Cinda Chullen

Bio: Cinda Chullen is an academic researcher. The author has contributed to research in topics: Space suit & Amine gas treating. The author has an hindex of 4, co-authored 24 publications receiving 57 citations.

Rapid Cycle Amine (RCA 2.0) System Development

Abstract: The Rapid Cycle Amine (RCA) system is a low-power assembly capable of simultaneously removing carbon dioxide (CO2) and humidity from an influent air steam and subsequent regeneration when exposed to a vacuum source. Two solid amine sorbent beds are alternated between an uptake mode and a regeneration mode. During the uptake mode, the sorbent is exposed to an air steam (ventilation loop) to adsorb CO2 and water (H2O) vapor, whereas during the regeneration mode, the sorbent rejects the adsorbed CO2 and H2O vapor to a vacuum source. The two beds operate such that while one bed is in the uptake mode, the other is in the regeneration mode, thus continuously providing an on-service sorbent bed by which CO2 and humidity may be removed. A novel valve assembly provides a simple means of diverting the process air flow through the uptake bed while simultaneously directing the vacuum source to the regeneration bed. Additionally, the valve assembly is designed to allow for switching between uptake and regeneration modes with only one moving part while minimizing gas volume losses to the vacuum source by means of an internal pressure equalization step during actuation. The process can be controlled by a compact, low-power controller design with several modes of operation available to the user. Together with NASA Johnson Space Center, Hamilton Sundstrand Space Systems International, Inc. has been developing RCA 2.0 based on performance and design feedback on several sorbent bed test articles and valve design concepts. A final design of RCA 2.0 was selected in November 2011 and fabricated and assembled between March and August 2012, with delivery to NASA Johnson Space Center in September 2012. This paper provides an overview of the RCA system design and results of pre-delivery testing.

Pre- and Post-Treatment Techniques for Spacecraft Water Recovery

Abstract: Distillation-based waste water pretreatment and recovered water posttreatment methods are proposed for the NASA Space Station. Laboratory investigation results are reported for two nonoxidizing urine pretreatment formulas (hexadecyl trimethyl ammonium bromide and Cu/Cr) which minimize the generation of volatile organics, thereby significantly reducing posttreatment requirements. Three posttreatment methods (multifiltration, reverse osmosis, and UV-assisted ozone oxidation) have been identified which appear promising for the removal of organic contaminants from recovered water.

Continued Development of the Rapid Cycle Amine (RCA) System for Advanced Extravehicular Activity Systems

Abstract: Development activities related to the Rapid Cycle Amine (RCA) Carbon Dioxide (CO2) and Humidity control system have progressed to the point of integrating the RCA into an advanced Primary Life Support System (PLSS 2.0) to evaluate the interaction of the RCA among other PLSS components in a ground test environment. The RCA 2.0 assembly (integrated into PLSS 2.0) consists of a valve assembly with commercial actuator motor, a sorbent canister, and a field-programmable gate array (FPGA)-based process node controller. Continued design and development activities for RCA 3.0 have been aimed at optimizing the canister size and incorporating greater fidelity in the valve actuator motor and valve position feedback design. Further, the RCA process node controller is envisioned to incorporate a higher degree of functionality to support a distributed PLSS control architecture. This paper will describe the progression of technology readiness levels of RCA 1.0, 2.0 and 3.0 along with a review of the design and manufacturing successes and challenges for 2.0 and 3.0 units. The anticipated interfaces and interactions with the PLSS 2.0/2.5/3.0 assemblies will also be discussed.

