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Dissertations / Theses on the topic 'Aerospike Nozzle'

Author: Grafiati

Published: 4 June 2021

Last updated: 1 February 2022

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1

Case, William Scott. "AEROSPIKE THRUST VECTORING SLOT-TYPE COMPOUND NOZZLE." DigitalCommons@CalPoly, 2010. https://digitalcommons.calpoly.edu/theses/316.

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A study of thrust vectoring techniques of annular aerospike nozzles was conducted. Cold-flow blow-down testing along with solid modeling and rapid prototyping technology were used to investigate the effects of slot size, placement, geometry and orientation. The use of slot-type compound nozzles proved to be a feasible approach to thrust vectoring. Previous methods of thrust vectoring have proved to be difficult to implement in a cost effective manner or have had limited effectiveness or durability.

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2

Beebe, Stanley Ikuo. "HOLE-TYPE AEROSPIKE COMPOUND NOZZLE THRUST VECTORING." DigitalCommons@CalPoly, 2009. https://digitalcommons.calpoly.edu/theses/164.

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Compound aerospike nozzles were designed and tested as part of an ongoing experimental study to determine the feasibility of thrust vectoring an aerospike nozzle with the addition of a secondary port. Earlier phases of the study have indicated that a compound aerospike nozzle could provide sufficient thrust vectoring. The addition of a hole-type secondary port was found to provide effective thrust vectoring. Experiments were carried out to determine the effects of secondary port size, secondary port inlet geometry and compound aerospike nozzle chamber pressure. Results show good predictability

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3

Gould, Cedric Oldfield. "DESIGN OF AN AEROSPIKE NOZZLE FOR A HYBRID ROCKET." MSSTATE, 2008. http://sun.library.msstate.edu/ETD-db/theses/available/etd-04292008-102320/.

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This document describes the design of an axisymmetric aerospike nozzle to replace the conical converging-diverging nozzle of a commercially available hybrid rocket motor. The planar method of characteristics is used with isentropic flow assumptions to design the nozzle wall. Axisymmetric adjustments are made with quasi-one-dimensional flow approximations. Computational Fluid Dynamics (CFD) simulations verify these assumptions, and illustrate viscous effects within the flow. Nozzle truncations are also investigated. Development of a hybrid-rocket-specific data acquisition system is also detaile

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4

Imbaratto, David Michael. "The Interaction between Throttling and Thrust Vectoring of an Annular Aerospike Nozzle." DigitalCommons@CalPoly, 2009. https://digitalcommons.calpoly.edu/theses/159.

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Applied research and testing has been conducted at the Cal Poly San Luis Obispo High-pressure Blow-Down facility to study the affects of throttling in a thrust-vectored aerospike nozzle. This study supports the ongoing research at Cal Poly to effectively thrust vector a hybrid rocket motor. Such thrust vectoring is achieved by small secondary ports in the nozzle body that are perpendicular to the main nozzle. The testing conducted included characterizing and comparing the performance of a straight aerospike nozzle to that of a thrust-vectored aerospike nozzle. Throttling effects on the aerospi

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5

Zahn, Alexander R. "Characterization and Examination of Performance Parameters of a Back-pressurized RDC." University of Cincinnati / OhioLINK, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1554119639742205.

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6

Armstrong, Isaac W. "Development and Testing of Additively Manufactured Aerospike Nozzles for Small Satellite Propulsion." DigitalCommons@USU, 2019. https://digitalcommons.usu.edu/etd/7428.

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Automatic altitude compensation has been a holy grail of rocket propulsion for decades. Current state-of-the-art bell nozzles see large performance decreases at low altitudes, limiting rocket designs, shrinking payloads, and overall increasing costs. Aerospike nozzles are an old idea from the 1960’s that provide superior altitude-compensating performance and enhanced performance in vacuum, but have survivability issues that have stopped their application in satellite propulsion systems. A growing need for CubeSat propulsion systems provides the impetus to study aerospike nozzles in this applic

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7

Grieb, Daniel Joseph. "Design and Analysis of a Reusable N2O-Cooled Aerospike Nozzle for Labscale Hybrid Rocket Motor Testing." DigitalCommons@CalPoly, 2012. https://digitalcommons.calpoly.edu/theses/692.

