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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.

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NASA NTRS2023

Cryogenic Oxygen Storage Modules with Carbon Dioxide Sequestration for Environmental Control and Life Support Applications

NASA Kennedy Space Center engineers developed a Cryogenic Oxygen Storage Module (COSM) to store oxygen in solid-state form and deliver it as a gas to an end-use environmental control and/or life support system. Additionally, the COSM can scrub out nuisance or containment gases such as carbon dioxide and/or water vapor in conjunction with supplying oxygen, forming a synergistic system when used in a closed-loop application. Closed-loop life support systems require both oxygen supply and removal of toxic or nuisance gases such as CO2 from the breathing loop. In most deployed systems, these two requirements are accomplished independently. COSM combines these capabilities to work simultaneously which may allow for reduced system volume, mass, complexity and cost of a rebreathing device.

Jeffrey A Kohler↗
NASA NTRS1987

Technology demonstrator program for Space Station Environmental Control Life Support System

The main objectives and requirements of the NASA/Marshall Space Flight Center Technology Demonstration Program are discussed. The program consists of a comparative test and a 90-day manned system test to evaluate an Environmental Control and Life Support System (ECLSS). In the comparative test phase, 14 types of subsystems which perform oxygen and water reclamation functions are to be examined in terms of performance maintenance/service requirements, reliability, and safety. The manned chamber testing phase involves a four person crew using a partial ECLSS for 90 days. The schedule for the program and the program hardware requirements are described.

Adams, Alan M.↗
NASA NTRS1992

The environmental control and life-support system for a lunar base: What drives its design

The purpose of this paper is to identify and briefly discuss some of the ground rules and mission scenario details that become drivers of the environmental control and life support (ECLS) system design and of the logistics related to the design. This paper is written for mission planners and non-ECLS system engineers to inform them of the details that will be important to the ECLS engineer when the design phase is reached. In addition, examples illustrate the impact of some selected mission characteristics on the logistics associated with ECLS systems. The last section of this paper focuses on the ECLS system technology development sequence and highlights specific portions that need emphasis.

Hypes, Warren D.↗
NASA NTRS2007

Boeing Crew Exploration Vehicle Environmental Control and Life Support System Architecture Overview

The Boeing Company under the teaming agreement with the Northrop Grumman Systems Corporation and in compliance with the NASA Phase 1 contract, had the responsibilities for the CEV architecture development of the Environmental control and life support (ECLS) system under the NASA Phase 1 contract. The ECLS system was comprised of the various subsystems which provided for a shirt-sleeve habitable environment for crew to live and work in the crew module of the CEV. This architecture met the NASA requirements to ferry cargo and crew to ISS, and Lunar sortie missions, with extensibility to long duration missions to Moon and MARS. This paper provides a summary overview of the CEV ECLS subsystems which was proposed in compliance with the contract activities.

Saiidi, Mo↗
NASA NTRS2019

Electrochemical, Polarization, and Crevice Corrosion Testing of Inconel X750: A Supplement to the Environmental Control and Life Support System Sustaining Metal Materials Compatibility Study

