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  • Spacecraft Design, Testing and Performance  (9)
  • ASTRONOMY
  • 2010-2014  (2)
  • 2000-2004  (7)
  • 1
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    Analytical Assessment of a Gross Leakage Event Within the International Space Station (ISS) Node 2 Internal Active Thermal Control System (IATCS) (2001)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Results of the International Space Station (ISS) Node 2 Internal Active Thermal Control System (IATCS) gross leakage analysis are presented for evaluating total leakage flow rates and volume discharge caused by a gross leakage event (i.e. open boundary condition). A Systems Improved Numerical Differencing Analyzer and Fluid Integrator (SINDA85/FLUINT) thermal hydraulic mathematical model (THMM) representing the Node 2 IATCS was developed to simulate system performance under steady-state nominal conditions as well as the transient flow effect resulting from an open line exposed to ambient. The objective of the analysis was to determine the adequacy of the leak detection software in limiting the quantity of fluid lost during a gross leakage event to within an acceptable level.
    Keywords: Spacecraft Design, Testing and Performance
    Type: The Tenth Thermal and Fluids Analysis Workshop; NASA/CP-2001-211141
    Format: application/pdf
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  • 2
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    Assessment and Accommodation of Thermal Expansion of the Internal Active Thermal Control System Coolant During Launch to On-Orbit Activation of International Space Station Elements (2002)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The International Space Station (ISS) employs an Internal Active Thermal Control System (IATCS) comprised of several single-phase water coolant loops. These coolant loops are distributed throughout the ISS pressurized elements. The primary element coolant loops (i.e. U.S. Laboratory module) contain a fluid accumulator to accomodate thermal expansion of the system. Other element coolant loops are parasitic (i.e. Airlock), have no accumulator, and require an alternative approach to insure that the system maximum design pressure (MDP) is not exceeded during the Launch to Activation (LTA) phase. During this time the element loops is a stand alone closed system. The solution approach for accomodating thermal expansion was affected by interactions of system components and their particular limitations. The mathematical solution approach was challenged by the presence of certain unknown or not readily obtainable physical and thermodynamic characteristics of some system components and processes. The purpose of this paper is to provide a brief description of a few of the solutions that evolved over time, a novel mathematical solution to eliminate some of the unknowns or derive the unknowns experimentally, and the testing and methods undertaken.
    Keywords: Spacecraft Design, Testing and Performance
    Type: Twelfth Thermal and Fluids Analysis Workshop; NASA/CP-2002-211783
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  • 3
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    Effects of Surfactant Contamination on the Next Generation Gas Trap for the ISS Internal Thermal Control System (2004)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: The current dual-membrane gas trap is designed to remove non-condensed gas bubbles from the Internal Thermal Control System (ITCS) coolant on board the International Space Station (ISS). To date it has successfully served its purpose of preventing gas bubbles from causing depriming, overspeed, and shutdown of the ITCS pump. However, contamination in the ITCS coolant has adversely affected the gas venting rate and lifetime of the gas trap, warranting a development effort for a next-generation gas trap. Previous testing has shown that a hydrophobic-only design is capable of performing even better than the current dual-membrane design for both steady-state gas removal and gas slug removal in clean deionized water. This paper presents results of testing to evaluate the effects of surfactant contamination on the steady-state performance of the hydrophobic-only design.
    Keywords: Spacecraft Design, Testing and Performance
    Type: SAE-04ICES-203 , 2004 International Conference on Environmental Systems 34th Annual Meeting; Jul 19, 2004 - Jul 22, 2004; Colorado Springs, CO; United States
    Format: text
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  • 4
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    Case Study of Risk Mitigation Based on Hardware/Software Integration (HSI) Testing for the International Space Station (ISS) Node 2 Module (2004)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: Within the pressurized elements of the International Space Station (ISS), requirements exist to ensure a safe, habitable environment for the crew. In order to provide this environment, thermal control components work in conjunction with software controls to provide heat rejection for subsystem avionics equipment, for the environmental control system and for experiment payloads. It is essential to ISS operations, mission success and crew safety that necessary testing incorporates the extreme conditions to ensure proper performance. This paper provides a general description and methodology applied to thermal related Hardware/Software Integration (HSI) tests for the ISS Node 2 module. A detailed test plan was developed and implemented with two objectives: the first was for risk mitigation of the thermal control algorithms and software qualification, and the second was for data collection which will substantiate thermalhydraulic models of the Internal Active Thermal Control System (IATCS). Analytical models are utilized to determine on-orbit performance for conditions and scenarios where the simulation of actual on-orbit system performance is limited by test configuration constraints. Node 2 IATCS HSI activities were performed at the Alenia Spazio facility in Torino, Italy with participation from the National Aeronautics and Space Administration (NASA), Alenia Spazio, Jacobs Engineering Sverdrup (JE Sverdrup) and Boeing.