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A reusable oxidizer-cooled annular aerospike nozzle was designed for testing on a labscale PMMA-N20[1] hybrid rocket motor at Cal Poly-SLO.[2] The detailed design was based on the results of previous research involving cold-flow testing of annular aerospike nozzles and hot-flow testing of oxidizer-cooled converging-diverging nozzles. In the design, nitrous oxide is routed to the aerospike through a tube that runs up the middle of the combustion chamber. The solid fuel is arranged in an annular configuration, with a solid cylinder of fuel in the center of the combustion chamber and a hollow cyl

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8

Pearl, Jason M. "Two-Dimensional Numerical Study of Micronozzle Geometry." ScholarWorks @ UVM, 2016. http://scholarworks.uvm.edu/graddis/579.

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Supersonic micronozzles operate in the unique viscosupersonic flow regime, characterized by large Mach numbers (M>1) and low Reynolds numbers (Re<1000). Past research has primarily focused on the design and analysis of converging-diverging de Laval nozzles; however, plug (i.e. centerbody) designs also have some promising characteristics that might make them amenable to microscale operation. In this study, the effects of plug geometry on plug micronozzle performance are examined for the Reynolds number range Re = 80-640 using 2D Navier-Stokes-based simulations. Nozzle plugs are shortened to red

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9

Brennen, Peter Alexander. "SIMULATION OF AN OXIDIZER-COOLED HYBRID ROCKET THROAT: METHODOLOGY VALIDATION FOR DESIGN OF A COOLED AEROSPIKE NOZZLE." DigitalCommons@CalPoly, 2009. https://digitalcommons.calpoly.edu/theses/166.

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A study was undertaken to create a finite element model of a cooled throat converging/diverging rocket nozzle to be used as a tool in designing a cooled aerospike nozzle. Using ABAQUS, a simplified 2D axisymmetric model was created featuring only the copper throat and stainless steel support ring, which were brazed together for the experimental test firings. This analysis was a sequentially coupled thermal/mechanical model. The steady state thermal data matched closely to experimental data. The subsequent mechanical model predicted a life of over 300 cycles using the Manson-Halford fatigue

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10

Papp, John Laszlo. "SIMULATION OF TURBULENT SUPERSONIC SEPARATED BASE FLOWS USING ENHANCED TURBULENCE MODELING TECHNIQUES WITH APPLICATION TO AN X-33 AEROSPIKE ROCKET NOZZLE SYSTEM." University of Cincinnati / OhioLINK, 2000. http://rave.ohiolink.edu/etdc/view?acc_num=ucin962118912.

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11

Bulut, Jane. "Design and CFD analysis of the demonstrator aerospike engine for a small satellite launcher application." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2020.

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Starting with a brief overview of thrust generation for launchers, this study focuses on the design process of the demonstrator aerospike engine, DEMOP-1, of the Pangea Aerospace's commercial grade engine and its flow field analysis. The primary goal of the study is to obtain the plug nozzle design delivers 30 kN thrust using cryogenic liquid oxygen (LOX) as the oxidizer and cryogenic liquid methane (LCH4) as the fuel, with the mixture ratio of 3.4. Design parameters considered as 30 bar of combustion chamber pressure (Po) and expansion ratio as 15 for an optimum expanded nozzle. On the basi

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12

Boccaletto, Luca. "Maîtrise du décollement de tuyère. Analyse du comportement d'une tuyère de type TOC et définition d'un nouveau concept : le BOCCAJET." Thesis, Aix-Marseille 1, 2011. http://www.theses.fr/2011AIX10012/document.

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Cette recherche s’articule en deux parties. L’objectif de la première partie est d’analyser par voie expérimentale et numérique la phénoménologie du décollement interne, dit décollement de jet (en regimes transitoire et établi) dans les tuyères supersoniques refroidies par film fluide. La deuxième partie porte sur la réinterprétation des concepts de tuyère existants pour aboutir à la proposition d’un nouveau dispositif de détente supersonique, qui offre une résistance accrue au décollement de jet. La première partie de cette thèse est basée sur l’analyse des résultats expérimentaux obtenus lor

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13

El, Mellouki Mohammed. "Numerical Study and Investigation of a Gurney Flap Supersonic Nozzle." Thesis, Mississippi State University, 2019. http://pqdtopen.proquest.com/#viewpdf?dispub=10979662.

