Louis M. Edelman, M. Gamba, Robin L. Hunt, A. Auslender
A highly confined shock train is investigated in a direct-connect isolator facility with a Mach 2 inflow and a constant-area low-aspect-ratio rectangular test section. High-speed schlieren imaging, wall static pressure measurements, surface oil-flow visualization, and particle image velocimetry from this isolator are synthesized into a three-dimensional schematic of the shock train structure. Against this, the prevailing pseudoshock models in the literature are assessed to evaluate the validity of their underlying assumptions. None of the prevailing pseudoshock models are found to simultaneously model the pressure and Mach number profiles, indicating a gap in the model formation and underlying assumptions when applied to the experimental isolator of interest. The presence of distortion in the isolator flowfield, such as a wall-bounded vortex, is found to skew the structure of the shock train, altering the strength and distribution of the compressive pressure gradient. It is further observed that the separated flow morphology surrounding the shock train is not monolithic, as is typically assumed, adjusting the balance of compressive forces within the shock cells. These findings lead to the conclusion that existing flux-conserved modeling approaches require modification to be effective in distorted and highly confined cases, including closure models that capture the three-dimensional distorted structure of the approach flow and its evolution along the shock train.
{"title":"Assessment of Pseudoshock Models Against Experiment in a Low-Aspect-Ratio Isolator","authors":"Louis M. Edelman, M. Gamba, Robin L. Hunt, A. Auslender","doi":"10.2514/1.b38913","DOIUrl":"https://doi.org/10.2514/1.b38913","url":null,"abstract":"A highly confined shock train is investigated in a direct-connect isolator facility with a Mach 2 inflow and a constant-area low-aspect-ratio rectangular test section. High-speed schlieren imaging, wall static pressure measurements, surface oil-flow visualization, and particle image velocimetry from this isolator are synthesized into a three-dimensional schematic of the shock train structure. Against this, the prevailing pseudoshock models in the literature are assessed to evaluate the validity of their underlying assumptions. None of the prevailing pseudoshock models are found to simultaneously model the pressure and Mach number profiles, indicating a gap in the model formation and underlying assumptions when applied to the experimental isolator of interest. The presence of distortion in the isolator flowfield, such as a wall-bounded vortex, is found to skew the structure of the shock train, altering the strength and distribution of the compressive pressure gradient. It is further observed that the separated flow morphology surrounding the shock train is not monolithic, as is typically assumed, adjusting the balance of compressive forces within the shock cells. These findings lead to the conclusion that existing flux-conserved modeling approaches require modification to be effective in distorted and highly confined cases, including closure models that capture the three-dimensional distorted structure of the approach flow and its evolution along the shock train.","PeriodicalId":16903,"journal":{"name":"Journal of Propulsion and Power","volume":null,"pages":null},"PeriodicalIF":1.9,"publicationDate":"2023-06-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"44522288","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
N. Yamamoto, Naoya Kuwabara, D. Kuwahara, Shinatora Cho, Y. Kosuga, Guilhem Dif Pradalier
To understand anomalous electron transport in a Hall thruster, plasma turbulence inside the acceleration channel was observed using a 76 GHz microwave interferometer. The dependence of the amplitude of the 100–500 kHz turbulence on magnetic flux density, and the relationships between the turbulence and other plasma instabilities and between the turbulence and the discharge current were investigated through spectral density and bicoherence analysis. The amplitude of electron number density fluctuations of the turbulence, integrating the spectral density from 100 to 500 kHz, is [Formula: see text], or almost 10% of the time-averaged electron number density. The amplitude of the turbulence decreases with increase in weak magnetic field strength (coil current less than 0.6 A) and then increases with increase in magnetic field strength. The amplitude of the turbulence has a positive relation to the discharge current, leads to anomalous electron transport inside the acceleration channel, and is coupled with ionization instability. In addition, low-frequency perturbations of several hundred hertz were observed, with a positive relation to the turbulence and coupled with both ionization instability and turbulence.
