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  • 1
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    Effect of idealized asymmetric inhibitor stubs on circumferential flow in the Space Shuttle SRM (1990)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 6; 5-10
    Format: text
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  • 2
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    Experimental determination of convective heat transfer coefficients in the separated flow region of the Space Shuttle Solid Rocket Motor (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A series of cold flow heat transfer tests was conducted with a 7.5-percent scale model of the Space Shuttle Rocket Motor (SRM) to measure the heat transfer coefficients in the separated flow region around the nose of the submerged nozzle. Modifications were made to an existing 7.5 percent scale model of the internal geometry of the aft end of the SRM, including the gimballed nozzle in order to accomplish the measurements. The model nozzle nose was fitted with a stainless steel shell with numerous thermocouples welded to the backside of the thin wall. A transient 'thin skin' experimental technique was used to measure the local heat transfer coefficients. The effects of Reynolds number, nozzle gimbal angle, and model location were correlated with a Stanton number versus Reynolds number correlation which may be used to determine the convective heating rates for the full scale Space Shuttle Solid Rocket Motor nozzle.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 90-0043
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  • 3
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    Semi-coupled flow and thermal analysis of the field joint during rapid pressurization of the redesigned solid rocket motor (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A transient, semi-coupled, multi-dimensional thermal and flow analysis methodology was developed to predict the thermal/gas dynamic conditions in the field joint region of the Redesigned Solid Rocket Motor (RSRM). Transient temperature response, pressure history, and combustion gas flow rate (within the field joint region), were of principle interest, in the course of this study. The thermal environment in the field joint was modeled using SINDA, a finite difference based thermal network analyzer. The combustion gas flow boundary condition was generated using the FLAP code; this code performs a transient, lumped-parameter, control volume analysis to solve the mass, momentum, and energy conservation equations. The FLAP computer code was modified to account for erosion of the NBR insulation material, following ignition. An independent grid sensitivity study was conducted to determine an appropriate grid distribution near the wall. The predicted results, obtained using an optimum grid distribution and computer generated flow boundary condition, were compared with subscale test data.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 92-0856
    Format: text
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  • 4
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    Circumferential flow analysis at the aft field joint of the Space Shuttle solid rocket motor (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Flow analyses have been performed to determine the nature of the three-dimensional flow field in the vicinity of the aft-most field joint of the Space Shuttle Redesigned Solid Rocket Motor (RSRM). Specific objectives included the quantification of the circumferential pressure and velocity gradients at the joint location which might be caused by the non-uniform erosion of the rubber inhibitor which protrudes from the wall into the flow field. Three-dimensional Navier-Stokes equations have been solved in conjunction with the conservation equation for the turbulence energy and the dissipation rate. The numerical predictions have been compared with the measurements from a 7.5 percent scale cold flow model of the redesigned solid rocket motor.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 88-3319
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  • 5
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    Fluid Transient Analysis During Priming of Evacuated Line (2017)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Pressure surges are critical in the design of spacecraft propellant feed lines. The pressure transients that occur during priming of feed lines are very important in the design and analysis of liquid propulsion systems. During the start-up of the propulsion system of a spacecraft, the process of filling of an evacuated pipeline is called priming. Priming can generate severe pressure peaks due to the slam (water hammer) of the propellant against a closed thruster valve. The downstream conditions strongly affect the pressure surge. In space systems, satellites, or interplanetary probes, the propellant lines are vacuum-pumped or filled with low pressure helium or nitrogen before the launch. Before operations, these lines are primed with a vaporizing liquid, sometimes in the presence of a non-condensable gas (NCG), which produces water hammer phenomena. The objective of the current study is to use a finite volume based network flow solver (Generalized Fluid System Simulation Program, GFSSP) for the numerical simulation of Priming in (a) a straight feedline and (b) a flow network. The geometrical configurations and dimensions for the pipe and other components used for the current study are identical to experimental study of Prickett et al.
    Keywords: Spacecraft Propulsion and Power; Fluid Mechanics and Thermodynamics
    Type: M17-5773 , AIAA/SAE/ASEE Joint Propulsion Conference (2017); Jul 10, 2017 - Jul 12, 2017; Atlanta, GA; United States
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  • 6
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    Adaptive Time Stepping for Transient Network Flow Simulation in Rocket Propulsion Systems (2017)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Fluid and thermal transients found in rocket propulsion systems such as propellant feedline system is a complex process involving fast phases followed by slow phases. Therefore their time accurate computation requires use of short time step initially followed by the use of much larger time step. Yet there are instances that involve fast-slow-fast phases. In this paper, we present a feedback control based adaptive time stepping algorithm, and discuss its use in network flow simulation of fluid and thermal transients. The time step is automatically controlled during the simulation by monitoring changes in certain key variables and by feedback. In order to demonstrate the viability of time adaptivity for engineering problems, we applied it to simulate water hammer and cryogenic chill down in pipelines. Our comparison and validation demonstrate the accuracy and efficiency of this adaptive strategy.