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<p> Flow separation is a common fluid dynamics phenomenon that occurs within supersonic nozzles while operating at off-design pressures. Typically, off-design pressures result in a shock formation that leads to a non-uniformity of the exiting flow and creates flow separation and flow recirculation. So far, no effective solution has been presented to eliminate flow separation and increase the total performance of the nozzle. The purpose of this work is to investigate whether a Gurney flap may beneficially affect the exiting flow pattern. For a better understanding of the Gurney flap effect, thi

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14

Niimi, Tomohide, Hideo Mori, Kazuki Okabe, Yusuke Masai, and Mashio Taniguchi. "ANALYSES OF FLOW FIELD STRUCTURES AROUND LINEAR-TYPE AEROSPIKE NOZZLES USING LIF AND PSP." IEEE, 2003. http://hdl.handle.net/2237/7168.

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15

Agricola, Lucas. "Nozzle Guide Vane Sweeping Jet Impingement Cooling." The Ohio State University, 2018. http://rave.ohiolink.edu/etdc/view?acc_num=osu1525436077557298.

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16

Ceci, Alessandro. "Transonic Flow Features in a Nozzle Guide Vane Passage." Thesis, KTH, Farkost och flyg, 2017. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-213986.

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The entropy noise in modern engines is mainly originating from two types of mechanisms.First, chemical reactions in the combustion chamber lead to unsteady heat releasewhich is responsible of the direct combustion noise. Second, hot and cold blobsof air coming from the combustion chamber are advected and accelerated throughturbine stages, giving rise to the so-called entropy noise (or indirect combustionnoise). In the present work, numerical characterization of indirect combustion noiseof a Nozzle Guide Vane passage was assessed using three-dimensional Large EddySimulations. The study was cond

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17

Dolan, Brian. "Flame Interactions and Thermoacoustics in Multiple-Nozzle Combustors." University of Cincinnati / OhioLINK, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1479822588098224.

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18

Bonilla, Carlos Humberto. "The Effect of Film Cooling on Nozzle Guide Vane Ash Deposition." The Ohio State University, 2012. http://rave.ohiolink.edu/etdc/view?acc_num=osu1353961326.

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19

Mandour, Eldeeb Mohamed F. "Development and Assessment of Altitude Adjustable Convergent Divergent Nozzles Using Passive Flow Control." University of Cincinnati / OhioLINK, 2014. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1415283904.

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20

Holder, Justin. "Fluid Structure Interaction in Compressible Flows." University of Cincinnati / OhioLINK, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=ucin159584692691518.

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21

Kiani, Niloufar. "Nozzle Flow Study and Geometry Optimization of Shear Thinning Non-Newtonian Fluid, Fuel Tank Sealant." Thesis, California State University, Long Beach, 2018. http://pqdtopen.proquest.com/#viewpdf?dispub=10838460.

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<p> Applications of sealant and adhesive technologies in aerospace industries require appropriate and reliable sealing materials and tools to provide suitable sealing. Due to a growing use of integral fuel tanks, which utilize the aircraft structure for fuel containment, this study focuses on nozzle geometry optimization of aircraft fuel tank sealant in order to develop and facilitate sealant approval process and to ensure the implementation of suitable fuel tank sealing. </p><p> Computational Fluid Dynamics (CFD) analyses were performed to study the sealant flow characterization and behavi

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22

Baier, Florian. "Noise Radiation from a Supersonic Nozzle with Jet/Surface Interaction." University of Cincinnati / OhioLINK, 2021. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1617108352134538.

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23

Casaday, Brian Patrick. "Investigation of Particle Deposition in Internal Cooling Cavities of a Nozzle Guide Vane." The Ohio State University, 2013. http://rave.ohiolink.edu/etdc/view?acc_num=osu1376651156.

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24

Marshall, Joel H. "Thrust Augmented Nozzle for a Hybrid Rocket with a Helical Fuel Port." DigitalCommons@USU, 2018. https://digitalcommons.usu.edu/etd/6915.

