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Journal articles on the topic 'Hydrogen peroxide rockets'

Author: Grafiati

Published: 4 June 2021

Last updated: 11 February 2022

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1

Okninski, Adam, Pawel Surmacz, Bartosz Bartkowiak, Tobiasz Mayer, Kamil Sobczak, Michal Pakosz, Damian Kaniewski, Jan Matyszewski, Grzegorz Rarata, and Piotr Wolanski. "Development of Green Storable Hybrid Rocket Propulsion Technology Using 98% Hydrogen Peroxide as Oxidizer." Aerospace 8, no. 9 (August 24, 2021): 234. http://dx.doi.org/10.3390/aerospace8090234.

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This paper presents the development of indigenous hybrid rocket technology, using 98% hydrogen peroxide as an oxidizer. Consecutive steps are presented, which started with interest in hydrogen peroxide and the development of technology to obtain High Test Peroxide, finally allowing concentrations of up to 99.99% to be obtained in-house. Hydrogen peroxide of 98% concentration (mass-wise) was selected as the workhorse for further space propulsion and space transportation developments. Over the course nearly 10 years of the technology’s evolution, the Lukasiewicz Research Network—Institute of Aviation completed hundreds of subscale hybrid rocket motor and component tests. In 2017, the Institute presented the first vehicle in the world to have demonstrated in-flight utilization for 98% hydrogen peroxide. This was achieved by the ILR-33 AMBER suborbital rocket, which utilizes a hybrid rocket propulsion as the main stage. Since then, three successful consecutive flights of the vehicle have been performed, and flights to the Von Karman Line are planned. The hybrid rocket technology developments are described. Advances in hybrid fuel technology are shown, including the testing of fuel grains. Theoretical studies and sizing of hybrid propulsion systems for spacecraft, sounding rockets and small launch vehicles have been performed, and planned further developments are discussed.

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2

Pasini, A., L. Torre, L. Romeo, A. Cervone, and L. d’Agostino. "Performance Characterization of Pellet Catalytic Beds for Hydrogen Peroxide Monopropellant Rockets." Journal of Propulsion and Power 27, no. 2 (March 2011): 428–36. http://dx.doi.org/10.2514/1.b34000.

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3

Bonifacio, S., G. Festa, and A. Russo Sorge. "Novel Structured Catalysts for Hydrogen Peroxide Decomposition in Monopropellant and Hybrid Rockets." Journal of Propulsion and Power 29, no. 5 (September 2013): 1130–37. http://dx.doi.org/10.2514/1.b34864.

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4

Lee, Eunkwang, Hongjae Kang, and Sejin Kwon. "Demonstration of Thrust Vector Control by Hydrogen Peroxide Injection in Hybrid Rockets." Journal of Propulsion and Power 35, no. 1 (January 2019): 109–14. http://dx.doi.org/10.2514/1.b37074.

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5

Farbar, E., J. Louwers, and T. Kaya. "Investigation of Metallized and Nonmetallized Hydroxyl Terminated Polybutadiene/Hydrogen Peroxide Hybrid Rockets." Journal of Propulsion and Power 23, no. 2 (March 2007): 476–86. http://dx.doi.org/10.2514/1.22091.

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6

Yun, Yongtae, Jeongmoo Huh, and Sejin Kwon. "Port diameter design of multiport solid fuel in hydrogen peroxide hybrid rockets." Aerospace Science and Technology 110 (March 2021): 106485. http://dx.doi.org/10.1016/j.ast.2020.106485.

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7

Ahn, Byeonguk, Jeongmoo Huh, Vikas Khandu Bhosale, and Sejin Kwon. "Three-Dimensionally Printed Polylactic Acid as Solid Fuel for Hydrogen Peroxide Hybrid Rockets." Journal of Propulsion and Power 37, no. 1 (January 2021): 171–75. http://dx.doi.org/10.2514/1.b37957.

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8

John, Jerin, Purushothaman Nandagopalan, Seung Wook Baek, and Sung June Cho. "Hypergolic ignition delay studies of solidified ethanol fuel with hydrogen peroxide for hybrid rockets." Combustion and Flame 212 (February 2020): 205–15. http://dx.doi.org/10.1016/j.combustflame.2019.10.029.

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9

Zhang, Yue, and Xuan J. Wang. "The Preparation of Graphite Oxide Controlled by Optimum Oxidation Potential with any Rejected Nitro-Oxidizer." Nano 14, no. 02 (February 2019): 1950018. http://dx.doi.org/10.1142/s1793292019500188.