In previous studies, electrochemical test results were experimentally acquired and then presented for several noble alloys in two specific solutions representative of waste liquids generated or present within the Environmental Control and Life Support System (ECLSS) aboard the International Space Station (ISS). Subsequently, another metal candidate, Inconel X750, has been submitted and was subjected to the same test routines in the same solutions and evaluated with the same statistical/analytical methodologies as those utilized in the earlier studies. Previous studies included three titanium grades, (Commercially Pure, 6Al-4V alloy, and 6Al-4V Low Interstitial alloy), two nickel-chromium alloys (Inconel® 625 and Hastelloy® C276), one high tier stainless steel (Cronidur® 30), and a nickel-titanium alloy (Nitinol 60). Thus far, all candidate alloys have exhibited excellent corrosion protection and galvanic compatibility attributes and have been deemed qualified materials for application within the ECLSS facility. Inconel X750 now joins that group. The titanium alloys gave the best results of all the metal candidates by demonstrating superior nobility and galvanic protection properties. It is worth noting that the corrosion performance properties for the three titanium alloys were essentially indistinguishable. As such and for expediency, this study and all future evaluations will refer only to the comparative properties already documented for Titanium 6Al-4V as this alloy is representative of all three alloys and considered to be more mainstream. Now the measured corrosion properties for Inconel X750 were very similar to those determined previously for Inconel 625 and Hastelloy C276 which were also determined to be very high performers. For the current effort, the results have clearly shown that Inconel X750 possesses exceptional anti-corrosion attributes comparable to metals in the highest tier of the galvanic series. Overall, one can conclude that Inconel X750 is quite noble, highly corrosion resistant and galvanically compatible with the other metal groups from both an electrochemical perspective and a long-term exposure scenario. This was clearly demonstrated after utilizing the same techniques as those applied in previous studies which included linear, Tafel and cyclic polarization, galvanic coupling with each of the other metal candidates, and pitting/crevicing assessments after one full year of immersion in the subject test solutions. Attributes defining the nobility and anti-corrosion capabilities for X750 appear to be on par with all the other candidates thus far and this alloy can now be classified as ‘excellent’ exhibiting very high resistance toward general, localized, and galvanic corrosion in the subject test media.

Lee, R. E.↗
NASA NTRSDate not supplied

Utilizing Gaps and Key Performance Parameters to Inform NASA Environmental Control and Life Support Capability Technology Decisions

Human spaceflight is a complex endeavor requiring multiple capabilities for transportation, crew health, scientific goals, and safe return to Earth. The difference between spaceflight proven capabilities and those needed for future exploration architectures is defined as a capability gap. Capability gaps are not technology specific. Each capability gap may be closed with a wide array of technologies that have unique benefits and challenges. Determining what a capability’s relevant and distinguishing key performance parameters (KPPs) are for a mission is critical. Mass, power, and volume are always constrained and important, but defining these in a way normalized by performance is very important. KPP definition for reliability, dormancy, and integration needs are hard to define but critical. Outside of technical considerations, the programmatic factors of the estimated time to develop the technology vs when a mission element is also a strong consideration in which technologies should be pursued. The Environmental Control and Life Support (ECLSS) capability areas include: life support, environmental monitoring, fire safety, and logistics. These capability areas are decomposed to high level gaps. While KPPs should be technology agnostic, they can be used to both compare technologies and measure progress of technology development over time. KPPs help define when the gap is closed, and the core mission objectives can be accomplished. Proposed technology improvements to enhance a capability should balance improved KPPs and against investments in other capabilities that are not yet closed. A selection of ECLSS gaps and KPPs and their formulation, current state, and how they inform capability roadmap planning are discussed.

Life Support↗
NASA NTRS2010

Evaluating the Applicability of Heritage Flight Hardware in Orion Environmental Control and Life Support Systems

Recent changes in the overall NASA vision has resulted in further cost and schedule challenges for the Orion program. As a result, additional scrutiny has been focused on the use of new developments for hardware in the environmental control and life support systems. This paper will examine the Orion architecture as it is envisioned to support missions to the International Space Station and future exploration missions and determine what if any functions can be satisfied through the use of existing, heritage hardware designs. An initial evaluation of each component is included and where a heritage component was deemed likely further details are examined. Key technical parameters, mass, volume and vibration loads are a few of the specific items that are evaluated. Where heritage hardware has been identified that may be substituted in the Orion architecture a discussion of key requirement changes that may need to be made as well as recommendation to further evaluate applicability are noted.