U.S. Spacesuit Knowledge Capture

Abstract: The ability to learn from both the mistakes and successes of the past is vital to assuring success in the future. Due to the close physical interaction between spacesuit systems and human beings as users, spacesuit technology and usage lends itself rather uniquely to the benefits realized from the skillful organization of historical information; its dissemination; the collection and identification of artifacts; and the education of individuals and groups working in the field. The National Aeronautics and Space Administration (NASA), other organizations and individuals have been performing United States (U.S.) spacesuit knowledge capture since the beginning of space exploration. Avenues used to capture the knowledge have included publication of reports; conference presentations; specialized seminars; and classes usually given by veterans in the field. Recently, the effort has been more concentrated and formalized whereby a new avenue of spacesuit knowledge capture has been added to the archives through which videotaping occurs, engaging both current and retired specialists in the field presenting technical scope specifically for education and preservation of knowledge. Now with video archiving, all these avenues of learning can be brought to life with the real experts presenting their wealth of knowledge on screen for future learners to enjoy. U.S. spacesuit knowledge capture topics have included lessons learned in spacesuit technology, experience from the Gemini, Apollo, Skylab and Shuttle programs, hardware certification, design, development and other program components, spacesuit evolution and experience, failure analysis and resolution, and aspects of program management. Concurrently, U.S. spacesuit knowledge capture activities have progressed to a level where NASA, the National Air and Space Museum (NASM), Hamilton Sundstrand (HS) and the spacesuit community are now working together to provide a rather closed-looped spacesuit knowledge capture system which includes specific attention to spacesuit system artifacts as well. A NASM report has recently been created that allows the cross reference of history to the artifacts and the artifacts to the history including spacesuit manufacturing details with current condition and location. NASA has examined spacesuits in the NASM collection for evidence of wear during their operational life. NASA s formal spacesuit knowledge capture efforts now make use of both the NASM spacesuit preservation collection and report to enhance its efforts to educate NASA personnel and contribute to spacesuit history. Be it archiving of human knowledge or archiving of the actual spacesuit legacy hardware with its rich history, the joining together of spacesuit system artifact history with that of development and use during past programs will provide a wealth of knowledge which will greatly enhance the chances for the success of future and more ambitious spacesuit system programs.

U.S. Spacesuit Knowledge Capture Accomplishments in Fiscal Years 2012 and 2013

Abstract: The NASA U.S. Spacesuit Knowledge Capture (KC) program has existed since the beginning of 2008. The program was designed to augment engineers and other technical team members with historical spacesuit information to add to their understanding of the spacesuit, its evolution, its limitations, and its capabilities. Over 40 seminars have captured spacesuit history and knowledge over the last six years of the program's existence. Subject matter experts have provided lectures and some were interviewed to help bring the spacesuit to life so that lessons learned will never be lost. As well, the program concentrated in reaching out to the public and industry by making the recorded events part of the public domain through the NASA technical library through YouTube media. The U.S. Spacesuit KC topics have included lessons learned from some of the most prominent spacesuit experts and spacesuit users including current and former astronauts. The events have enriched the spacesuit legacy knowledge from Gemini, Apollo, Skylab, Space Shuttle and International Space Station Programs. As well, expert engineers and scientists have shared their challenges and successes to be remembered. Based on evidence by the thousands of people who have viewed the recordings online, the last few years have been some of the most successful years of the KC program's life with numerous digital recordings and public releases. This paper reviews the events accomplished and archived over Fiscal Years 2012 and 2013 and highlights a few of the most memorable ones. This paper also communicates ways to access the events that are available internally on the NASA domain as well as those released on the public domain.

An Independent Assessment of the Technical Feasibility of the Mars One Mission Plan

Abstract: In mid-2012, the Mars One program was announced, aiming to build the first human settlement on the surface of Mars. Following a series of precursor missions to develop and deploy key technologies, the first crewed mission would depart Earth in 2024, sending four people on a one-way journey to the surface of Mars. Additional fourperson crews would be sent to Mars at every subsequent launch opportunity to further support and expand the Martian colony. While this program has been received with great fanfare, very little has been published in the technical literature on this mission architecture. As the Mars One mission plan represents a dramatic departure from more conservative exploration approaches, there are many uncertainties in the mission design. The establishment of a colony on Mars will rely on in-situ resource utilization (ISRU) and life support technologies that are more capable than the current state of the art. Moreover, resupply logistics and sparing will play a large role in the proposed colony, though the magnitude and behavior of these two effects is not well understood. In light of this, we develop a Mars settlement analysis tool that integrates a habitat simulation with an ISRU sizing model and a sparing analysis. A logistics model is utilized to predict the required number of launchers and provide a preliminary estimate of a portion of the program cost. We leverage this tool to perform an independent assessment of the technical feasibility of the Mars One mission architecture. Our assessment revealed a number of insights into architecture decisions for establishing a colony on the Martian surface. If crops are used as the sole food source, they will produce unsafe oxygen levels in the habitat. Furthermore, the ISRU system mass estimate is 8% of the mass of the resources it would produce over a two year period. That being said, the ISRU technology required to produce nitrogen, oxygen, and water on the surface of Mars is at a relatively low Technology Readiness Level (TRL), so such findings are preliminary at best. A spare parts analysis revealed that spare parts quickly come to dominate resupply mass as the settlement grows: after 130 months on the Martian surface, spare parts compose 62% of the mass brought from Earth to the Martian surface. The space logistics analysis revealed that, for the best scenario considered, establishing the first crew for a Mars settlement will require approximately 15 Falcon Heavy launchers and require $4.5 billion in funding, and these numbers will grow with additional crews. It is important to note that these numbers are derived only when considering the launch of life support and ISRU systems with spare parts. To capture a more realistic estimate of mission cost, future work should consider development and operations costs, as well as the integration of other key mission elements, such as communications and power systems. Technology development towards improving the reliability of life support systems, the TRL of ISRU systems, and the capability of Mars in-situ manufacturing will have a significant impact on reducing the mass and cost of Mars settlement architectures.