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Nitro-oxidizers (nitric acid-27S, nitrogen tetroxide and mixed nitrogen oxide) are common liquid oxidants widely used in liquid rockets and missile weapons. How to deal with large quantities of scrapped nitro-oxidizers is a complex, costly and dangerous project. We pretreated it with hydrogen peroxide (H2O[Formula: see text] and converted the active oxidant component of nitro-oxidizers into nitric acid, which can be used as oxidant source to prepare graphite oxide from natural graphite. The comprehensive oxidation ability of the reaction system can be effectively controlled by adding different volumes of H2O2, and the oxidation ability can be expressed by the redox potential of the system. Combined with FT-IR, Raman and XRD characterization analysis, the optimal redox potential interval, [1700, 1800][Formula: see text]mV, has been determined for the synthesis of graphite oxide. With the help of data interpolation and function nonlinear fitting and the initial potential of rejected nitro-oxidants obtained, the composition ratio of nitric acid and nitrogen tetroxide (N2O[Formula: see text] has been preliminarily determined with the optimum amount of H2O2. Furthermore, the optimum oxidizing atmosphere for the synthesis of graphite oxide can be formed in spite of a wide range of concentrations of oxidant components, and the resulting graphite oxide has been proven to be a qualified and effective product.

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10

Tsujikado, Nobuo, and Atsushi Ishihara. "90% HYDROGEN PEROXIDE/POLYETHYLENE HYBRID ROCKET." International Journal of Energetic Materials and Chemical Propulsion 7, no. 4 (2008): 263–80. http://dx.doi.org/10.1615/intjenergeticmaterialschemprop.v7.i4.10.

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11

Al – Daraji, Hazim J. "Effect of dietary supplementation with rocket salad (Eruca sativa) seeds powder on certain seminal plasma traits of Hy – line laying breeder roosters subjected to oxidative stress induced by hydrogen peroxide." Iraqi Journal of Veterinary Medicine 36, no. 0A (March 4, 2012): 62–69. http://dx.doi.org/10.30539/iraqijvm.v36i0a.356.

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This study was conducted to evaluate the effect of adding different levels of rocket salad seeds powder to the diet on seminal plasma traits of roosters subjected to oxidative stress induced by hydrogen peroxide. A total of 60 Hy – line laying breeder roosters 57 weeks old were used in this study. Roosters were randomly distributed into 5 treatments with 3 replicates each. Each replicate constituted of 4 roosters (12 roosters for each treatment). Experimental treatments were as following: T1: Males fed control diet and normal water, T2: Males fed diet supplemented with 3 gm rocket salad powder / kg of diet + 0.25 ml hydrogen peroxide (0.5%) / litter of water, T3: Males fed diet supplemented with 3 gm rocket salad powder / kg of diet + 0.5 ml hydrogen peroxide (0.5%) / litter of water, T4: Males fed diet supplemented with 3 gm rocket salad powder / kg of diet + 1 ml hydrogen peroxide (0.5%) / litter of water, and T5: Males fed control diet and drink tap water supplemented with 1 ml hydrogen peroxide (0.5%) / litter of water. Males were treated with hydrogen peroxide (6%) and rocket salad for 12 weeks starting from 59 week of male ages. Results revealed that treated the roosters with hydrogen peroxide without adding rocket salad powder to the diet of these roosters (T5) resulted in highly significant (p< 0.01) decrease as regards concentrations of phospholipids, cholesterol, glutathione, the activity of superoxide desmutase and catalase, and total antioxidant activity in seminal plasma and highly significant (p< 0.01) increase concerning concentrations of tyrosine and malondialdehyde as compared with control group (T1) and rocket salad powder treatments (T2, T3, T4) after 12 weeks of experiment. However, supplementing diet of roosters with rocket salad powder (T2, T3, T4) resulted in highly significant (p< 0.01) increase with relation to concentrations of phospholipids, cholesterol, glutathione, the activity of superoxide desmutase and catalase, and total antioxidant activity in seminal plasma and highly significant (p< 0.01) decrease respecting concentrations of tyrosine and malondialdehyde as compared with (T5) In conclusion adding rocket salad powder to the diet of roosters had important role in limiting the negative effect of oxidative stress induced by hydrogen peroxide on seminal plasma quality of roosters. Therefore, dietary supplementation with rocket salad powder could be used as one of important tools for improving semen quality of roosters.

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12

PELIN, George, Cornel STOICA, Cristina Elisabeta PELIN, and Raluca BALASA. "High concentration hydrogen peroxide for rocket fuel applications." INCAS BULLETIN 12, no. 3 (September 1, 2020): 151–57. http://dx.doi.org/10.13111/2066-8201.2020.12.3.12.

