RS-34 Phoenix In-Space Propulsion System Applied to Active Debris Removal Mission
No abstract available
Esther, Elizabeth A.↗
Engineering topics
Russell, Tiffany E.
Publications and source records attributed to Russell, Tiffany E..
Nuclear Cryogenic Propulsion Stage Conceptual Design and Mission Analysis
The Nuclear Cryogenic Propulsion Stage (NCPS) is an in-space transportation vehicle, comprised of three main elements, designed to support a long-stay human Mars mission architecture beginning in 2035. The stage conceptual design and the mission analysis discussed here support the current nuclear thermal propulsion going on within partnership activity of NASA and the Department of Energy (DOE). The transportation system consists of three elements: 1) the Core Stage, 2) the In-line Tank, and 3) the Drop Tank. The driving mission case is the piloted flight to Mars in 2037 and will be the main point design shown and discussed. The corresponding Space Launch System (SLS) launch vehicle (LV) is also presented due to it being a very critical aspect of the NCPS Human Mars Mission architecture due to the strong relationship between LV lift capability and LV volume capacity.
Kos, Larry D.↗
Reduction of Martian Sample Return Mission Launch Mass with Solar Sail Propulsion
Solar sails have the potential to provide mass and cost savings for spacecraft traveling within the innter solar system. Companies like L'Garde have demonstrated sail manufacturability and various i-space development methods. The purpose of this study was to evaluate a current Mars sample return architecture and to determine how cost and mass would be reduced by incorporating a solar sail propulsion system. The team validated the design proposed by L'Garde, and scaled the design based on a trajectory analysis. Using the solar sail design reduced the required mass, eliminating one of the three launches required in the original architecture.
Russell, Tiffany E.↗
Reduction of Martian Sample Return Mission Launch Mass with Solar Sail Propulsion
Solar sails have the potential to provide mass and cost savings for spacecraft traveling within the inner solar system. Companies like L'Garde have demonstrated sail manufacturability and various in-space deployment methods. The purpose of this study was to evaluate a current Mars sample return architecture and to determine how cost and mass would be reduced by incorporating a solar sail propulsion system. The team validated the design proposed by L'Garde, and scaled the design based on a trajectory analysis. Using the solar sail design reduced the required mass, eliminating one of the three launches required in the original architecture.
Russell, Tiffany E.↗
DEPLOYTECH: Deployment Technology Survey Web Publication Version
The information in this survey provides a sample of details on deployable structures that have been proposed, tested, and flown from the 1960s to today.
Russell, Tiffany E.↗