Cross, Cynthia D.↗
NASA NTRS2011

Evaluating the Applicability of Heritage Flight Hardware in Orion Environmental Control and Life Support Systems

Recent changes in the overall NASA vision has resulted in further cost and schedule challenges for the Orion program. As a result, additional scrutiny has been focused on the use of new developments for hardware in the environmental control and life support systems. This paper will examine the Orion architecture as it is envisioned to support missions to the International Space Station and future exploration missions and determine what if any functions can be satisfied through the use of existing, heritage hardware designs. An initial evaluation of each component is included and where a heritage component was deemed likely further details are examined. Key technical parameters, mass, volume and vibration loads are a few of the specific items that are evaluated. Where heritage hardware has been identified that may be substituted in the Orion architecture a discussion of key requirement changes that may need to be made as well as recommendation to further evaluate applicability are noted.

Cross, Cynthia D.↗
NASA NTRS2000

International Space Station Sustaining Engineering: A Ground-Based Test Bed for Evaluating Integrated Environmental Control and Life Support System and Internal Thermal Control System Flight Performance

As the International Space Station's (ISS) various habitable modules are placed in service on orbit, the need to provide for sustaining engineering becomes increasingly important to ensure the proper function of critical onboard systems. Chief among these are the Environmental Control and Life Support System (ECLSS) and the Internal Thermal Control System (ITCS). Without either, life onboard the ISS would prove difficult or nearly impossible. For this reason, a ground-based ECLSS/ITCS hardware performance simulation capability has been developed at NASA's Marshall Space Flight Center. The ECLSS/ITCS Sustaining Engineering Test Bed will be used to assist the ISS Program in resolving hardware anomalies and performing periodic performance assessments. The ISS flight configuration being simulated by the test bed is described as well as ongoing activities related to its preparation for supporting ISS Mission 5A. Growth options for the test facility are presented whereby the current facility may be upgraded to enhance its capability for supporting future station operation well beyond Mission 5A. Test bed capabilities for demonstrating technology improvements of ECLSS hardware are also described.

Ray, Charles D.↗
NASA NTRS2009

Node 3 Relocation Environmental Control and Life Support System Modification Kit Verification and Updated Status

Node 1 (Unity) flew to International Space Station (ISS) on Flight 2A. Node 1 was the first module of the United States On-Orbit Segment (USOS) launched to ISS. The Node 1 ISS Environmental Control and Life Support (ECLS) design featured limited ECLS capability. The main purpose of Node 1 was to provide internal storage by providing four stowage rack locations within the module and to allow docking of multiple modules and a truss segment to it. The ECLS subsystems inside Node 1 were routed through the element prior to launch to allow for easy integration of the attached future elements, particularly the Habitation Module which was planned to be located at the nadir docking port of Node 1. After Node 1 was on-orbit, the Program decided not to launch the Habitation Module and instead, to replace it with Node 3 (Tranquility). In 2007, the Program became concerned with a potential Russian docking port approach issue for the Russian FGB nadir docking port after Node 3 is attached to Node 1. To solve this concern the Program decided to relocate Node 3 from Node 1 nadir to Node 1 port. To support the movement of Node 3 the Program decided to build a modification kit for Node 1, an on-orbit feedthrough leak test device, and new vestibule jumpers to support the ECLS part of the relocation. This paper provides a design overview of the modification kit, a summary of the Node 1 ECLS re-verification to support the Node 3 relocation from Node 1 nadir to Node 1 port, and a status of the ECLS modification kit installation into Node 1.

Williams, David E.↗
NASA NTRS2010

Node 3 Relocation Environmental Control and Life Support System Modification Kit Verification and Updated Status