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This paper presents the experimental study of the distillation of hydrogen peroxide to increase the concentration of the solution, in order to use it as rocket fuel in space applications. The process of obtaining the desired concentration required for the operation of the wind tunnel model rocket engine was obtained using the vacuum distillation method. The process consists in removing a calculated value of the water content from the hydrogen peroxide solution with a concentration of 35%, thus increasing its concentration up to the value of 90%. The key factors that contribute in obtaining the desired concentration were evaluated and experimental results were compared with the calculated values.

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13

LEE, Yang-Suk, and Jun Hwan JANG. "The design and performance on 200N-class bipropellant rocket engine using decomposed H2O2 and Kerosene." INCAS BULLETIN 11, no. 3 (September 9, 2019): 99–110. http://dx.doi.org/10.13111/2066-8201.2019.11.3.9.

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Mono-propellant thrusters are widely utilized in satellites and space launchers. In many cases, they are using hydrazine as a propellant. However, hydrazine has high toxicity and high risks in using for launch campaign. Recently, low-toxic (green) propellant is being highlighted as a replacement for hydrazine. In this paper, 200N bi-propellant engine using hydrogen peroxide/kerosene was designed/manufactured, and the spray or atomization characteristic and inflation pressure were determined by cold flow test, and combustion and pulse tests in a single cycle same as previous methods were conducted. As uniformly supplying hydrogen peroxide through plate-type orifice to a catalyst bed, the hot gas was created as a reaction with hydrogen and catalyst. And then, it was confirmed that the ignition is possible on the wide range of O/F ratio without additional ignition source. The liquid rocket engine with bi-propellant of hydrogen peroxide/kerosene and design/test methods which developed in this study are expected to be utilized as an essential database for designing of the ignitor/injector of bi-propellant liquid rocket engine using hydrogen peroxide/kerosene with high-thrust/performance in near future.

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14

Guseinov, Sh L., S. G. Fedorov, V. A. Kosykh, and P. A. Storozhenko. "Hydrogen Peroxide Decomposition Catalysts Used in Rocket Engines." Russian Journal of Applied Chemistry 93, no. 4 (April 2020): 467–87. http://dx.doi.org/10.1134/s1070427220040011.

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15

Ahn, Byeonguk, Hongjae Kang, Eunkwang Lee, Yongtae Yun, and Sejin Kwon. "Design of Multiport Grain with Hydrogen Peroxide Hybrid Rocket." Journal of Propulsion and Power 34, no. 5 (September 2018): 1189–97. http://dx.doi.org/10.2514/1.b36949.

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16

Huh, Jeongmoo, Botchu V. S. Jyoti, Yongtae Yun, M. N. Shoaib, and Sejin Kwon. "Preliminary Assessment of Hydrogen Peroxide Gel as an Oxidizer in a Catalyst Ignited Hybrid Thruster." International Journal of Aerospace Engineering 2018 (December 30, 2018): 1–14. http://dx.doi.org/10.1155/2018/5630587.

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In regard to propulsion system applications, the stability of liquid propellants in long-term storage is of increasing importance, and this had led to a greater interest in gelation technology. As part of a preliminary test to determine the feasibility of using a gel propellant in a rocket with a catalyst bed, a hybrid rocket with a catalyst reactor using a gel propellant as an oxidizer was tested for the first time in this study. Experiments were conducted with two different oxidizers: one with liquid phase hydrogen peroxide and the other with gel phase hydrogen peroxide, as well as high-density polyethylene as fuel for a 250 N class hybrid thruster performance test. The thruster was designed with the catalyst ignition system, and a catalyst was manufactured to be inserted into the catalyst reactor to facilitate oxidizer decomposition. While the test result with neat hydrogen peroxide indicated sufficient decomposition efficiency using a manganese dioxide/alumina catalyst and successful autoignition of the fuel via the decomposed product, gel hydrogen peroxide exhibited insufficient decomposition and there were difficulties in operating the thruster as a part of the catalyst was covered in the gelling agent. This preliminary study identifies the potential challenges of using a gel phase oxidizer in a catalyst ignited hybrid thruster and discusses the technical issues that should be addressed in regard to a gel propellant hybrid thruster design with a catalyst reactor.

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17

Wernimont, E. J., and S. D. Heister. "Combustion Experiments in Hydrogen Peroxide/Polyethylene Hybrid Rocket with Catalytic Ignition." Journal of Propulsion and Power 16, no. 2 (March 2000): 318–26. http://dx.doi.org/10.2514/2.5571.

