Limit ◽  
Environment Modeling ◽  
Cylindrical Structures ◽  
Transport Vehicle ◽  
Impact Angles ◽  
The Impact

Abstract The DebriSat hypervelocity impact experiment, performed at the Arnold Engineering Development Center, is intended to update the catastrophic break-up models for modern satellites. To this end, the DebrisSat was built with many modern materials including structural panels of carbon-fiber, reinforced-polymer (CFRP). Subsequent to the experiment, fragments of the DebrisSat have been extracted from porous, catcher panels used to gather the debris from the impact event. Thus far, one of the key observations from the collected fragments is that CFRP represents a large fraction of the fragments and that these fragments tend to be thin, flake-like structures or long, needle-like structures; whereas, debris with nearly equal dimensions is less prevalent. As current ballistic limit models are all developed based upon spherical impacting particles, the experiment has pointed to a missing component in the current approach that must be considered. To begin to understand the implications of this observation, simulations have been performed using cylindrical structures at a representative orbital speed into an externally-insulated, double-wall shield that is representative of shielding on the current International Space Station crew transport vehicle, the Soyuz. These simulations have been performed for normal impacts to the surface with three different impact angles-of-attack to capture the effect on the shield performance. This paper documents the simulated shield and the models developed to study the effect of fragments and derives the critical characteristics of CFRP impacting particles for the selected shield. This work gives a deployable form of a critical, non-spherical projectile ballistic limit equation for evaluating non-spherical space debris for orbital debris environment modeling.

Sign in / Sign up

Export Citation Format

Share Document