{"title":"Observation of Plasma Turbulence in a Hall Thruster Using Microwave Interferometry","authors":"N. Yamamoto, Naoya Kuwabara, D. Kuwahara, Shinatora Cho, Y. Kosuga, Guilhem Dif Pradalier","doi":"10.2514/1.b38711","DOIUrl":"https://doi.org/10.2514/1.b38711","url":null,"abstract":"To understand anomalous electron transport in a Hall thruster, plasma turbulence inside the acceleration channel was observed using a 76 GHz microwave interferometer. The dependence of the amplitude of the 100–500 kHz turbulence on magnetic flux density, and the relationships between the turbulence and other plasma instabilities and between the turbulence and the discharge current were investigated through spectral density and bicoherence analysis. The amplitude of electron number density fluctuations of the turbulence, integrating the spectral density from 100 to 500 kHz, is [Formula: see text], or almost 10% of the time-averaged electron number density. The amplitude of the turbulence decreases with increase in weak magnetic field strength (coil current less than 0.6 A) and then increases with increase in magnetic field strength. The amplitude of the turbulence has a positive relation to the discharge current, leads to anomalous electron transport inside the acceleration channel, and is coupled with ionization instability. In addition, low-frequency perturbations of several hundred hertz were observed, with a positive relation to the turbulence and coupled with both ionization instability and turbulence.","PeriodicalId":16903,"journal":{"name":"Journal of Propulsion and Power","volume":null,"pages":null},"PeriodicalIF":1.9,"publicationDate":"2023-06-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"47766074","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
In the present work, we discuss the employment of a computational fluid dynamics approach to evaluate the specific impulse of solid rocket motors. Particular care is focused on two-phase flow and divergence losses, which represent the most important contributions to the overall nozzle performance loss. A comprehensive parametric study is performed on the Zefiro 9A nozzle with the aim to evaluate the detrimental influence of relevant key features, such as alumina particle dimension, polydispersion, crystallization, and motor operating conditions. The capability of the present model to represent, with good accuracy, the overall performance of solid rocket motors is demonstrated by comparing the experimental specific impulse of several motors with numerical predictions.
{"title":"Multiphase Effects on Solid Rocket Nozzle Performance","authors":"M. Grossi, Alessio Sereno, D. Bianchi, B. Favini","doi":"10.2514/1.b39096","DOIUrl":"https://doi.org/10.2514/1.b39096","url":null,"abstract":"In the present work, we discuss the employment of a computational fluid dynamics approach to evaluate the specific impulse of solid rocket motors. Particular care is focused on two-phase flow and divergence losses, which represent the most important contributions to the overall nozzle performance loss. A comprehensive parametric study is performed on the Zefiro 9A nozzle with the aim to evaluate the detrimental influence of relevant key features, such as alumina particle dimension, polydispersion, crystallization, and motor operating conditions. The capability of the present model to represent, with good accuracy, the overall performance of solid rocket motors is demonstrated by comparing the experimental specific impulse of several motors with numerical predictions.","PeriodicalId":16903,"journal":{"name":"Journal of Propulsion and Power","volume":null,"pages":null},"PeriodicalIF":1.9,"publicationDate":"2023-05-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"47421267","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Liquid fuel is the choice for volume-limited propulsion systems, including detonation-based propulsion. A liquid fuel with high vapor pressure has the advantage of more fuel vapor in the mixture, which supports the transition from deflagration to detonation. This paper reports on an experimental study of deflagration-to-detonation transition (DDT) in a pulse detonation engine with heterogenous mixtures of oxygen and ethanol or acetone. Single-cycle tests were taken for different fuels, equivalence ratios, and DDT enhancement methods. The size distribution of fuel droplets was characterized at the atomizer and engine exit. The effect of the fuel evaporation was dominant for the acetone spray only. Comparing the measured detonation velocities of the two mixtures, a lower velocity deficit relative to the theoretical Chapman–Jouguet detonation velocity was measured for the acetone–oxygen mixtures, and this behavior is related to the higher amount of fuel vapor that existed in the mixtures. Moreover, a shorter transition to detonation was observed in the acetone–oxygen mixture. The addition of a Shchelkin spiral reduced the DDT distance; however, the Chapman–Jouguet condition could be reached only downstream of the obstacle. The measured detonation cell size of the heterogeneous acetone–oxygen mixture was smaller than that of the ethanol–oxygen mixture, indicating that it is more detonable.