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18

Ventura, M. C., and S. D. Heister. "Hydrogen peroxide as an alternate oxidizer for a hybrid rocket booster." Journal of Propulsion and Power 11, no. 3 (May 1995): 562–65. http://dx.doi.org/10.2514/3.23878.

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19

Rusek, John J. "New decomposition catalysts and characterization techniques for rocket-grade hydrogen peroxide." Journal of Propulsion and Power 12, no. 3 (May 1996): 574–79. http://dx.doi.org/10.2514/3.24071.

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20

Kozhevnikov, A., M. Semushina, E. Podrukhina, and D. Kosyakov. "Modification of Hydrolysis Lignin by Hydrogen Peroxide to Obtain an Effective Adsorbent of Highly Toxic Rocket Fuel." Eurasian Chemico-Technological Journal 19, no. 2 (June 30, 2017): 155. http://dx.doi.org/10.18321/ectj646.

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Lignin, a large scale by-product of papermaking and bioethanol production, is applied now in various fields. One of the main areas of use is in the development of different adsorbents, including those intended for detoxification of the spills of 1,1-dimethylhydrazine-based rocket fuel. The present work has shown the possibility of oxidative modification of hydrolytic lignin by hydrogen peroxide to improve the efficiency of the adsorbent. The change in functional composition of the modified adsorbent was studied by IR and NMR spectroscopy. It was shown that the oxidative treatment led to an increase in the content of carbonyl and carboxyl groups, which act as the active adsorption centres for hydrazine molecules. The optimum oxidation conditions were found. An increase in treatment duration from 15 to 120 min and in concentration of hydrogen peroxide from 6 to 30% did not have a significant effect on the functional composition and adsorption properties of lignin.

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21

Whitmore, Stephen A., Christopher J. Martinez, and Daniel P. Merkley. "Catalyst development for an arc-ignited hydrogen peroxide/ABS hybrid rocket system." Aeronautics and Aerospace Open Access Journal 2, no. 6 (2018): 356–88. http://dx.doi.org/10.15406/aaoaj.2018.02.00069.

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22

Maia, Fernanda F., Luis G. F. Pereira, Leonardo H. Gouvea, Fernando S. Costa, and Ricardo Vieira. "CoMn-Based Oxides as Bulk Catalyst for Rocket-Grade Hydrogen Peroxide Decomposition." Journal of Propulsion and Power 30, no. 2 (March 2014): 309–13. http://dx.doi.org/10.2514/1.b34996.

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23

Ferroni Pereira, Luís Gustavo, Leandro José Maschio, Emmanuel Péres de Araújo, Leonardo Henrique Gouvêa, and Ricardo Vieira. "CoMn‐Spinel Oxides as Supported Catalyst for Rocket‐Grade Hydrogen Peroxide Decomposition." Propellants, Explosives, Pyrotechnics 45, no. 10 (August 6, 2020): 1627–33. http://dx.doi.org/10.1002/prep.202000020.

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24

POURPOINT, TIMOTHÉE L., and WILLIAM E. ANDERSON. "HYPERGOLIC REACTION MECHANISMS OF CATALYTICALLY PROMOTED FUELS WITH ROCKET GRADE HYDROGEN PEROXIDE." Combustion Science and Technology 179, no. 10 (September 5, 2007): 2107–33. http://dx.doi.org/10.1080/00102200701386149.

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25

Romantsova, O. V., and V. B. Ulybin. "Safety issues of high-concentrated hydrogen peroxide production used as rocket propellant." Acta Astronautica 109 (April 2015): 231–34. http://dx.doi.org/10.1016/j.actaastro.2014.10.022.

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26

Zhao, Bo, Nanjia Yu, Yufei Liu, Peng Zeng, and Jue Wang. "Unsteady simulation and experimental study of hydrogen peroxide throttleable catalyst hybrid rocket motor." Aerospace Science and Technology 76 (May 2018): 27–36. http://dx.doi.org/10.1016/j.ast.2018.02.008.

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27

Whitmore, Stephen A., Isaac W. Armstrong, Mark C. Heiner, and Christopher J. Martinez. "High-performing hydrogen peroxide hybrid rocket with 3-D printed and extruded ABS fuel." Aeronautics and Aerospace Open Access Journal 2, no. 6 (2018): 334–54. http://dx.doi.org/10.15406/aaoaj.2018.02.00068.

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28

Paulsen, Riley T., and Dmitri S. Kilin. "Silver Nanoparticles for Catalysis of Hydrogen Peroxide Decomposition: Atomistic Modeling." MRS Proceedings 1787 (2015): 21–25. http://dx.doi.org/10.1557/opl.2015.731.

