Update: A subscale solid rocket motor for characterization of submerged nozzle erosion

Andrew C. Cortopassi, J. Eric Boyer, Kenneth K. Kuo

    Research output: Chapter in Book/Report/Conference proceedingConference contribution

    9 Citations (Scopus)

    Abstract

    Current understanding of physical and chemical processes involved in the erosion of submerged nozzles by highly-aluminized solid propellants is limited. The ability to predict the surface erosion rate of a given carbon-cloth phenolic (CCP) nozzle material is very important for the future design or modification of large solid rocket boosters for space launch applications. Although current erosion codes provide engineering accuracy for nozzle throat erosion rates, calculated rates for the forward surfaces of the submerged nozzle can vary significantly from observed values. The overall objective of this research study under the NASA Constellation University Institutes Project (NASA-CUIP) is to improve the understanding of nozzle erosion and related phenomena. In previous work, the design of a subscale solid rocket motor was performed based upon engineering analysis of the interior ballistic process and a series of CFD simulations of the flow field in both the region of the submerged nozzle and the entire subscale motor. This motor design allows for the use of real-time X-ray radiography with a high-resolution image intensifier system to obtain submerged nozzle erosion data. An update on the design and fabrication of this subscale solid rocket motor is presented in the present work. In addition to this, 3D simulation of the internal flow-field of the rocket motor was performed including the effects of liquid alumina droplets. The modeling of the nozzle surface erosion, coupled with the flow field structure, addresses scientific understanding and characterization of the influence of a liquid layer formed due to deposition of Al2O3/Al droplets on the surface of the converging section of the submerged nozzle. Calculations have been performed which compute the accretion rate of alumina onto the nozzle surface, with accretion rates on the order of 20 kg/m2-s. As a part of the overall study, we examine several physicochemical processes on the nozzle surface due to the presence of this molten liquid layer. Future test results from this newly designed rocket motor will be highly beneficial for model validation as well as attaining in-depth understanding of interactions between the liquid alumina and nozzle materials.

    Original languageEnglish (US)
    Title of host publication45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
    StatePublished - 2009
    Event45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit - Denver, CO, United States
    Duration: Aug 2 2009Aug 5 2009

    Other

    Other45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
    CountryUnited States
    CityDenver, CO
    Period8/2/098/5/09

    Fingerprint

    Rocket engines
    rockets
    nozzles
    erosion
    Erosion
    Nozzles
    aluminum oxide
    flow field
    liquid
    erosion rate
    droplet
    accretion
    engineering
    radiography
    Flow fields
    flow distribution
    Alumina
    aluminum oxides
    model validation
    Liquids

    All Science Journal Classification (ASJC) codes

    • Aerospace Engineering
    • Control and Systems Engineering
    • Space and Planetary Science
    • Energy(all)
    • Electrical and Electronic Engineering
    • Mechanical Engineering

    Cite this

    Cortopassi, A. C., Boyer, J. E., & Kuo, K. K. (2009). Update: A subscale solid rocket motor for characterization of submerged nozzle erosion. In 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
    Cortopassi, Andrew C. ; Boyer, J. Eric ; Kuo, Kenneth K. / Update : A subscale solid rocket motor for characterization of submerged nozzle erosion. 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. 2009.
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    title = "Update: A subscale solid rocket motor for characterization of submerged nozzle erosion",
    abstract = "Current understanding of physical and chemical processes involved in the erosion of submerged nozzles by highly-aluminized solid propellants is limited. The ability to predict the surface erosion rate of a given carbon-cloth phenolic (CCP) nozzle material is very important for the future design or modification of large solid rocket boosters for space launch applications. Although current erosion codes provide engineering accuracy for nozzle throat erosion rates, calculated rates for the forward surfaces of the submerged nozzle can vary significantly from observed values. The overall objective of this research study under the NASA Constellation University Institutes Project (NASA-CUIP) is to improve the understanding of nozzle erosion and related phenomena. In previous work, the design of a subscale solid rocket motor was performed based upon engineering analysis of the interior ballistic process and a series of CFD simulations of the flow field in both the region of the submerged nozzle and the entire subscale motor. This motor design allows for the use of real-time X-ray radiography with a high-resolution image intensifier system to obtain submerged nozzle erosion data. An update on the design and fabrication of this subscale solid rocket motor is presented in the present work. In addition to this, 3D simulation of the internal flow-field of the rocket motor was performed including the effects of liquid alumina droplets. The modeling of the nozzle surface erosion, coupled with the flow field structure, addresses scientific understanding and characterization of the influence of a liquid layer formed due to deposition of Al2O3/Al droplets on the surface of the converging section of the submerged nozzle. Calculations have been performed which compute the accretion rate of alumina onto the nozzle surface, with accretion rates on the order of 20 kg/m2-s. As a part of the overall study, we examine several physicochemical processes on the nozzle surface due to the presence of this molten liquid layer. Future test results from this newly designed rocket motor will be highly beneficial for model validation as well as attaining in-depth understanding of interactions between the liquid alumina and nozzle materials.",
    author = "Cortopassi, {Andrew C.} and Boyer, {J. Eric} and Kuo, {Kenneth K.}",
    year = "2009",
    language = "English (US)",
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    booktitle = "45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit",