Node 1 (Unity) flew to International Space Station (ISS) on Flight 2A. Node 1 was the first module of the United States On-Orbit Segment (USOS) launched to ISS. The Node 1 ISS Environmental Control and Life Support (ECLS) design featured limited ECLS capability. The main purpose of Node 1 was to provide internal storage by providing four stowage rack locations within the module and to allow docking of multiple modules and a truss segment to it. The ECLS subsystems inside Node 1 were routed through the element prior to launch to allow for easy integration of the attached future elements, particularly the Habitation Module which was planned to be located at the nadir docking port of Node 1. After Node I was on-orbit, the Program decided not to launch the Habitation Module and instead, to replace it with Node 3 (Tranquility). In 2007, the Program became concerned with a potential Russian docking port approach issue for the Russian FGB nadir docking port after Node 3 is attached to Node 1. To solve this concern the Program decided to relocate Node 3 from Node I nadir to Node 1 port. To support the movement of Node 3 the Program decided to build a modification kit for Node 1, an on-orbit feedthrough leak test device, and new vestibule jumpers to support the ECLS part of the relocation. This paper provides a design overview of the modification kit for Node 1, a summary of the Node 1 ECLS re-verification to support the Node 3 relocation from Node 1 nadir to Node 1 port, and a status of the ECLS modification kit installation into Node 1.

Williams, David E.↗
NASA NTRS2018

International Space Station (ISS) Environmental Control and Life Support System (ECLSS) Vent Flow Reflection and Detection by Robotic External Leak Locator (RELL)

On-orbit Robotic External Leak Locator (RELL) (i.e., mass spectrometer and ion gauge) measurements on the International Space Station (ISS) are presented to show the detection of recurring Environmental Control and Life Support System (ECLSS) vents at multiple ISS locations and RELL pointing directions. The path of ECLSS effluents to the RELL detectors is not entirely obvious at some locations, but the data indicates that diffuse gas-surface reflection or scattering resulting from plume interaction with vehicle surfaces is responsible. RELL was also able to confirm the ISS ECLSS constituents and distinguish them from the ammonia leak based on the ion mass spectra and known venting times during its operation to locate a leak in the ISS port-side External Active Thermal Control System (EATCS) coolant loop.

Gas/Surface Reflections or Scattering↗
NASA NTRS2018

International Space Station (ISS) Environmental Control and Life Support System (ECLSS) Vent Flow Reflection and Detection by Robotic External Leak Locator (RELL)

On-orbit Robotic External Leak Locator (RELL) (i.e., mass spectrometer and ion gauge) measurements on the International Space Station (ISS) are presented to show the detection of recurring Environmental Control and Life Support System (ECLSS) vents at multiple ISS locations and RELL pointing directions. The path of ECLSS effluents to the RELL detectors is not entirely obvious at some locations, but the data indicates that diffuse gas-surface reflection or scattering resulting from plume interaction with vehicle surfaces is responsible. RELL was also able to confirm the ISS ECLSS constituents and distinguish them from the ammonia leak based on the ion mass spectra and known venting times during its operation to locate a leak in the ISS port-side External Active Thermal Control System (EATCS) coolant loop.

Gas/Surface Reflections or Scattering↗
NASA NTRS2023

Gateway Integrated Environmental Control and Life Support System Overview and Status

The Gateway will be a lunar orbiting platform that is a critical element in establishing a sustainable, long-term human presence on the lunar surface and beyond to deep space exploration. As part of this mission, the Gateway Environmental Control and Life Support Subsystem (ECLSS), employs its capabilities to: - Support two to four-person crew expeditions for at least 30 days, approximately once every one to three years with extended periods of dormancy, - Provide life support functionality during nominal and contingency scenarios, - Support crew expeditions to the Lunar surface by providing a Habitable volume, from which staging, or preparation can take place for missions to the Lunar surface or to deep space destinations, and - Facilitate a platform to demonstrate the necessary capabilities to expand a sustainable human presence into Deep Space, including the surface of the Moon and Mars. The Gateway consists of an assembly of modules provided by commercial and international partnerships with varied capability that, together, achieve these objectives. The Habitation and Logistics Outpost (HALO) and International Habitat (I-Hab) modules provide the air revitalization and conditioning capabilities for the Gateway with some ECLSS functionality provided in the other modules to support crew operations. This paper explains the architecture of the Gateway ECLSS and provides the status of its development.

