The Experts below are selected from a list of 171 Experts worldwide ranked by ideXlab platform

Christopher M. Matty - One of the best experts on this subject based on the ideXlab platform.

  • Overview of Carbon Dioxide Control Issues During International Space Station/Space Shuttle Joint Docked Operations
    40th International Conference on Environmental Systems, 2010
    Co-Authors: Christopher M. Matty
    Abstract:

    Crewed space vehicles have a common requirement to remove the Carbon Dioxide (CO2) created by the crew’s metabolic processes. The space shuttle [Space Transportation System (STS)] and International Space Station (ISS) each have systems in place that allow Control and removal of CO2 from the habitable cabin environment. During periods in which the STS is docked to the ISS, known as “joint docked operations,” the space shuttle and ISS share a common atmosphere environment. During this period, an elevated amount of CO2 is produced through the combined metabolic activity of the STS and ISS crews. This elevated CO2 production, together with the large effective atmosphere created by collective volumes of the docked vehicles, creates a unique set of requirements for CO2 removal. This paper will describe individual CO2 Control plans implemented by STS and ISS engineering teams, as well as the integrated plans used when both vehicles are docked. The paper will also discuss some of the issues and anomalies experienced by both engineering teams.

  • overview of Carbon Dioxide Control issues during international space station space shuttle joint docked operations
    40th International Conference on Environmental Systems, 2010
    Co-Authors: Christopher M. Matty
    Abstract:

    Crewed space vehicles have a common requirement to remove the Carbon Dioxide (CO2) created by the crew’s metabolic processes. The space shuttle [Space Transportation System (STS)] and International Space Station (ISS) each have systems in place that allow Control and removal of CO2 from the habitable cabin environment. During periods in which the STS is docked to the ISS, known as “joint docked operations,” the space shuttle and ISS share a common atmosphere environment. During this period, an elevated amount of CO2 is produced through the combined metabolic activity of the STS and ISS crews. This elevated CO2 production, together with the large effective atmosphere created by collective volumes of the docked vehicles, creates a unique set of requirements for CO2 removal. This paper will describe individual CO2 Control plans implemented by STS and ISS engineering teams, as well as the integrated plans used when both vehicles are docked. The paper will also discuss some of the issues and anomalies experienced by both engineering teams.

Heather L. Paul - One of the best experts on this subject based on the ideXlab platform.

  • Carbon Dioxide Control System for a Mars Space Suit Life Support System
    41st International Conference on Environmental Systems, 2011
    Co-Authors: Gokhan Alptekin, Ambalavanan Jayaraman, Robert James Copeland, Amanda Parker, Heather L. Paul
    Abstract:

    Carbon Dioxide (CO2) Control during Extravehicular Activities (EVAs) on Mars will be challenging. Lithium hydroxide (LiOH) canisters have impractical logistics penalties, and regenerable metal oxide (MetOx) canisters weigh too much. Cycling bed systems and permeable membranes that are regenerable in space vacuum cannot vent on Mars due to the high partial pressure of CO2 in the atmosphere. Although sweep gas regeneration is under investigation, the feasibility, logistics penalties, and failure modes associated with this technique have not been fully determined. TDA Research, Inc. is developing a durable, high-capacity regenerable adsorbent that can remove CO2 from the space suit ventilation loop. The system design allows sorbent regeneration at or above 6 torr, eliminating the potential for Martian atmosphere to leak into the regeneration bed and into the ventilation loop. Regeneration during EVA eliminates the consumable requirement related to the use of LiOH canisters and the mission duration limitations imposed by MetOx system. The concept minimizes the amount of consumable to be brought from Earth and makes the mission more affordable, while providing great operational flexibility during EVA. The feasibility of the concept has been demonstrated in a series of bench-scale experiments and a preliminary system analysis. Results indicate that sorbent regeneration can be accomplished by applying a 14 C temperature swing, while regenerating at 13 torr (well above the Martian atmospheric pressure), withstanding over 1,000 adsorption/regeneration cycles. This paper presents the latest results from these sorbent and system development efforts.

Bob M. Bagdigian - One of the best experts on this subject based on the ideXlab platform.