    Keywords: Spacecraft Design, Testing and Performance
    Type: French Aviation and Space Association Complex and Safe Systems Engineering Conference; Jun 21, 2004 - Jun 22, 2004; Paris; France
    Format: text
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  • 5
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    Recent Operational Experience with the Internal Thermal Control System Dual-Membrane Gas Trap (2004)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A dual-membrane gas trap is currently used to remove gas bubbles from the Internal Thermal Control System (ITCS) coolant on board the International Space Station. The gas trap consists of concentric tube membrane pairs, comprised of outer hydrophilic tubes and inner hydrophobic fibers. Liquid coolant passes through the outer hydrophilic membrane, which traps the gas bubbles. The inner hydrophobic fiber allows the trapped gas bubbles to pass through and vent to the ambient atmosphere in the cabin. The gas removal performance and operational lifetime of the gas trap have been affected by contamination in the ITCS coolant. However, the gas trap has performed flawlessly with regard to its purpose of preventing gas bubbles from causing depriming, overspeed, and shutdown of the ITCS pump. This paper discusses on-orbit events over the course of the last year related to the performance and functioning of the gas trap.
    Keywords: Spacecraft Design, Testing and Performance
    Type: SAE-04ICES-201 , 2004 International Conference on Environmental Systems 34th Annual Meeting; Jul 19, 2004 - Jul 22, 2004; Colorado Springs, CO; United States
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  • 6
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    International Space Station Internal Thermal Control System Cold Plate/Fluid-Stability Test: Two Year Update (2003)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Operation of the Internal Thermal Control System (ITCS) Cold Plate/Fluid-Stability Test Facility commenced on September 5, 2000. The facility was intended to provide advance indication of potential problems on board the International Space Station (ISS) and was designed: 1) To be materially similar to the flight ITCS. 2) To allow for monitoring during operation. 3) To run continuously for three years. During the first two years of operation the conditions of the coolant and components were remarkably stable. During this same period of time, the conditions of the ISS ITCS significantly diverged from the desired state. Due to this divergence, the test facility has not been providing information useful for predicting the flight ITCS condition. Results of the first two years are compared with flight conditions over the same time period, showing the similarities and divergences. To address the divergences, the test facility was modified incrementally to more closely match the flight conditions, and to gain insight into the reasons for the divergence. Results of these incremental changes are discussed and provide insight into the development of the conditions on orbit.
    Keywords: Spacecraft Design, Testing and Performance
    Type: SAE Paper-2003-01-2518 , 33rd International Conference on Environmental Systems; Jul 07, 2003 - Jul 10, 2003; Vancouver, BC; Canada
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  • 7
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    Cryogenic Propellant Storage and Transfer Technology Demonstration: Prephase A Government Point-of-Departure Concept Study (2012)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The primary purpose of this study was to define a point-of-departure prephase A mission concept for the cryogenic propellant storage and transfer technology demonstration mission to be conducted by the NASA Office of the Chief Technologist (OCT). The mission concept includes identification of the cryogenic propellant management technologies to be demonstrated, definition of a representative mission timeline, and definition of a viable flight system design concept. The resulting mission concept will serve as a point of departure for evaluating alternative mission concepts and synthesizing the results of industry- defined mission concepts developed under the OCT contracted studies
    Keywords: Spacecraft Design, Testing and Performance
    Type: NASA/TM-2012-217467 , M-1343
    Format: application/pdf
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  • 8
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    Benefits of Operational Consideration into the Guidance, Navigation, and Control Design of Spacecraft (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The following paper points out historical examples where operational consideration into the GN&C design could have helped avoid operational complexity, reduce costs, ensure the ability for a GN&C system to be able to adapt to failures, and in some cases might have helped save mission objectives. A costly repeat of mistakes could befall a program if previous operational lessons, especially from operators of vehicles with similar GN&C systems, are not considered during the GN&C design phase of spacecraft. The information gained from operational consideration during the design can lead to improvements of the design, allow less ground support during operations, and prevent repetition of previous mistakes. However, this benefit can only occur if spacecraft operators adequately capture lessons learned that would improve future designs for operations and those who are designing spacecraft incorporate inputs from those that have previously operated similar GN&C systems.
    Keywords: Spacecraft Design, Testing and Performance
    Type: JSC-CN-22520 , AIAA Guidance, Navigation and Control Conference; Aug 08, 2011 - Aug 11, 2011; Portland, OR; United States
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  • 9
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    EXPRESS Pallet Payload Interface Requirements (2004)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A viewgraph presentation describing the EXPRESS Pallet Space Station payload interface requirements is shown. The topics include: 1) External Payload Sites; 2) EXPRESS Pallet with Six Payload Envelopes; 3) EXPRESS Pallet in Payload Bay Representative Layout; 4) EXPRESS Pallet Installation SSRMS positions pallet for PAS mating on S3 truss; 5) EXPRESS Pallet Major Components; 6) EXPRESS Pallet Adapter; 7) EXPRESS Pallet Center Location Payload Envelope; 8) Envelope Restriction for EXPRESS Pallet Corner Payload Locations; 9) EXPRESS Pallet-PAS Truss Configuration; and 10) EXPRESS Pallet Payload Services and Specifications.
    Keywords: Spacecraft Design, Testing and Performance
    Type: X-ray Source Based Navigation Industry Day; Aug 19, 2004; Arlington, VA; United States
    Format: application/pdf
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