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ABSTRACTThe interest in adopting hydrogen peroxide (H2O2) rocket propulsion systems has rekindled because H2O2 is more environmentally friendly than alternative propellants, has a high density to maximize the oxidizer-to-fuel ratio, and is able to be stored non-cryogenically. Simulations utilizing ab initio molecular dynamics have been generated to analyze the decomposition of H2O2 on the surface of a silver (Ag) metal cluster. The electronic structure for an atomic model of gaseous H2O2 molecules in the vicinity of an Ag13 cluster – one central Ag atom coordinated by the remaining twelve Ag atoms – was analyzed through density functional theory (DFT). After undergoing thermalization, the system was equilibrated at a high temperature of approximately 2000 K. The molecular dynamics did confirm that the Ag catalyst functions in facilitating the H2O2 decomposition to the final products of water and oxygen, while that the overall mechanism contains several intermediates.

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29

Towner, Tyler W., and Donald G. Plumlee. "Design and Fabrication of LTCC Catalyst Chambers." Additional Conferences (Device Packaging, HiTEC, HiTEN, and CICMT) 2011, CICMT (September 1, 2011): 000037–42. http://dx.doi.org/10.4071/cicmt-2011-ta15.

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The reduction in satellite size and mass presents the need to develop a proportionally smaller propulsion system for orbital station keeping. A liquid, monopropellant micropropulsion device made from Low Temperature Co-Fired Ceramics (LTCC) has been developed at Boise State University. This robust, simple design uses an embedded silver catalyst chamber to decompose a rocket-grade hydrogen peroxide monopropellant into a hot gas, which is then expelled out through a nozzle to generate thrust. Using LTCC eliminates the planar geometry fabrication constraint commonly found in silicon MEMS processing. This report presents the design and fabrication, and optimization of the hydrogen peroxide catalyst chamber used in these monopropellant microthrusters. Using the standard fabrication process for LTCC an initial prototype was developed. The design of this initial device was developed to measure the efficiency of the catalyst chamber by evaluating the ability of the device to decompose hydrogen peroxide. Catastrophic cracking within the device substrate was observed during initial testing. In order to obtain sufficient data, it was assumed that the cracking was due to thermal expansion and so a new functional design was implemented that decreased the overall cross sectional area of the device and decreased failure rates. To ensure that this assumption is correct, an investigation of device failure will be presented using an embedded resistor to simulate the catalytic reaction occurring inside the substrate. The results from this investigation will be documented. Additionally, optical microscope images will be used to document the failure investigation process. Several conclusions will be presented to improve the ability to use LTCC for high temperature applications.

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30

Yun, Yongtae, Jeongmoo Huh, Youngil Kim, Seonuk Heo, Hyuntak Kim, and Sejin Kwon. "Scale-Up Validation of Hydrogen Peroxide/High-Density Polyethylene Hybrid Rocket with Multiport Solid Fuel." Journal of Spacecraft and Rockets 58, no. 2 (March 2021): 552–65. http://dx.doi.org/10.2514/1.a34707.

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31

Cai, Guobiao, Chengen Li, and Hui Tian. "Numerical and experimental analysis of heat transfer in injector plate of hydrogen peroxide hybrid rocket motor." Acta Astronautica 128 (November 2016): 286–94. http://dx.doi.org/10.1016/j.actaastro.2016.05.041.

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32

LEPAUS, Bárbara Morandi, Jéssica Souza ROCHA, and Jackline Freitas Brilhante de SÃO JOSÉ. "Organic acids and hydrogen peroxide can replace chlorinated compounds as sanitizers on strawberries, cucumbers and rocket leaves." Food Science and Technology 40, suppl 1 (June 2020): 242–49. http://dx.doi.org/10.1590/fst.09519.

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33

Chen, Song, Jian Li, Lei Wei, Yongliang Jin, Bingxue Cheng, Wu Chen, and Haitao Duan. "Comparative effects of rocket-grade hydrogen peroxide solution on POM and UHMWPE: aging behaviors and tribological properties." Colloid and Polymer Science 296, no. 6 (May 2, 2018): 1087–96. http://dx.doi.org/10.1007/s00396-018-4322-y.

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34

Li, Sen, Yifei Ge, Xiaolin Wei, and Teng Li. "Mixing and combustion modeling of hydrogen peroxide/kerosene shear-coaxial jet flame in lab-scale rocket engine." Aerospace Science and Technology 56 (September 2016): 148–54. http://dx.doi.org/10.1016/j.ast.2016.07.008.

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35

Zeff, Jack D., and Jerome T. Barich. "UV/Oxidation of Organic Contaminants in Ground, Waste and Leachate Waters." Water Quality Research Journal 27, no. 1 (February 1, 1992): 139–50. http://dx.doi.org/10.2166/wqrj.1992.008.