{"title":"Deflagration to Detonation Transition in Heterogeneous Mixtures Containing Ethanol/Acetone and Oxygen","authors":"H. Kadosh, D. Michaels","doi":"10.2514/1.b39154","DOIUrl":"https://doi.org/10.2514/1.b39154","url":null,"abstract":"Liquid fuel is the choice for volume-limited propulsion systems, including detonation-based propulsion. A liquid fuel with high vapor pressure has the advantage of more fuel vapor in the mixture, which supports the transition from deflagration to detonation. This paper reports on an experimental study of deflagration-to-detonation transition (DDT) in a pulse detonation engine with heterogenous mixtures of oxygen and ethanol or acetone. Single-cycle tests were taken for different fuels, equivalence ratios, and DDT enhancement methods. The size distribution of fuel droplets was characterized at the atomizer and engine exit. The effect of the fuel evaporation was dominant for the acetone spray only. Comparing the measured detonation velocities of the two mixtures, a lower velocity deficit relative to the theoretical Chapman–Jouguet detonation velocity was measured for the acetone–oxygen mixtures, and this behavior is related to the higher amount of fuel vapor that existed in the mixtures. Moreover, a shorter transition to detonation was observed in the acetone–oxygen mixture. The addition of a Shchelkin spiral reduced the DDT distance; however, the Chapman–Jouguet condition could be reached only downstream of the obstacle. The measured detonation cell size of the heterogeneous acetone–oxygen mixture was smaller than that of the ethanol–oxygen mixture, indicating that it is more detonable.","PeriodicalId":16903,"journal":{"name":"Journal of Propulsion and Power","volume":null,"pages":null},"PeriodicalIF":1.9,"publicationDate":"2023-05-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"44185231","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
{"title":"Experimental Characterization of a Hollow Cathode with Iridium–Cerium Alloy","authors":"Hiroki Watanabe, Shinatora Cho, Yoshiki Matsunaga, Yasushi Ohkawa, Yu Tao, Fumiaki Kudo, K. Koga, Satoshi Yabu","doi":"10.2514/1.b38511","DOIUrl":"https://doi.org/10.2514/1.b38511","url":null,"abstract":"","PeriodicalId":16903,"journal":{"name":"Journal of Propulsion and Power","volume":null,"pages":null},"PeriodicalIF":1.9,"publicationDate":"2023-05-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"41510330","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Yunping Zhang, Lee Organski, A. Shashurin, K. Ostrikov
A coaxial low-energy surface flashover (LESF) ignitor for CubeSat electric propulsion systems was developed and tested. The ignitor features a coaxial geometry with copper electrodes directly bonded to the inner and outer surfaces of the alumina ceramic tubular insulator. The ignitor proved to be operational throughout (and after) an extended duration test of 10 million pulses. Characterization of a single LESF event via intensified charge-coupled device fast photography showed that the initial plasma was generated along the insulator surface, while the later plasma production was governed by the column attached to the copper electrodes. The plasma plume propagated primarily perpendicular to the insulator surface at around [Formula: see text]. Further investigation on the erosion of ceramic insulator and copper electrodes via energy-dispersive x-ray spectroscopy analysis of a witness plate exposed to LESF and scanning electron microscopy observation of the electrodes revealed that the ceramic erosion ([Formula: see text] molecules per pulse) was predominant over electrodes erosion ([Formula: see text] atoms per pulse or [Formula: see text]).
