A hypervelocity impact facility optimised for the dynamic study of high pressure shock compression

Ringrose, T. J.; Doyle, Hugo; Foster, P. S.; Betney, Matthew; Skidmore, J.; Edwards, Thomas A.; Tully, Brett; Parkin, J.R.; Hawker, Nicholas

doi:10.1016/j.proeng.2017.09.756

Cited by 13 publications

(2 citation statements)

References 7 publications

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“…There are different types of Hypervelocity laboratories that perform impact tests, the most common are the powder-gas guns [4], it is possible to manufacture them in a two-stage light gas configuration that does not involve the use of explosive dust [5].…”

Section: Hypervelocity Impact Facilitymentioning

confidence: 99%

Overview of spacecraft fragmentation testing

Lopresti

2023

Materials Research Proceedings

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Abstract. Spacecraft fragmentation due to collisions with space debris is a major concern for space agencies and commercial entities, since the production of collisional fragments is one of the major sources of space debris. It is in fact believed that, in certain circumstances, the increase of fragmentation events could trigger collisional cascade that makes the future debris environmental not sustainable. Experimental studies have shown that the fragmentation process is highly complex and influenced by various factors, such as the material properties, the velocity and angle of the debris impact and the point of collision (e.g. central, glancing, on spacecraft appendages). In recent years, numerous impact tests have been performed, varying one or more of these parameters to better understand the physics behind these phenomena. In this context some tests have been also performed at the hypervelocity impact facility of the university of Padova. This paper provides an overview of the main experiments performed, the most critical issues observed and proposes some future directions for further research. Moreover, it summarizes the current state of research in spacecraft fragmentation, including the methods and techniques used to simulate debris impacts, the characterization of fragment properties and the analysis of the resulting debris cloud.

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Section: Hypervelocity Impact Facilitymentioning

confidence: 99%

Overview of spacecraft fragmentation testing

Lopresti

2023

Materials Research Proceedings

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“…Adding more charge results in entering a regime of diminishing returns with most of the work wasted in accelerating the additional charge [1]. Many ways to overcome this velocity limit were explored, including light gas guns, heavy guns, and guns with excessive propellants [2][3][4][5], wherein the Electromagnetic gun-railgun-with a totally different propulsion technology has emerged as the practical and feasible solution to launch hypervelocity projectile.…”

Section: Introductionmentioning

confidence: 99%

Design and Development of High Current Pulse Shaping Inductor Based on Bitter Magnet Configuration for Electro Magnetic Launcher

Kumar*,

Jadhav,

Kumar

et al. 2019

IJEAT

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A unique pulse shaping inductor was designed and developed using a modified Bitter magnet configuration, to operate at peak current of 150 kA for duration of 5-10 ms in a Pulse Forming Network (PFN). The inductor was designed with a stack of parallel copper plates in the form of circular discs with a central hole, with GRP insulation plates in between. The design is optimized by electromagnetic finite element techniques for inductance and structural stability. The conducting discs and insulators are clamped together with tie rods between two endplates to provide adequate contact pressure and sufficient mechanical support. The conducting, inter connecting and insulating components were modeled and optimised parametrically for the desired performance and structural integrity. The device was fabricated, assembled and tested with 24 bitter plates for 28 µH inductance. The inductor was integrated with 400 kJ capacitor bank module and tested under static and dynamic condition. Current pulse of peak above 100 kA was generated, with consistent arc-free performance, high reliability and structural stability.

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Digital Twin Applications in Spacecraft Protection

Yavuz¹,

Konacaklı²

2023

Digital Twin Driven Intelligent Systems and Emerging Metaverse

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A hypervelocity impact facility optimised for the dynamic study of high pressure shock compression

Cited by 13 publications

References 7 publications

Overview of spacecraft fragmentation testing

Overview of spacecraft fragmentation testing

Design and Development of High Current Pulse Shaping Inductor Based on Bitter Magnet Configuration for Electro Magnetic Launcher

Digital Twin Applications in Spacecraft Protection

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