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  • 1
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    Preliminary design of the Space Station internal thermal control system (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The baseline preliminary design configuration of the Internal Thermal Control system (ITCS) of the U.S. Space Station pressurized elements (i.e., the Habitation and U.S. Laboratory modules, pressurized logistics carrier, and resources nodes) is defined. The ITCS is composed of both active and passive components. The subsystems which comprise the ITCS are identified and their functional descriptions are provided. The significant trades and analyses, which were performed during Phase B (i.e., the preliminary design phase) that resulted in the design described herein, are discussed. The ITCS interfaces with the station's central Heat Rejection and Transport System (HRTS), other systems, and externally attached pressurized payloads are described. Requirements on the ITCS with regard to redundancy and experiment support are also addressed.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: SAE PAPER 871505
    Format: text
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  • 2
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    Thermal/Fluid Analysis of a Composite Heat Exchanger for Use on the RLV Rocket Engine (2001)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: As part of efforts to design a regeneratively cooled composite nozzle ramp for use on the reusable vehicle (RLV) rocket engine, a C-SiC composite heat exchanger concept was proposed for thermal performance evaluation. To test the feasibility of the concept, sample heat exchanger panels were made to fit the Glenn Research Center's cell 22 for testing. Operation of the heat exchanger was demonstrated in a combustion environment with high heat fluxes similar to the RLV Aerospike Ramp. Test measurements were reviewed and found to be valuable for the on-going fluid and thermal analysis of the actual RLV composite ramp. Since the cooling fluid for the heat exchanger is water while the RLV Ramp cooling fluid is LH2, fluid and therma models were constructed to correlate to the specific test set-up. The knowledge gained from this work will be helpful for analyzing the thermal response of the actual RLV Composite Ramp. The coolant thermal properties for the models are taken from test data. The heat exchanger's cooling performance was analyzed using the Generalized Fluid System Simulation Program (GFSSP). Temperatures of the heat exchanger's structure were predicted in finite element models using Patran and Sinda. Results from the analytical models and the tests show that RSC's heat exchanger satisfied the combustion environments in a series of 16 tests.
    Keywords: Spacecraft Propulsion and Power
    Type: Thermal Fluid Analysis Workshop; Sep 10, 2001 - Sep 14, 2001; Huntsville, AL; United States
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  • 3
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    Thermal Design, Analysis, and Testing of the Quench Module Insert Bread Board (2001)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The science requirements for materials processing is to provide the desired PI requirements of thermal gradient, solid/liquid interface front velocity for a given processing temperature desired by the PI. Processing is performed by translating the furnace with the sample in a stationary position to minimize any disturbances to the solid/liquid interface front during steady state processing. Typical sample materials for this metals and alloys furnace are lead-tin alloys, lead-antimony alloys, and aluminum alloys. Samples must be safe to process and therefore typically are contained with hermetically sealed cartridge tubes (gas tight) with inner ceramic liners (liquid tight) to prevent contamination and/or reaction of the sample material with the cartridge tube.
    Keywords: Space Processing
    Type: Thermal and Fluids Analysis Workshop; Sep 10, 2001 - Sep 14, 2001; Huntsville, AL; United States
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  • 4
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    Fundamental Boiling and RP-1 Freezing Experiments (2001)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper describes results from experiments performed to help understand certain aspects of the MC-1 engine prestart thermal conditioning procedure. The procedure was constrained by the fact that the engine must chill long enough to get quality LOX at the LOX pump inlet but must be short enough to prevent freezing of RP-1 in the fuel pump. A chill test of an MC-1 LOX impeller was performed in LN2 to obtain data on film boiling, transition boiling and impeller temperature histories. The transition boiling data was important to the chill time so a subsequent experiment was performed chilling simple steel plates in LOX to obtain similar data for LOX. To address the fuel freezing concern, two experiments were performed. First, fuel was frozen in a tray and its physical characteristics were observed and temperatures of the fuel were measured. The result was physical characteristics as a function of temperature. Second was an attempt to measure the frozen thickness of RP-1 on a cold wall submerged in warm RP-1 and to develop a method for calculating that thickness for other conditions.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: Thermal and Fluids Analysis Workshop; Sep 10, 2001 - Sep 14, 2001; Huntsville, AL; United States
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  • 5
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    Comparison of Analytical and Numerical Performance Predictions for a Regenerative Heat Exchanger in the International Space Station Node 3 Internal Active Thermal Control System (2001)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The complexity of International Space Station (ISS) systems modeling often necessitates the concurrence of various dissimilar, parallel analysis techniques to validate modeling. This was the case with a feasibility and performance study of the ISS Node 3 Regenerative Heat Exchanger (RHX). A thermo-hydraulic network model was created and analyzed in SINDA/FLUINT. A less complex, closed form solution of the system dynamics was created using Excel. The purpose of this paper is to provide a brief description of the modeling processes utilized, the results and benefits of each to the ISS Node 3 RHX study.