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    Cortopassi, AC, Boyer, JE & Kuo, KK 2009, Update: A subscale solid rocket motor for characterization of submerged nozzle erosion. in 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Denver, CO, United States, 8/2/09.

    Update : A subscale solid rocket motor for characterization of submerged nozzle erosion. / Cortopassi, Andrew C.; Boyer, J. Eric; Kuo, Kenneth K.

    45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. 2009.

    Research output: Chapter in Book/Report/Conference proceedingConference contribution

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    N2 - Current understanding of physical and chemical processes involved in the erosion of submerged nozzles by highly-aluminized solid propellants is limited. The ability to predict the surface erosion rate of a given carbon-cloth phenolic (CCP) nozzle material is very important for the future design or modification of large solid rocket boosters for space launch applications. Although current erosion codes provide engineering accuracy for nozzle throat erosion rates, calculated rates for the forward surfaces of the submerged nozzle can vary significantly from observed values. The overall objective of this research study under the NASA Constellation University Institutes Project (NASA-CUIP) is to improve the understanding of nozzle erosion and related phenomena. In previous work, the design of a subscale solid rocket motor was performed based upon engineering analysis of the interior ballistic process and a series of CFD simulations of the flow field in both the region of the submerged nozzle and the entire subscale motor. This motor design allows for the use of real-time X-ray radiography with a high-resolution image intensifier system to obtain submerged nozzle erosion data. An update on the design and fabrication of this subscale solid rocket motor is presented in the present work. In addition to this, 3D simulation of the internal flow-field of the rocket motor was performed including the effects of liquid alumina droplets. The modeling of the nozzle surface erosion, coupled with the flow field structure, addresses scientific understanding and characterization of the influence of a liquid layer formed due to deposition of Al2O3/Al droplets on the surface of the converging section of the submerged nozzle. Calculations have been performed which compute the accretion rate of alumina onto the nozzle surface, with accretion rates on the order of 20 kg/m2-s. As a part of the overall study, we examine several physicochemical processes on the nozzle surface due to the presence of this molten liquid layer. Future test results from this newly designed rocket motor will be highly beneficial for model validation as well as attaining in-depth understanding of interactions between the liquid alumina and nozzle materials.

    AB - Current understanding of physical and chemical processes involved in the erosion of submerged nozzles by highly-aluminized solid propellants is limited. The ability to predict the surface erosion rate of a given carbon-cloth phenolic (CCP) nozzle material is very important for the future design or modification of large solid rocket boosters for space launch applications. Although current erosion codes provide engineering accuracy for nozzle throat erosion rates, calculated rates for the forward surfaces of the submerged nozzle can vary significantly from observed values. The overall objective of this research study under the NASA Constellation University Institutes Project (NASA-CUIP) is to improve the understanding of nozzle erosion and related phenomena. In previous work, the design of a subscale solid rocket motor was performed based upon engineering analysis of the interior ballistic process and a series of CFD simulations of the flow field in both the region of the submerged nozzle and the entire subscale motor. This motor design allows for the use of real-time X-ray radiography with a high-resolution image intensifier system to obtain submerged nozzle erosion data. An update on the design and fabrication of this subscale solid rocket motor is presented in the present work. In addition to this, 3D simulation of the internal flow-field of the rocket motor was performed including the effects of liquid alumina droplets. The modeling of the nozzle surface erosion, coupled with the flow field structure, addresses scientific understanding and characterization of the influence of a liquid layer formed due to deposition of Al2O3/Al droplets on the surface of the converging section of the submerged nozzle. Calculations have been performed which compute the accretion rate of alumina onto the nozzle surface, with accretion rates on the order of 20 kg/m2-s. As a part of the overall study, we examine several physicochemical processes on the nozzle surface due to the presence of this molten liquid layer. Future test results from this newly designed rocket motor will be highly beneficial for model validation as well as attaining in-depth understanding of interactions between the liquid alumina and nozzle materials.

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    Cortopassi AC, Boyer JE, Kuo KK. Update: A subscale solid rocket motor for characterization of submerged nozzle erosion. In 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. 2009