  • Parametric Analysis of Life Support Systems for Future Space Exploration Missions
    41st International Conference on Environmental Systems, 2011
    Co-Authors: Michael J. Swickrath, Molly Anderson, Bob M. Bagdigian
    Abstract:

    Having adopted a flexible path approach to space exploration, the National Aeronautics and Space Administration is in a process of evaluating future targets for space exploration. In order to maintain the welfare of a crew during future missions, a suite of life support technology is responsible for oxygen and water generation, Carbon Dioxide Control, the removal of trace concentrations of organic contaminants, processing and recovery of water, and the storage and reclamation of solid waste. For each particular life support subsystem, a variety competing technologies either exist or are under aggressive development efforts. Each individual technology has strengths and weaknesses with regard to launch mass, power and cooling requirements, volume of hardware and consumables, and crew time requirements for operation. However, from a system level perspective, the favorability of each life support architecture is better assessed when the sub-system technologies are analyzed in aggregate. In order to evaluate each specific life support system architecture, the measure of equivalent system mass (ESM) was employed to benchmark system favorability. Moreover, the results discussed herein will be from the context of loop-closure with respect to the air, water, and waste sub-systems. Specifically, closure relates to the amount of consumables mass that crosses the boundary of the vehicle over the lifetime of a mission. As will be demonstrated in this manuscript, the optimal level of loop closure is heavily dependent upon mission requirements such as duration and the level of extra- vehicular activity (EVA) performed. Sub-system level trades were also considered as a function of mission duration to assess when increased loop closure is practical. Although many additional factors will likely merit consideration in designing life support systems for future missions, the ESM results described herein provide a context for future architecture design decisions toward a flexible path program.

Gokhan Alptekin - One of the best experts on this subject based on the ideXlab platform.

  • Carbon Dioxide Control System for a Mars Space Suit Life Support System
    41st International Conference on Environmental Systems, 2011
    Co-Authors: Gokhan Alptekin, Ambalavanan Jayaraman, Robert James Copeland, Amanda Parker, Heather L. Paul
    Abstract:

    Carbon Dioxide (CO2) Control during Extravehicular Activities (EVAs) on Mars will be challenging. Lithium hydroxide (LiOH) canisters have impractical logistics penalties, and regenerable metal oxide (MetOx) canisters weigh too much. Cycling bed systems and permeable membranes that are regenerable in space vacuum cannot vent on Mars due to the high partial pressure of CO2 in the atmosphere. Although sweep gas regeneration is under investigation, the feasibility, logistics penalties, and failure modes associated with this technique have not been fully determined. TDA Research, Inc. is developing a durable, high-capacity regenerable adsorbent that can remove CO2 from the space suit ventilation loop. The system design allows sorbent regeneration at or above 6 torr, eliminating the potential for Martian atmosphere to leak into the regeneration bed and into the ventilation loop. Regeneration during EVA eliminates the consumable requirement related to the use of LiOH canisters and the mission duration limitations imposed by MetOx system. The concept minimizes the amount of consumable to be brought from Earth and makes the mission more affordable, while providing great operational flexibility during EVA. The feasibility of the concept has been demonstrated in a series of bench-scale experiments and a preliminary system analysis. Results indicate that sorbent regeneration can be accomplished by applying a 14 C temperature swing, while regenerating at 13 torr (well above the Martian atmospheric pressure), withstanding over 1,000 adsorption/regeneration cycles. This paper presents the latest results from these sorbent and system development efforts.

Michael J. Swickrath - One of the best experts on this subject based on the ideXlab platform.

  • Parametric Analysis of Life Support Systems for Future Space Exploration Missions
    41st International Conference on Environmental Systems, 2011
    Co-Authors: Michael J. Swickrath, Molly Anderson, Bob M. Bagdigian
    Abstract:

    Having adopted a flexible path approach to space exploration, the National Aeronautics and Space Administration is in a process of evaluating future targets for space exploration. In order to maintain the welfare of a crew during future missions, a suite of life support technology is responsible for oxygen and water generation, Carbon Dioxide Control, the removal of trace concentrations of organic contaminants, processing and recovery of water, and the storage and reclamation of solid waste. For each particular life support subsystem, a variety competing technologies either exist or are under aggressive development efforts. Each individual technology has strengths and weaknesses with regard to launch mass, power and cooling requirements, volume of hardware and consumables, and crew time requirements for operation. However, from a system level perspective, the favorability of each life support architecture is better assessed when the sub-system technologies are analyzed in aggregate. In order to evaluate each specific life support system architecture, the measure of equivalent system mass (ESM) was employed to benchmark system favorability. Moreover, the results discussed herein will be from the context of loop-closure with respect to the air, water, and waste sub-systems. Specifically, closure relates to the amount of consumables mass that crosses the boundary of the vehicle over the lifetime of a mission. As will be demonstrated in this manuscript, the optimal level of loop closure is heavily dependent upon mission requirements such as duration and the level of extra- vehicular activity (EVA) performed. Sub-system level trades were also considered as a function of mission duration to assess when increased loop closure is practical. Although many additional factors will likely merit consideration in designing life support systems for future missions, the ESM results described herein provide a context for future architecture design decisions toward a flexible path program.