    Keywords: Computer Programming and Software; Spacecraft Propulsion and Power
    Type: M17-5801 , AIAA Propulsion And Energy Forum And Exposition; Jul 10, 2017 - Jul 12, 2017; Atlanta, GA; United States
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  • 7
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    Fluid Transient Analysis during Priming of Evacuated Line (2017)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Water hammer analysis in pipe lines, in particularly during priming into evacuated lines is important for the design of spacecraft and other in-space application. In the current study, a finite volume network flow analysis code is used for modeling three different geometrical configurations: the first two being straight pipe, one with atmospheric air and other with evacuated line, and the third case is a representation of a complex flow network system. The numerical results show very good agreement qualitatively and quantitatively with measured data available in the literature. The peak pressure and impact time in case of straight pipe priming in evacuated line shows excellent agreement.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: M17-6106 , AIAA Propulsion and Energy Forum; Jul 10, 2017 - Jul 12, 2017; Atlanta, GA; United States
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  • 8
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    Method and Apparatus for Predicting Unsteady Pressure and Flow Rate Distribution in a Fluid Network (2009)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: A method and apparatus for analyzing steady state and transient flow in a complex fluid network, modeling phase changes, compressibility, mixture thermodynamics, external body forces such as gravity and centrifugal force and conjugate heat transfer. In some embodiments, a graphical user interface provides for the interactive development of a fluid network simulation having nodes and branches. In some embodiments, mass, energy, and specific conservation equations are solved at the nodes, and momentum conservation equations are solved in the branches. In some embodiments, contained herein are data objects for computing thermodynamic and thermophysical properties for fluids. In some embodiments, the systems of equations describing the fluid network are solved by a hybrid numerical method that is a combination of the Newton-Raphson and successive substitution methods.
    Keywords: Fluid Mechanics and Thermodynamics
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  • 9
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    Modeling of Chill Down in Cryogenic Transfer Lines (2001)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: A numerical model to predict chill down in cryogenic transfer lines has been developed. Three chill down cases using hydrogen as the working fluid are solved: 1) a simplified model amenable to analytical solution, 2) a realistic model of superheated vapor flow, and 3) a realistic model of initially subcooled liquid flow. The first case compares a numerical model with an analytical solution with very good agreement between the two. Additionally, the analytical solution provides a convenient way to look at parametric effects on the chill down. The second and third cases are numerical models which provide temperature histories of the fluid and solid tube wall during chill down as well as several other quantities of interest such as pressure and mass flow rate. Of great interest is the ability to predict accurate values of chill down time (the time required to achieve steady-state cryogenic flow). The models predict that a 26 in. long, 3/16 in. ID aluminum tube has a shorter chill down time (approx. equal to 100 sec) and uses less hydrogen with superheated vapor flow than with initially subcooled liquid flow (greater than 200 sec for chill down).
    Keywords: Engineering (General)
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  • 10
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    Multi-Node Modeling of Cryogenic Tank Pressurization System Using Generalized Fluid System Simulation Program (2019)
    In:  CASI
    Details
    Publication Date: 2019-09-06
    Description: Cryogenic Tanks are pressurized by inert gas such as Helium or Nitrogen to maintain the required pressure of the propellant delivered to the turbo-pump of a liquid rocket engine. Thermo-fluid system simulation tools are used to analyze the pressurization process of a cryogenic tank. Most system level codes (GFSSP and ROCETS) use single node1 to represent ullage which is the gaseous space in the tank. Ullage space in a cryogenic tank is highly stratified because the entering inert gas is at ambient temperature whereas the liquid propellant is at a cryogenic temperature. A single node model does not account for the effect of temperature gradient in the ullage. High fidelity Navier-Stokes based CFD model of Tank Pressurization is not practical for running a long duration transient model with thousands and millions of nodes. A possible recourse is to construct a multi-node model with system level code that can account for ullage stratification.
    Keywords: Fluid Mechanics and Thermodynamics; Propellants and Fuels
    Type: M19-7155 , AIAA Propulsion and Energy Forum and Exposition; Aug 19, 2019 - Aug 22, 2019; Indianapolis, IN; United States
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