Towards Earth independence - tradespace exploration of long-duration crewed Mars surface system architectures

Abstract: In recent years, an unprecedented level of interest has grown around the prospect of sending humans to Mars for the exploration and eventual settlement of that planet. With the signing of the 2010 NASA Authorization Act, this goal became the official policy of the United States and consequently, has become the long-term objective of NASA's human spaceflight activities. A review of past Mars mission planning efforts, however, reveals that while numerous analyses have studied the challenges of transporting people to the red planet, relatively little analyses have been performed in characterizing the challenges of sustaining humans upon arrival. In light of this observation, this thesis develops HabNet - an integrated Habitation, Environmental Control and Life Support (ECLS), In-Situ Resource Utilization (ISRU), and Supportability analysis framework - and applies it to three different Mars mission scenarios to analyze the impacts of different system architectures on the costs of deploying and sustaining a continuous human presence on the surface of Mars. Through these case studies, a number of new insights on the mass-optimality of Mars surface system architectures are derived. The most significant of these is the finding that ECLS architecture mass-optimality is strongly dependent on the cost of ISRU - where open-loop ECLS architectures become mass-optimal when the cost of ISRU is low, and ECLS architectures with higher levels of resource recycling become mass-optimal when the cost of ISRU is high. For the Martian surface, the relative abundance of resources equates to a low cost of ISRU, which results in an open-loop ECLS system supplemented with ISRU becoming an attractive, if not dominant surface system architecture, over a range of mission scenarios and ISRU performance levels. This result, along with the others made in this thesis, demonstrates the large potential of integrated system analyses in uncovering previously unseen trends within the Mars mission architecture tradespace. By integrating multiple traditionally disparate spaceflight disciplines into a unified analysis framework, this thesis attempts to make the first steps towards codifying the human spaceflight mission architecting process, with the ultimate goal of enabling the efficient evaluation of the architectural decisions that will shape humanity's expansion into the cosmos.

Performance Characterization and Simulation of Amine-Based Vacuum Swing Sorption Units for Spacesuit Carbon Dioxide and Humidity Control

Abstract: Controlling carbon dioxide (CO2) and water (H2O) concentrations in the vapor phase of a space suit is critical to ensuring an astronauts safety, comfortability, and capability to perform extra-vehicular activity (EVA) tasks. Historically, this has been accomplished using lithium hydroxide (LiOH) and metal oxides (MetOx). Lithium hydroxide is a consumable material and requires priming with water before it becomes effective at removing carbon dioxide. MetOx is regenerable through a power-intensive thermal cycle but is significantly heavier on a volume basis than LiOH. As an alternative, amine-based vacuum swing beds are under aggressive development for EVA applications which control atmospheric concentrations of both CO2 and H2O through a fully-regenerative process. The current concept, referred to as the rapid cycle amine (RCA), has resulted in numerous laboratory prototypes. Performance of these prototypes have been assessed and documented from experimental and theoretical perspectives. To support developmental efforts, a first principles model has also been established for the vacuum swing adsorption technology. The efforts documented herein summarize performance characterization and simulation results for several variable metabolic profiles subjected to the RCA. Furthermore, a variety of control methods are explored including timed swing cycles, instantaneous CO2 feedback control, and time-averaged CO2 feedback control. A variety of off-nominal tests are also explored including high/low suit temperatures, increasingly high humidity cases, and dynamic pressure cases simulating the suit pre-breathe protocol. Consequently, this work builds on efforts previous efforts to fully bound the performance of the rapid cycle amine under a variety of nominal and off-nominal conditions.

Status of the Space Station water reclamation and management subsystem design concept

Abstract: A development status report is presented for the NASA Space Station's water reclamation and management (WRM) system, for which the candidate phase change-employing processing technologies are an air evaporation subsystem, a thermoelectric integrated membrane evaporation subsystem, and the vapor compression distillation subsystem. These WRM candidates employ evaporation to effect water removal from contaminants, but differ in their control of the vapor/liquid interface in zero-gravity and in the recovery of the latent heat of vaporization.