Relevant bibliographies by topics / Hydrogen peroxide rockets

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  1. Journal articles
  2. Dissertations / Theses
  3. Book chapters
  4. Conference papers

Academic literature on the topic 'Hydrogen peroxide rockets'

Author: Grafiati
Published: 4 June 2021
Last updated: 11 February 2022

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Journal articles on the topic "Hydrogen peroxide rockets"

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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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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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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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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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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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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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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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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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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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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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Dissertations / Theses on the topic "Hydrogen peroxide rockets"

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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 potentially improved as well. Using this concept, the payload capacity of a launch vehicle can be increased and provides an excellent option for single stage to orbit vehicles.
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Cheng-RuLu and 呂政儒. "Study of Hypergolic Hybrid Rocket Using Hydrogen Peroxide as Oxidizer." Thesis, 2017. http://ndltd.ncl.edu.tw/handle/y28uzq.

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碩士
國立成功大學
航空太空工程學系
105
With the inherent merits of high maneuverability, hypergolic rocket system is extensively utilized in difficult and complicate space missions, such as planetary landing and orbital injection. Hybrid rockets with hypergolic feature is capable of producing reliable rapid ignition and generating thrust without additional ignition device. Hypergolic mechanisms utilized in hybrid rockets also have enormous research potential which can develop into throttling and restartable propulsion system and fulfilling the functionality of hybrid rocket propulsion. In this research, hypergolic features are achieved by the use of high concentration hydrogen peroxide as oxidizer and catalyst-added fuel grains, a mixture of plastic binder and catalyst for the decomposition of hydrogen peroxide. It is found that as hydrogen peroxide droplets contact with catalytic propellant surface, the exothermic heterogeneous reaction is initiated on the interface and heats up fuel grain surface inducing motor ignition. By modifying the oxidizer operating conditions and fuel grain configurations, we have shown reliably successful ignitions of the motor within a short period of time (〈0.5sec) in hot fire experiments, and based on the trend of pressure rise the hypergolic starting characteristics can be classified into three different kinds of ignition processes. From the experimental observation using the transparent motor, we infer that the motor starting characteristic is related to the interaction of hydrogen peroxide droplets and catalytic propellant surface inducing flooding and splattering phenomena when liquid oxidizers impact on propellant surface, that may lead to hard-start or smooth-start of the rocket motor.
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Yi-LiangChen and 陳奕良. "Development of a 300kgf Bypass Hydrogen Peroxide Hybrid Rocket System." Thesis, 2018. http://ndltd.ncl.edu.tw/handle/66wur8.

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Chen, Ching-Sung, and 陳菁菘. "Studies on the Design of Hydrogen Peroxide / Gasoline Liquid Rocket." Thesis, 2004. http://ndltd.ncl.edu.tw/handle/20138130665926583449.

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Abstract:
碩士
國立成功大學
航空太空工程學系碩博士班
92
Recently, because of the rise in environmental consciousness and under the consideration of cost reduction, toxic propellants such as MMH has gradually been replaced by non-toxic and powerful propellants such as hydrogen peroxide. Due to the high decomposition heat of hydrogen peroxide, the decomposed gases come with very high temperature, so it is very suitable for using in both mono-propellant and bi-propellant liquid rockets. 　　The purpose of this study is to design and test a hydrogen peroxide(50%) / gasoline bi-propellants liquid rocket with catalyst potassium permanganate. The ignition is carried out by powder compound. This rocket is designed in a two-stage of reaction; In the first stage, hydrogen peroxide reacts with potassium permanganate to produce high temperature oxygen and water vapor, and these high temperature gas further reacts and burns with gasoline in the second stage. 　　It is shown that decomposition temperature is not influenced by peroxide flow rate. The decomposition temperature is about 130℃, and the decomposition efficiency is higher than 80% all the time. It reveals that the peroxide has enough time to react with catalyst. In the hot firing test, it is shown that successful ignition and combustion can be maintained continuously, and the maximum chamber pressure is measured about 240 psia, maximum thrust is around 56 lbf, and its specific impulse is about 80s±20s.
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Book chapters on the topic "Hydrogen peroxide rockets"

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"Hydrogen Peroxide, Hydroxyl Ammonium Nitrate, and Other Storable Oxidizers." In Fundamentals of Hybrid Rocket Combustion and Propulsion, 457–88. Reston ,VA: American Institute of Aeronautics and Astronautics, 2007. http://dx.doi.org/10.2514/5.9781600866876.0457.0488.

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Conference papers on the topic "Hydrogen peroxide rockets"

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Cervone, Angelo, Lucio Torre, Luca d'Agostino, Antony J. Musker, Graham T. Roberts, Cristina Bramanti, and Giorgio Saccoccia. "Development of Hydrogen Peroxide Monopropellant Rockets." In 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-5239.

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Wernimont, E., and G. Garboden. "Experimentation with hydrogen peroxide oxidized rockets." In 35th Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1999. http://dx.doi.org/10.2514/6.1999-2743.

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Chiappetta, L., L. Spadaccini, H. Huang, W. Watkins, and A. Crocker. "Modeling a hydrogen peroxide gas generator for rockets." In 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-3223.

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Wernimont, E., and S. Heister. "Characterization of fuel regression in hybrid rockets utilizing hydrogen peroxide oxidizer." In 31st Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1995. http://dx.doi.org/10.2514/6.1995-3084.

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Heister, S., E. Wernimont, E. Wernimont, and S. Heister. "Experimental study of chamber pressure effects in hydrogen peroxide oxidized hybrid rockets." In 33rd Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-2801.

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Morlan, P., P. K. Wu, D. Ruttle, R. Fuller, A. Nejad, and W. Anderson. "Catalyst development for hydrogen peroxide rocket engines." In 35th Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1999. http://dx.doi.org/10.2514/6.1999-2740.

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"Hydrogen peroxide hybrid rocket engine performance investigation." In 30th Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1994. http://dx.doi.org/10.2514/6.1994-3147.

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Musker, Antony. "Highly Stabilised Hydrogen Peroxide as a Rocket Propellant." In 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/6.2003-4619.

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Ahn, Sang-Hee, Tae-Hoon Choi, S. Krishnan, and Choong-Won Lee. "A Laboratory Scale Hydrogen-Peroxide Rocket-Engine Facility." In 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/6.2003-4647.

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Wernimont, E., and S. Heister. "Progress in hydrogen peroxide oxidized hybrid rocket experiments." In 32nd Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1996. http://dx.doi.org/10.2514/6.1996-2696.

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