A ballistic limit equation for hypervelocity impacts on composite honeycomb sandwich panel satellite structures

Ryan, Shannon; Schaefer, Frank; Destefanis, R.; Lambert, M.

doi:10.1016/j.asr.2007.02.032

Cited by 75 publications

(37 citation statements)

References 5 publications

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“…(Ryan et al, 2007;Schäfer et al, 2008). This BLE could even be applied to batteries, e-boxes, harnesses, fuel pipes, heat pipes and carbon-fiber wrapped pressure vessels.…”

Section: Recent Workmentioning

confidence: 97%

Protecting Earth-orbiting spacecraft against micro-meteoroid/orbital debris impact damage using composite structural systems and materials: An overview

Schonberg

2010

Advances in Space Research

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“…(Ryan et al, 2007;Schäfer et al, 2008). This BLE could even be applied to batteries, e-boxes, harnesses, fuel pipes, heat pipes and carbon-fiber wrapped pressure vessels.…”

Section: Recent Workmentioning

confidence: 97%

Protecting Earth-orbiting spacecraft against micro-meteoroid/orbital debris impact damage using composite structural systems and materials: An overview

Schonberg

2010

Advances in Space Research

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“…It requires the knowledge of physical and geometrical characteristics of all subcomponents (Honeycomb definition and thickness, facesheet material and thickness…). Other investigators' developments are considered as well for implementation as they rely on a large amount of test data on various types of spaced plates structures, see for example [6][7][8] to quote a few of the numerous articles published in the area.…”

Section: Development Contextmentioning

confidence: 99%

Effects of Debris Cloud Interaction with Satellites Critical Equipments – Experiments and Modeling

Sibeaud

Puillet

2015

Procedia Engineering

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The level of damage imparted on three types of satellites components resulting from hypervelocity impacts of aluminum projectiles onto a neighboring structural part have been assessed experimentally by using a double stage light gas gun. The experimental configurations were designed to simulate debris encounters with a space vehicle during its operational life time around the Earth. The first test was conducted against a set of separate harness strapped down on the inner surface of a carbon facesheet sandwich panel in order to assess the effectiveness of redundant cables spacing in case of unitary debris perforating impact onto the structure. The resistance to damaging of a silicon carbide mirror and a solar panel was then evaluated against debris cloud generated by prior impact of chunky debris with the satellite structure. Potential losses of electrical functional capabilities were then derived. The vulnerability/Survivability Pléiades software was updated accordingly.

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“…In Fig. 8 the ballistic limits of the GAIA SP front and rear facesheets are shown (calculated using equations from [11] and [12], respectively). It can be seen that low and intermediate level impacts cover the four penetration conditions previously defined.…”

Section: A General Excitation Function For Impact On the Gaia Cfrp/almentioning

confidence: 99%

Characterizing the transient response of CFRP/Al HC spacecraft structures induced by space debris impact at hypervelocity

Ryan¹,

Schäfer²,

Guyot³

et al. 2008

International Journal of Impact Engineering

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To quantify the disturbance induced by the impact of micrometeoroid and space debris particles at hypervelocity on vibration-sensitive CFRP/Al HC SP satellite platforms a method is presented which uses experimentally validated hydrocode models to characterize the impact-induced transient wave in the local structure. Key features of the transient waveform are simplified by a mathematical function which is expressed in terms of impactor momentum. Evolution of the transient waveform is characterized using multiple measurement gauges located on the sandwich panel facesheets outside the area of mechanical damage. The characterization is then used to extrapolate the elastic waveform back to the impact location. The elastic-equivalent excitation of a CFRP/Al HC SP is defined in terms of force with respect to time for application in finite element: structural codes for propagation of the local disturbance to vibration-sensitive locations (i.e. measurement devices)

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A ballistic limit equation for hypervelocity impacts on composite honeycomb sandwich panel satellite structures

Cited by 75 publications

References 5 publications

Protecting Earth-orbiting spacecraft against micro-meteoroid/orbital debris impact damage using composite structural systems and materials: An overview

Protecting Earth-orbiting spacecraft against micro-meteoroid/orbital debris impact damage using composite structural systems and materials: An overview

Effects of Debris Cloud Interaction with Satellites Critical Equipments – Experiments and Modeling

Characterizing the transient response of CFRP/Al HC spacecraft structures induced by space debris impact at hypervelocity

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