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A thrust augmented nozzle for hybrid rocket systems is investigated. The design lever-ages 3-D additive manufacturing to embed a helical fuel port into the thrust chamber of a hybrid rocket burning gaseous oxygen and ABS plastic as propellants. The helical port significantly increases how quickly the fuel burns, resulting in a fuel-rich exhaust exiting the nozzle. When a secondary gaseous oxygen flow is injected into the nozzle downstream of the throat, all of the remaining unburned fuel in the plume spontaneously ignites. This secondary reaction produces additional high pressure gases that ar

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25

Perrino, Michael. "An Experimental Study into Pylon, Wing, and Flap Installation Effects on Jet Noise Generated by Commercial Aircraft." University of Cincinnati / OhioLINK, 2014. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1406819764.

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26

Maxted, Katsuo J. "Experimental Investigation on Acoustic Characteristics of Convergent Orifices in Bias Flow." University of Cincinnati / OhioLINK, 2015. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1439304400.

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27

Soliman, Salah M. "Micro-Particles and Gas Dynamics in an Axi-Symmetric Supersonic Nozzle." University of Cincinnati / OhioLINK, 2011. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1313772443.

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28

Webb, Joshua J. "The Effect of Particle Size and Film Cooling on Nozzle Guide Vane Deposition." The Ohio State University, 2011. http://rave.ohiolink.edu/etdc/view?acc_num=osu1313528110.

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29

MOHAMED, ASHRAF ELSAID. "An Experimental Investigation of Supersonic Rectangular Over-Expanded Nozzle of Single and Two-Phase Flows." University of Cincinnati / OhioLINK, 2008. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1204661977.

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30

Lakhamraju, Raghava Raju. "Characterization of the jet emanating from a self-exciting flexible membrane nozzle." University of Cincinnati / OhioLINK, 2012. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1337887322.

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31

Selvaraj, Sudharshan. "Use of CFD to Validate and Predict the Jet Noise from a High Aspect-ratio Nozzle at Off-design Conditions." University of Cincinnati / OhioLINK, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1595850094240426.

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32

Giri, Ritangshu. "Numerical Analysis of Non-Reacting Flow in a Multi-nozzle Swirl Stabilized Lean Direct Injection Combustor." University of Cincinnati / OhioLINK, 2015. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1447690568.

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33

Heiner, Mark C. "Development and Testing of a Hydrogen Peroxide Injected Thrust Augmenting Nozzle for a Hybrid Rocket." DigitalCommons@USU, 2019. https://digitalcommons.usu.edu/etd/7630.

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During a rocket launch, the point at which the most thrust is needed is at lift-off where the rocket is the heaviest since it is full of propellant. Unfortunately, this is also the point at which rocket engines perform the most poorly due to the relatively high atmospheric pressure at sea level. The Thrust Augmenting Nozzle (TAN) investigated in this paper provides a solution to this dilemma. By injecting extra propellant into the nozzle but downstream of the throat, the internal nozzle pressure is raised and the thrust is increased, and the nozzle efficiency, or specific impulse is potentiall

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34

Munday, David. "Flow and Acoustics of Jets from Practical Nozzles for High-Performance Military Aircraft." University of Cincinnati / OhioLINK, 2010. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1289842789.

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35

Raja, Sandeep. "The systematic development of Direct Write (DW) technology for the fabrication of printed antennas for the aerospace and defence industry." Thesis, Loughborough University, 2014. https://dspace.lboro.ac.uk/2134/14930.

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Low profile, conformal antennas have considerable advantages for Aerospace and Military platforms where conventional antenna system add weight and drag. Direct Write (DW) technology has been earmarked as a potential method for fabricating low profile antennas directly onto structural components. This thesis determines the key design rules and requirements for DW fabrication of planar antennas. From this, three key areas were investigated: the characterisation of DW ink materials for functionality and durability in harsh environments, localised processing of DW inks and the optimisation of DW c

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36

Nastic, Aleksandra. "Repair of Aluminum Alloy Aerospace Components and Cold Gas Dynamic Spray Flow Distribution Study." Thesis, Université d'Ottawa / University of Ottawa, 2015. http://hdl.handle.net/10393/32998.

