Ablation modeling of electro-magnetic launched projectile for access to space

Ryan Gosse; Graham V Candler

Ablation modeling of electro-magnetic launched projectile for access to space

Ryan Gosse, Graham V Candler

Aerospace Engineering and Mechanics

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

17 Scopus citations

Abstract

It has been proposed to study and identify the technical issues involved in the launch to space of micro-satellite payloads using an electromagnetic launcher (EML). A CFD code was developed to help characterize the aero-thermal issues involved with the flight of the projectile as it exits the Earth's atmosphere. Initial conceptual geometries were chosen to evaluate the feasibility of launching to orbit from an aircraft. Due to expected high heating fluxes, carbon-carbon was selected for the heat shield. Results of the initial selected geometries are presented and used to evaluate the practicality of a passive thermal protection system.

Original language	English (US)
Title of host publication	Collection of Technical Papers - 45th AIAA Aerospace Sciences Meeting
Pages	14444-14460
Number of pages	17
Volume	21
State	Published - Jul 2 2007
Event	45th AIAA Aerospace Sciences Meeting 2007 - Reno, NV, United States Duration: Jan 8 2007 → Jan 11 2007

Other

Other	45th AIAA Aerospace Sciences Meeting 2007
Country/Territory	United States
City	Reno, NV
Period	1/8/07 → 1/11/07

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title = "Ablation modeling of electro-magnetic launched projectile for access to space",

abstract = "It has been proposed to study and identify the technical issues involved in the launch to space of micro-satellite payloads using an electromagnetic launcher (EML). A CFD code was developed to help characterize the aero-thermal issues involved with the flight of the projectile as it exits the Earth's atmosphere. Initial conceptual geometries were chosen to evaluate the feasibility of launching to orbit from an aircraft. Due to expected high heating fluxes, carbon-carbon was selected for the heat shield. Results of the initial selected geometries are presented and used to evaluate the practicality of a passive thermal protection system.",

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year = "2007",

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language = "English (US)",

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note = "45th AIAA Aerospace Sciences Meeting 2007 ; Conference date: 08-01-2007 Through 11-01-2007",

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AB - It has been proposed to study and identify the technical issues involved in the launch to space of micro-satellite payloads using an electromagnetic launcher (EML). A CFD code was developed to help characterize the aero-thermal issues involved with the flight of the projectile as it exits the Earth's atmosphere. Initial conceptual geometries were chosen to evaluate the feasibility of launching to orbit from an aircraft. Due to expected high heating fluxes, carbon-carbon was selected for the heat shield. Results of the initial selected geometries are presented and used to evaluate the practicality of a passive thermal protection system.

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Y2 - 8 January 2007 through 11 January 2007

ER -

Ablation modeling of electro-magnetic launched projectile for access to space

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