    Keywords: Numerical Analysis
    Type: Thermal and Fluids Analysis Workshop; Sep 10, 2001 - Sep 14, 2001; Huntsville, AL; United States
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  • 6
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    Thermal Analysis of the MC1 Engine Turbopump (2001)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The MC1 Engine turbopump supplied the propellants to the main injector. The turbopump consisted of four parts; lox pump, interpropellant seal package (IPS), RP pump and turbine. The thermal analysis was divided into two 2D finite element models; Housing or stationary parts and rotor or rotating parts. Both models were analyzed at the same boundary conditions using SINDA. The housing model consisted of, lox pump housing, ips housing, RP housing, turbine inlet housing, turbine housing, exit guide vane, heat shield and both bearing outer races. The rotor model consisted of the lox impeller; lox end bearing and id race, RP impeller, and RP bearing and id race, shaft and turbine disk. The objectives of the analysis were to: (1) verified the original design and recommend modifications to it, (2) submitted a thermal environment to support the structural analysis, (3) support the component and engine test program. and (4) to support the X34 vehicle program.
    Keywords: Quality Assurance and Reliability
    Type: Thermal and Fluids Analysis Workshop (TFAWS) 2001; Sep 10, 2001 - Sep 14, 2001; Huntsville, AL; United States
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  • 7
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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 (2001)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    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., US Laboratory module) contain a fluid accumulator to accommodate 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 phase. During this time the element loop is a stand alone closed individual system. The solution approach for accommodating 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: Launch Vehicles and Launch Operations
    Type: Thermal and Fluids Analysis Workshop; Sep 10, 2001 - Sep 14, 2001; Huntsville, AL; United States
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  • 8
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    Thermal Analysis in Support of the Booster Separation Motor Crack Investigation (2001)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: During a post-test inspection of a Booster Separation Motor (BSM) from a Lot Acceptance Test (LAT), a crack was noticed in the graphite throat. Since this was an out-of-family occurrence, an investigation team was formed to determine the cause of the crack. This paper will describe thermal analysis techniques used in support of this investigation. Models were generated to predict gradients in nominal motor conditions, as well as potentially anomalous conditions. Analysis was also performed on throats that were tested in the Laser Hardened Material Evaluation Laboratory (LHMEL). Some of these throats were pre-cracked, while others represented configurations designed to amplify effects of thermal stresses. Results from these analyses will be presented in this paper.
    Keywords: Spacecraft Propulsion and Power
    Type: 2001 Thermal and Fluids Analysis Workshop; Sep 10, 2001 - Sep 14, 2001; Huntsville, AL; United States
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  • 9
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    An Analysis of an Automatic Coolant Bypass in the International Space Station Node 2 Internal Active Thermal Control System (2001)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A challenging part of International Space Station (ISS) thermal control design is the ability to incorporate design changes into an integrated system without negatively impacting performance. The challenge presents itself in that the typical ISS Internal Active Thermal Control System (IATCS) consists of an integrated hardware/software system that provides active coolant resources to a variety of users. Software algorithms control the IATCS to specific temperatures, flow rates, and pressure differentials in order to meet the user-defined requirements. What may seem to be small design changes imposed on the system may in fact result in system instability or the temporary inability to meet user requirements. The purpose of this paper is to provide a brief description of the solution process and analyses used to implement one such design change that required the incorporation of an automatic coolant bypass in the ISS Node 2 element.
    Keywords: Man/System Technology and Life Support
    Type: Thermal and Fluids Analysis Workshop; Sep 10, 2001 - Sep 14, 2001; Huntsville, AL; United States
    Format: application/pdf
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