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Aluminum alloys have been used for decades in aircraft as they offer a wide range of properties explicitly developed to provide a set of characteristics adapted to structural and non-structural components. However, aircraft components inevitably undergo degradation during service due to their extensive use and exposure to harsh environments. Typical repair methods are either not efficient for large scale repairs due to their low material growth rate, not suitable for field repair or involve the use of high process temperatures. The present research aims at evaluating the cold gas dynamic spray

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37

Mustafa, Mansoor. "Investigation into Offset Streams for Jet Noise Reduction." The Ohio State University, 2015. http://rave.ohiolink.edu/etdc/view?acc_num=osu1437477139.

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38

Clark, Kylen D. "A Numerical Comparison of Symmetric and Asymmetric Supersonic Wind Tunnels." University of Cincinnati / OhioLINK, 2015. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1447071393.

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39

MA, ZHANHUA. "INVESTIGATION ON THE INTERNAL FLOW CHARACTERISTICS OF PRESSURE-SWIRL ATOMIZERS." University of Cincinnati / OhioLINK, 2002. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1016634882.

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40

Stack, Cory M. "Turbulence Mechanisms in a Supersonic Rectangular Multistream Jet with an Aft-Deck." The Ohio State University, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=osu1560352886647369.

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41

Ramunno, Michael Angelo. "Control Optimization of Turboshaft Engines for a Turbo-electric Distributed Propulsion Aircraft." The Ohio State University, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=osu1587657623577243.

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42

Roy, Jean-Michel L. "Development of Cold Gas Dynamic Spray Nozzle and Comparison of Oxidation Performance of Bond Coats for Aerospace Thermal Barrier Coatings at Temperatures of 1000°C and 1100°C." Thesis, Université d'Ottawa / University of Ottawa, 2012. http://hdl.handle.net/10393/20681.

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The purpose of this research work was to develop a nozzle capable of depositing dense CoNiCrAlY coatings via cold gas dynamic spray (CGDS) as well as compare the oxidation performance of bond coats manufactured by CGDS, high-velocity oxy-fuel (HVOF) and air plasma spray (APS) at temperatures of 1000°C and 1100°C. The work was divided in two sections, the design and manufacturing of a CGDS nozzle with an optimal profile for the deposition of CoNiCrAlY powders and the comparison of the oxidation performance of CoNiCrAlY bond coats. Throughout this work, it was shown that the quality of coatings

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43

Chen, Ru-Ching. "Development of a Supersonic Nozzle and Test Section for use with a Magnetic Suspension System for Re-Entry Aeroshell Models." Case Western Reserve University School of Graduate Studies / OhioLINK, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=case1544179612537658.

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44

ALLGOOD, DANIEL CLAY. "AN EXPERIMENTAL AND COMPUTATIONAL STUDY OF PULSE DETONATION ENGINES." University of Cincinnati / OhioLINK, 2004. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1095259010.

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45

Bhide, Kalyani R. "Shock Boundary Layer Interactions - A Multiphysics Approach." University of Cincinnati / OhioLINK, 2018. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1543994392025663.

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46

Sasson, Jonathan. "Small Scale Mass Flow Plug Calibration." Case Western Reserve University School of Graduate Studies / OhioLINK, 2015. http://rave.ohiolink.edu/etdc/view?acc_num=case1417540797.

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47

Hossain, Mohammad Arif. "Sweeping Jet Film Cooling." The Ohio State University, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=osu1586462423029754.

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48

Murad, Mark Richard. "Radiation View Factors Between A Disk And The Interior Of A Class Of Axisymmetric Bodies Including Converging Diverging Rocket Nozzles." Cleveland State University / OhioLINK, 2008. http://rave.ohiolink.edu/etdc/view?acc_num=csu1210962269.

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49

Asar, Munevver Elif. "Investigating Turbine Vane Trailing Edge Pin Fin Cooling in Subsonic and Transonic Cascades." The Ohio State University, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=osu155551385206548.

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50

Jiang, Hua. "Effect of Changes in Flow Geometry, Rotation and High Heat Flux on Fluid Dynamics, Heat Transfer and Oxidation/Deposition of Jet Fuels." University of Dayton / OhioLINK, 2011. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1300553102.

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