{"title":"Long-Duration Test of Coaxial Low-Energy Surface Flashover Ignitor","authors":"Yunping Zhang, Lee Organski, A. Shashurin, K. Ostrikov","doi":"10.2514/1.b39071","DOIUrl":"https://doi.org/10.2514/1.b39071","url":null,"abstract":"A coaxial low-energy surface flashover (LESF) ignitor for CubeSat electric propulsion systems was developed and tested. The ignitor features a coaxial geometry with copper electrodes directly bonded to the inner and outer surfaces of the alumina ceramic tubular insulator. The ignitor proved to be operational throughout (and after) an extended duration test of 10 million pulses. Characterization of a single LESF event via intensified charge-coupled device fast photography showed that the initial plasma was generated along the insulator surface, while the later plasma production was governed by the column attached to the copper electrodes. The plasma plume propagated primarily perpendicular to the insulator surface at around [Formula: see text]. Further investigation on the erosion of ceramic insulator and copper electrodes via energy-dispersive x-ray spectroscopy analysis of a witness plate exposed to LESF and scanning electron microscopy observation of the electrodes revealed that the ceramic erosion ([Formula: see text] molecules per pulse) was predominant over electrodes erosion ([Formula: see text] atoms per pulse or [Formula: see text]).","PeriodicalId":16903,"journal":{"name":"Journal of Propulsion and Power","volume":null,"pages":null},"PeriodicalIF":1.9,"publicationDate":"2023-05-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"46529812","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Dominic Gallegos, Henry Pace, Charles Arnold, L. Massa, Greg Young
Introducing cavity flameholders into a solid-fuel ramjet fuel grain demonstrated increased fuel loading with sustained combustion in previously unfavorable geometries. Volumetric fuel loading improvements of up to 26% were demonstrated to sustain combustion. Regression patterns of cavity fuel grains are presented and show that the effect of implementing a cavity flameholder is to change the location of maximum regression and the reattachment point. The addition of a cavity flameholder does not appear to have a significant effect on combustion efficiency. However, it is noteworthy that longer cavities increased the chamber pressure above what was observed for a center-perforated fuel grains as a result of the increased mass addition and higher equivalence ratio associated with the higher regression rate. Large-eddy simulation computations were performed using a fourth-order discontinuous Galerkin finite element solver with a novel flamelet and progress variable formulation. The predictions agree well with the experiments and point to the increased heat transfer for longer cavities as the main flameholder mechanism. The larger heat feedback is supported by the formation of a stronger recirculation region, which leads to increased coherent fluctuations due to the transition between local and global instabilities.
{"title":"Regression and Flame Structure in Cavity Flameholding Solid-Fuel Ramjet Fuel Grains","authors":"Dominic Gallegos, Henry Pace, Charles Arnold, L. Massa, Greg Young","doi":"10.2514/1.b39139","DOIUrl":"https://doi.org/10.2514/1.b39139","url":null,"abstract":"Introducing cavity flameholders into a solid-fuel ramjet fuel grain demonstrated increased fuel loading with sustained combustion in previously unfavorable geometries. Volumetric fuel loading improvements of up to 26% were demonstrated to sustain combustion. Regression patterns of cavity fuel grains are presented and show that the effect of implementing a cavity flameholder is to change the location of maximum regression and the reattachment point. The addition of a cavity flameholder does not appear to have a significant effect on combustion efficiency. However, it is noteworthy that longer cavities increased the chamber pressure above what was observed for a center-perforated fuel grains as a result of the increased mass addition and higher equivalence ratio associated with the higher regression rate. Large-eddy simulation computations were performed using a fourth-order discontinuous Galerkin finite element solver with a novel flamelet and progress variable formulation. The predictions agree well with the experiments and point to the increased heat transfer for longer cavities as the main flameholder mechanism. The larger heat feedback is supported by the formation of a stronger recirculation region, which leads to increased coherent fluctuations due to the transition between local and global instabilities.","PeriodicalId":16903,"journal":{"name":"Journal of Propulsion and Power","volume":null,"pages":null},"PeriodicalIF":1.9,"publicationDate":"2023-05-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"41865905","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
This paper presents a method for evaluating the risk of autoignition for the canonical problem of an enclosed hydrogen jet in crossflow (JICF), which is highly relevant to the design of mixing ducts. The proposed method is based on the separation of the underlying mixing pattern from the evolution of the chemical reactions, whereas the effect of mixing is maintained on the latter with the purpose of creating a reliable yet computationally efficient design tool for hydrogen gas turbines. Two variants of the incompletely stirred reactor network (ISRN) approach are proposed that provide the evolution of preignition radicals and autoignition kernel location, leveraging a nonreacting computational fluid dynamics solution or an analytical mixing pattern. The ISRN governing equations include all the salient features of hydrogen transport and lead to a conservative estimate of autoignition risk. Application to a few model problems with varied operating conditions suggests that radical buildup in the JICF can lead to autoignition in the vicinity of a most reactive mixture fraction, which is consistent with other laminar or turbulent hydrogen flows. However, the radical formation and autoignition kernel location strongly depend on the prediction of the underlying mixing field and the amount of differential diffusion within the JICF, which here primarily favors lower values of the composite mixture fraction and the transport of hydrogen and radicals away from the jet trajectory.