Gateway↗
NASA NTRSDate not supplied

Gateway Integrated Environmental Control and Life Support System (ECLSS) Overview and Status

The Gateway comprised of modules provided by commercial and international partners will be a lunar orbiting platform that is a critical element in the Moon to Mars architecture. Of the 4 modules that comprise the Gateway, the core Environmental Control and Life Support System (ECLSS) is provided by the Habitation and Logistics Outpost (HALO) module provided by NASA, and the International Habitat (I-Hab) provided by the European Space Agency (ESA) with the ECLSS provided by the Japanese Space Agency (JAXA). These modules work together to provide pressure control, air revitalization, and air conditioning capabilities for the Gateway integrated habitable volumes and attached visiting vehicles during open hatch crewed operations. Individually, they maintain the internal atmosphere during the long periods of dormancy between crewed operations to support payload operations and ensure a safe environment when the crew returns. Additionally, NASA bolsters crew survivability by providing government furnished equipment (GFE) to support crew survival in the face of catastrophic hazards (such as fire or a cabin air leak) until the Gateway stack reaches a point in the orbit where crew can safely abort on Orion. This paper explains the key driving requirements, architecture, and development status of the Gateway ECLSS.

Gateway↗
NASA NTRS1990

Space Station Freedom environmental control and life support system phase 3 simplified integrated test detailed report

A description of the phase 3 simplified integrated test (SIT) conducted at the Marshall Space Flight Center (MSFC) Core Module Integration Facility (CMIF) in 1989 is presented. This was the first test in the phase 3 series integrated environmental control and life support systems (ECLSS) tests. The basic goal of the SIT was to achieve full integration of the baseline air revitalization (AR) subsystems for Space Station Freedom. Included is a description of the SIT configuration, a performance analysis of each subsystem, results from air and water sampling, and a discussion of lessons learned from the test. Also included is a full description of the preprototype ECLSS hardware used in the test.

Roberts, B. C.↗
NASA NTRS2024

Enhancing Future Commercial Space Stations: Applying ISS Insights to Environmental Control and Life Support Systems (ECLSS) Development

The expansion of space exploration to commercial space stations represents a shift from government-led endeavors to a new competitive era driven by private companies and innovative forces. The journey to actualize these celestial outposts is fraught with difficulties, including the intricate establishment of Environmental Control and Life Support systems (ECLSS) within these commercial space stations. By applying the insights gleaned from the ISS, particularly during the initial conceptual design phase of the commercial developments, there is an opportunity to circumvent some of the teething issues and optimize the development process. Furthermore, applying insights from the ISS ECLSS design, development, test, and maintenance phases has the potential to enhance system compatibility and mitigate the challenges associated with upgrading a fixed design. This approach can lead to lower costs due to fewer iterations and streamlined processes. This paper will conduct an in-depth evaluation of the ECLS system from both system and operational perspectives with the aim to provide a knowledge capture for early-stage design considerations to bolster the development of sustainable, efficient, and habitable commercial space stations.

ISS↗
NASA NTRSDate not supplied

Enhancing Future Commercial Space Stations: Applying ISS Insights to Environmental Control and Life Support Systems (ECLSS) Development

The expansion of space exploration to commercial space stations represents a shift from government-led endeavors to a new competitive era driven by private companies and innovative forces. The journey to actualize these celestial outposts is fraught with difficulties, including the intricate establishment of Environmental Control and Life Support systems (ECLSS) within these commercial space stations. By applying the insights gleaned from the ISS, particularly during the initial conceptual design phase of the commercial developments, there is an opportunity to circumvent some of the teething issues and optimize the development process. Furthermore, applying insights from the ISS ECLSS design, development, test, and maintenance phases has the potential to enhance system compatibility and mitigate the challenges associated with upgrading a fixed design. This approach can lead to lower costs due to fewer iterations and streamlined processes. This paper will conduct an in-depth evaluation of the ECLS system from both system and operational perspectives with the aim to provide a knowledge capture for early-stage design considerations to bolster the development of sustainable, efficient, and habitable commercial space stations.

ISS↗