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Abstract Over the past four years, Ultrox International has demonstrated the efficacy of ultraviolet light-enhanced oxidation at industrial, Department of Defense and Superfund sites. Waters containing halogenated solvents such as trichloroethylene, perchloroethylene and other halogenated compounds have been successfully treated with UV/ozone or UV/hydrogen peroxide or UV with ozone and peroxide. Other contaminants such as benzene, toluene, xylene, hydrazines, phenols, chlorophenols, dioxanes, PCBs and pesticides in wastewaters and groundwaters have also been reduced to acceptable discharge standards. Summations of the above projects will be presented, along with some of the technological basis of this process. Data showing comparisons of UV-enhanced oxidation testing with traditional ozonation also will be presented based upon research conducted under government grants. Design and cost data from pilot plant testing and from operations at full-scale commercial installations will be presented. The applications will cover ultraviolet/oxidation systems treating waste water in the wood treating industry, rocket fuel waste water, and groundwater containing chlorinated solvents at automotive, aerospace and electronics manufacturers. A discussion of test results and process economics from a demonstration of the ULTROX® process in the U.S. EPA Superfund Innovative Technology Evaluation (SITE) Program also will be presented.

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36

Maschio, Leandro José, Luis Gustavo Ferroni Pereira, William Müller Meyer, Rodrigo Intini Marques, and Ricardo Vieira. "A DOE STUDY ON THE HYPERGOLICITY OF HYDROGEN PEROXIDE WITH A ROCKET LIQUID FUEL BASED ON MONOETHANOLAMINE AND ETHANOL." International Journal of Energetic Materials and Chemical Propulsion 17, no. 2 (2018): 137–45. http://dx.doi.org/10.1615/intjenergeticmaterialschemprop.2018029025.

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37

Ha, Seong-Up, Seon-Mi Lee, In-Sang Moon, and Soo-Yong Lee. "Numerical Simulations on Combustion Considering Propellant Droplet Atomization and Evaporation of 500 N Class Hydrogen Peroxide / Kerosene Rocket Engine." Journal of the Korean Society for Aeronautical & Space Sciences 40, no. 10 (October 1, 2012): 862–71. http://dx.doi.org/10.5139/jksas.2012.40.10.862.

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38

Li, Huixin, Liang Ye, Xiaolin Wei, Teng Li, and Sen Li. "The design and main performance of a hydrogen peroxide/kerosene coaxial-swirl injector in a lab-scale rocket engine." Aerospace Science and Technology 70 (November 2017): 636–43. http://dx.doi.org/10.1016/j.ast.2017.09.003.

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39

Pacholczak, Andrzej, Małgorzata Zajączkowska, and Karolina Nowakowska. "The Effect of Brassinosteroids on Rootting of Stem Cuttings in Two Barberry (Berberis thunbergii L.) Cultivars." Agronomy 11, no. 4 (April 7, 2021): 699. http://dx.doi.org/10.3390/agronomy11040699.

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Brassinosteroids are a group of over seventy steroid compounds whose discovery in lower and higher plant organisms created new possibilities of plant growth control. The aim of the work was to evaluate the effect of two brassinosteroids: brassinolide (BL) and 24-epibrassinolide (24epiBL) as compared to the auxin rooting enhancer indole-3-butyric acid (IBA), on the rooting of stem cuttings in two Thunberg’s barberry cultivars ‘Maria’ and ‘Red Rocket’. The cuttings were sprayed with water solutions of growth regulators: IBA (200 mg·L−1), 0.05% BL or 24epiBL, as well as with a combination of each of brassinosteroids with the auxin while the control cuttings were sprayed with water. In both cultivars brassinosteroids positively affected a degree of rooting and root length. Their application resulted in elevated contents of chlorophyll, total soluble sugars, free amino acids, hydrogen peroxide and catalase activity. Brassinosteroids were more effective when combined with the auxin than when used singly.

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40

Vorobiev, A. G., I. N. Borovik, and Song-Up Ha. "Analysis of nonstationary thermal state of low-thrust liquid rocket engine with high-concentration hydrogen peroxide and kerosene propellant with film cooling." VESTNIK of the Samara State Aerospace University, no. 1(43) (July 30, 2014): 30. http://dx.doi.org/10.18287/1998-6629-2014-0-1(43)-30-40.