{"title":"Low-Order Autoignition Modeling for Hydrogen Transverse Jets","authors":"S. Gkantonas, E. Mastorakos","doi":"10.2514/1.b39142","DOIUrl":"https://doi.org/10.2514/1.b39142","url":null,"abstract":"This paper presents a method for evaluating the risk of autoignition for the canonical problem of an enclosed hydrogen jet in crossflow (JICF), which is highly relevant to the design of mixing ducts. The proposed method is based on the separation of the underlying mixing pattern from the evolution of the chemical reactions, whereas the effect of mixing is maintained on the latter with the purpose of creating a reliable yet computationally efficient design tool for hydrogen gas turbines. Two variants of the incompletely stirred reactor network (ISRN) approach are proposed that provide the evolution of preignition radicals and autoignition kernel location, leveraging a nonreacting computational fluid dynamics solution or an analytical mixing pattern. The ISRN governing equations include all the salient features of hydrogen transport and lead to a conservative estimate of autoignition risk. Application to a few model problems with varied operating conditions suggests that radical buildup in the JICF can lead to autoignition in the vicinity of a most reactive mixture fraction, which is consistent with other laminar or turbulent hydrogen flows. However, the radical formation and autoignition kernel location strongly depend on the prediction of the underlying mixing field and the amount of differential diffusion within the JICF, which here primarily favors lower values of the composite mixture fraction and the transport of hydrogen and radicals away from the jet trajectory.","PeriodicalId":16903,"journal":{"name":"Journal of Propulsion and Power","volume":null,"pages":null},"PeriodicalIF":1.9,"publicationDate":"2023-05-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"45467165","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Mark E. Noftz, Andrew J. Shuck, Joseph S. Jewell, Jonathan Poggie, Andrew N. Bustard, Thomas J. Juliano, Nicholas J. Bisek
The design of an inward-turning high-speed three-dimensional streamline-traced intake is presented from osculating axisymmetric theory. To satisfy the osculating intake design criteria, a stitched Busemann diffuser and internal conical flow-A solution are used as the basic isentropic compressive streamline. This new contour provides efficient compression, high flow uniformity, and straight leading-edge shocks of equal strength. Additionally, a novel method for constructing the inlet cowl is presented. The combined process leads to a new method of high-speed intake design. A generic shape-transitioned intake is constructed and named the Indiana inlet for the Indiana universities that contributed to the project. Computational fluid dynamic results are assessed to validate the design method for the two-dimensional parent flowfields and the full three-dimensional design.
{"title":"Design of an Internal Osculating Waverider Intake","authors":"Mark E. Noftz, Andrew J. Shuck, Joseph S. Jewell, Jonathan Poggie, Andrew N. Bustard, Thomas J. Juliano, Nicholas J. Bisek","doi":"10.2514/1.b38916","DOIUrl":"https://doi.org/10.2514/1.b38916","url":null,"abstract":"The design of an inward-turning high-speed three-dimensional streamline-traced intake is presented from osculating axisymmetric theory. To satisfy the osculating intake design criteria, a stitched Busemann diffuser and internal conical flow-A solution are used as the basic isentropic compressive streamline. This new contour provides efficient compression, high flow uniformity, and straight leading-edge shocks of equal strength. Additionally, a novel method for constructing the inlet cowl is presented. The combined process leads to a new method of high-speed intake design. A generic shape-transitioned intake is constructed and named the Indiana inlet for the Indiana universities that contributed to the project. Computational fluid dynamic results are assessed to validate the design method for the two-dimensional parent flowfields and the full three-dimensional design.","PeriodicalId":16903,"journal":{"name":"Journal of Propulsion and Power","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-05-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135399846","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Filip Sazeček, Ondřej Vodochodský, R. Matyáš, Petr Stojan, J. Zigmund, J. Pachman
{"title":"Bicyclo-HMX as an Energetic Additive for Composite Propellants","authors":"Filip Sazeček, Ondřej Vodochodský, R. Matyáš, Petr Stojan, J. Zigmund, J. Pachman","doi":"10.2514/1.b38977","DOIUrl":"https://doi.org/10.2514/1.b38977","url":null,"abstract":"","PeriodicalId":16903,"journal":{"name":"Journal of Propulsion and Power","volume":null,"pages":null},"PeriodicalIF":1.9,"publicationDate":"2023-04-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"42038419","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
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