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41

Ariyanti, Dhita, and Muhammad Syaifuddin. "Au Extraction from Mineral Rocks with Aeration-Cyanidation Hydrometallurgy and Comparative Study of Its Effectiveness in Various Methods and Solvents." JKPK (Jurnal Kimia dan Pendidikan Kimia) 4, no. 2 (August 31, 2019): 115. http://dx.doi.org/10.20961/jkpk.v4i2.29020.

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<p>Indonesia is a country with abundant mining potential, one of it is gold (Au) which has a high economic value. Separation of gold metal from mineral rock consists of several methods, such as extraction, hydrometallurgy, and membrane emulsifier technology. These three methods produce different effectiveness of percentage recovery (%recovery), depend on the optimum conditions of each method and type of solvent. This study aims to separate the gold metal from mineral rocks through the hydrometallurgical method with an aeration-cyanidation solvent combination. Hidrometallurgy method is liquid extraction from ores. The test used is a qualitative test of SnCl<sub>2</sub> solution and characterization test with XRF. The results showed that the percentage of recovery (%recovery) of Au with aeration and cyanidation process for 24 hours was 92.8%. Aeration and cyanidation better than emulsifier membrane method and hydrometallurgy with sodium bisulphite, hydrogen peroxide, Cyanex 272 and NH<sub>4</sub>Cl 0.9 M.</p>

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Wei, S. S., M. C. Lee, Y. H. Chien, T. H. Chou, and J. S. Wu. "Experimental investigation of the effect of nozzle throat diameter on the performance of a hybrid rocket motor with swirling injection of high-concentration hydrogen peroxide." Acta Astronautica 164 (November 2019): 334–44. http://dx.doi.org/10.1016/j.actaastro.2019.07.020.

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Xylia, Panayiota, George Botsaris, Panagiotis Skandamis, and Nikolaos Tzortzakis. "Expiration Date of Ready-to-Eat Salads: Effects on Microbial Load and Biochemical Attributes." Foods 10, no. 5 (April 25, 2021): 941. http://dx.doi.org/10.3390/foods10050941.

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When minimally processed vegetables reach their expiration date, expose an increased microbial load. This includes mainly spoilage microorganisms but also foodborne pathogens, thus affecting the quality and safety of highly consumed ready-to-eat salads. A total of 144 ready-to-eat salads from the Cypriot market were analyzed in an attempt to determine the effects of the expiration date on the microbial load and plant metabolic variables of the salads. Possible correlations between them were also investigated for the first time. Furthermore, the impacts of the season (winter, summer), salad producing companies and type of salad and/or their interactions with the tested parameters were investigated. Results revealed that the microbial load (mainly spoilage microorganisms, such as Pseudomonas spp., yeasts and molds) increased towards the end of the shelf life. The microbial load was differentiated among the five salad producers and/or the salad types, highlighting the importance of a common and safe sanitation-processing chain in the preparation of ready-to-eat salads. Summer was the season in which Escherichia coli counts were found to be higher for plain lettuce, while Staphylococcus spp. was increased numbers for the lettuce+endive/radicchio, lettuce+rocket and lettuce+chives type of salads. Additionally, an increased Staphylococcus spp. was observed for plain rocket salads in winter. All samples examined were found negative for Salmonella enterica and Listeria monocytogenes. Moreover, carbon dioxide production and damage indexes (hydrogen peroxide and lipid peroxidation) increased on expiration date on both winter and summer seasons, indicating plant tissue stress at the end of shelf life. These findings indicate that the expiration date and relevant shelf life of processed vegetables are important parameters to be considered when postharvest management is applied to these products, ensuring safety and quality.

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Andriievskyi, M. V., and Yu O. Mitikov. "Influence of propellant leakage from pump area into turbine area on turbo-pump operation stability." Kosmìčna nauka ì tehnologìâ 27, no. 1 (2021): 97–102. http://dx.doi.org/10.15407/knit2021.01.097.

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There is an increasing trend to liquid-propellant rocket engines which run on eco-friendly storable propellant. This trend is mostly dictated by the refusal to use traditional toxic storable propellant in many countries. The most widespread eco-friendly storable propellant is hydrogen peroxide with kerosene. Though, this propellant has a lower specific impulse in comparison with traditional liquid oxygen with kerosene. To compensate the loss of specific impulse, there is a reason to design a staged combustion engine. Evidently, the turbopump is the most complicated system in the staged combustion propulsion system. This fact makes research devoted to turbo-pumps a top priority. The paper aims to determine the influence of propellant leakage from the pump area into the turbine area and create recommendations which would allow organizing the stable operation of turbopump. As a result of turbopump staged combustion cycle testing, a conclusion had been made that leakage, which opens during the test, significantly influences the stability of turbopump operation. Depending on the amount of leakage, the turbine generated power drop was between 20 and 45%, which led to a decrease in rotation speed and outlet pressure of the pump. During the R&D process, a way of leakage influence elimination had been offered. Formulated recommendations may be used during the design process of the turbopump for staged combustion liquid propulsion systems.

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Nosseir, Ahmed E. S., Angelo Cervone, and Angelo Pasini. "Review of State-of-the-Art Green Monopropellants: For Propulsion Systems Analysts and Designers." Aerospace 8, no. 1 (January 15, 2021): 20. http://dx.doi.org/10.3390/aerospace8010020.

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Current research trends have advanced the use of “green propellants” on a wide scale for spacecraft in various space missions; mainly for environmental sustainability and safety concerns. Small satellites, particularly micro and nanosatellites, evolved from passive planetary-orbiting to being able to perform active orbital operations that may require high-thrust impulsive capabilities. Thus, onboard primary and auxiliary propulsion systems capable of performing such orbital operations are required. Novelty in primary propulsion systems design calls for specific attention to miniaturization, which can be achieved, along the above-mentioned orbital transfer capabilities, by utilizing green monopropellants due to their relative high performance together with simplicity, and better storability when compared to gaseous and bi-propellants, especially for miniaturized systems. Owing to the ongoing rapid research activities in the green-propulsion field, it was necessary to extensively study and collect various data of green monopropellants properties and performance that would further assist analysts and designers in the research and development of liquid propulsion systems. This review traces the history and origins of green monopropellants and after intensive study of physicochemical properties of such propellants it was possible to classify green monopropellants to three main classes: Energetic Ionic Liquids (EILs), Liquid NOx Monopropellants, and Hydrogen Peroxide Aqueous Solutions (HPAS). Further, the tabulated data and performance comparisons will provide substantial assistance in using analysis tools—such as: Rocket Propulsion Analysis (RPA) and NASA CEA—for engineers and scientists dealing with chemical propulsion systems analysis and design. Some applications of green monopropellants were discussed through different propulsion systems configurations such as: multi-mode, dual mode, and combined chemical–electric propulsion. Although the in-space demonstrated EILs (i.e., AF-M315E and LMP-103S) are widely proposed and utilized in many space applications, the investigation transpired that NOx fuel blends possess the highest performance, while HPAS yield the lowest performance even compared to hydrazine.

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Hussain, Affan. "Using Pyrolyzed Plastic as an Alternative Fuel Source of Rockets & Hydrogen Peroxide as an Oxidizer." SSRN Electronic Journal, 2021. http://dx.doi.org/10.2139/ssrn.3797779.

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"Toxicity of rocket fuels: comparison of hydrogen peroxide with current propellants." Fuel and Energy Abstracts 43, no. 1 (January 2002): 18. http://dx.doi.org/10.1016/s0140-6701(02)80174-6.

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"The Past and Future Perspectives of Hydrogen Peroxide as Rocket Propellants." Journal of the Korean Society for Aeronautical Space Science 37, no. 7 (July 1, 2009): 717–28. http://dx.doi.org/10.5139/jksas.2009.37.7.717.

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Yun, Yongtae, Kyu-seop Kim, Vikas Khandu Bhosale, and Sejin Kwon. "Effect of Fuel Activation Energy on Ignition of Hydrogen Peroxide Hybrid Rocket." Journal of Spacecraft and Rockets, August 2, 2021, 1–5. http://dx.doi.org/10.2514/1.a35083.

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Wan Ali, Wan Khairuddin, Kiang Long Ang, and Mohammad Nazri Mohd. Jaafar. "Experimental Solid and Liquid Propellant Rocket Development in Universiti Teknologi Malaysia : 1992-2011." Jurnal Teknologi 73, no. 1 (February 10, 2015). http://dx.doi.org/10.11113/jt.v73.3378.

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This paper reports on the research and development activities related to the experimental solid and liquid propellant rocket in Universiti Teknologi Malaysia (UTM) from year 1992 to 2011. A total of 41 closed access academic theses and project papers from UTM library archive were exclusively selected for this review work. Some of these theses and papers originally written in Malay language were translated into English language in this paper for better understanding of the research community. This paper gives a historical insight on the apparatus and methodology designed for educational research activities related to rocket propulsion in UTM. With the available resources within UTM, a few chemical propellant using Ammonium Perchlorate, Potassium Nitrate and hydrogen peroxide as oxidizer were tested in UTM propulsion lab. Besides discussing the rocket fuel components, composite rocket body, ceramic nozzle and alternative binder using natural rubber also covered in this review work. Significant experimental results and numerical findings achieved by UTM researchers were included in this paper.

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