{"title":"Storage Stability of ADN: Prospects and Challenges (A Short–Review)","authors":"Jayashri Sehajpal, Pratim Kumar, Sunil Kumar Singh, Prasanta Kumar Adak, Srinibas Karmakar","doi":"10.1615/intjenergeticmaterialschemprop.2023045658","DOIUrl":"https://doi.org/10.1615/intjenergeticmaterialschemprop.2023045658","url":null,"abstract":"","PeriodicalId":44417,"journal":{"name":"International Journal of Energetic Materials and Chemical Propulsion","volume":null,"pages":null},"PeriodicalIF":0.7,"publicationDate":"2023-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"67419299","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2023-01-01DOI: 10.1615/intjenergeticmaterialschemprop.2023048965
Yu-Jia Chen, I. Tsai, Ming-Hsun Wu
{"title":"Combustion Characteristics of Hydroxylammonium Nitrate – Water Gels","authors":"Yu-Jia Chen, I. Tsai, Ming-Hsun Wu","doi":"10.1615/intjenergeticmaterialschemprop.2023048965","DOIUrl":"https://doi.org/10.1615/intjenergeticmaterialschemprop.2023048965","url":null,"abstract":"","PeriodicalId":44417,"journal":{"name":"International Journal of Energetic Materials and Chemical Propulsion","volume":null,"pages":null},"PeriodicalIF":0.7,"publicationDate":"2023-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"67422340","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2023-01-01DOI: 10.1615/intjenergeticmaterialschemprop.2023049635
Sergey Rashkovskiy
The analysis of combustion models of the main components of condensed combustion products (CCP) of boron-containing solid propellant: boron, boron carbide, boron nitride and carbon is carried out. Using the available experimental data, the parameters of the combustion model of boron carbide and boron nitride particles are determined. Using the models of combustion of boron, B4C, BN and carbon particles, parametric calculations of the combustion of both individual indicated particles and their mixtures, which simulates the composition of the CCP of boron-containing solid propellant, have been carried out. A comparative analysis of the combustion of particles of boron, B4C, BN, and carbon in proportions characteristic of CCP of boron-containing solid propellants showed that combustion of BN has the least effect on the completeness of combustion of CCP. This is due to its low calorific value and low content in CCP. Ceteris paribus, carbon particles burn the fastest, but their contribution to the completeness of CCP combustion is less than that of boron and boron carbide due to their lower calorific value.
{"title":"Combustion of condensed combustion products of boron-containing solid propellants in air","authors":"Sergey Rashkovskiy","doi":"10.1615/intjenergeticmaterialschemprop.2023049635","DOIUrl":"https://doi.org/10.1615/intjenergeticmaterialschemprop.2023049635","url":null,"abstract":"The analysis of combustion models of the main components of condensed combustion products (CCP) of boron-containing solid propellant: boron, boron carbide, boron nitride and carbon is carried out. Using the available experimental data, the parameters of the combustion model of boron carbide and boron nitride particles are determined. Using the models of combustion of boron, B4C, BN and carbon particles, parametric calculations of the combustion of both individual indicated particles and their mixtures, which simulates the composition of the CCP of boron-containing solid propellant, have been carried out. A comparative analysis of the combustion of particles of boron, B4C, BN, and carbon in proportions characteristic of CCP of boron-containing solid propellants showed that combustion of BN has the least effect on the completeness of combustion of CCP. This is due to its low calorific value and low content in CCP. Ceteris paribus, carbon particles burn the fastest, but their contribution to the completeness of CCP combustion is less than that of boron and boron carbide due to their lower calorific value.","PeriodicalId":44417,"journal":{"name":"International Journal of Energetic Materials and Chemical Propulsion","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135754025","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2023-01-01DOI: 10.1615/intjenergeticmaterialschemprop.2023048100
Davide Zuin, Simone La Luna, Filippo Maggi
Additive manufacturing techniques are modifying the space propulsion manufacturing panorama. These technologies, which are already implemented in manufacturing of aerospace components, are still to be further analysed and a complete quality assurance program to be defined. In this paper, a state of the art analysis of quality assurance for space propulsive applications is performed. In particular, the focus is centred on material challenges associated to space propulsion: the research is oriented towards powders and samples implemented in selective laser melting technologies. In particular, a qualification process of the supply chain related to powders in space propulsion is reported. Furthermore, the application of this process to a case study material is detailed, and preliminary result data are considered. Finally, a review of the qualification process is performed and suggestions for future work on this topic are presented.
{"title":"Overview of Additive Manufacturing and Quality Assurance of Powders for Space Propulsive Components","authors":"Davide Zuin, Simone La Luna, Filippo Maggi","doi":"10.1615/intjenergeticmaterialschemprop.2023048100","DOIUrl":"https://doi.org/10.1615/intjenergeticmaterialschemprop.2023048100","url":null,"abstract":"Additive manufacturing techniques are modifying the space propulsion manufacturing panorama. These technologies, which are already implemented in manufacturing of aerospace components, are still to be further analysed and a complete quality assurance program to be defined. In this paper, a state of the art analysis of quality assurance for space propulsive applications is performed. In particular, the focus is centred on material challenges associated to space propulsion: the research is oriented towards powders and samples implemented in selective laser melting technologies. In particular, a qualification process of the supply chain related to powders in space propulsion is reported. Furthermore, the application of this process to a case study material is detailed, and preliminary result data are considered. Finally, a review of the qualification process is performed and suggestions for future work on this topic are presented.","PeriodicalId":44417,"journal":{"name":"International Journal of Energetic Materials and Chemical Propulsion","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135102400","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2023-01-01DOI: 10.1615/intjenergeticmaterialschemprop.2023047125
Leo Peiffer, M. Tajmar, G. Sánchez-Arriaga, M. Harnisch, Christian Perfler
{"title":"ELECTRICAL PERFORMANCE EVALUATION OF PHOTOVOLTAIC TETHER SAMPLES FOR DEORBIT APPLICATIONS","authors":"Leo Peiffer, M. Tajmar, G. Sánchez-Arriaga, M. Harnisch, Christian Perfler","doi":"10.1615/intjenergeticmaterialschemprop.2023047125","DOIUrl":"https://doi.org/10.1615/intjenergeticmaterialschemprop.2023047125","url":null,"abstract":"","PeriodicalId":44417,"journal":{"name":"International Journal of Energetic Materials and Chemical Propulsion","volume":null,"pages":null},"PeriodicalIF":0.7,"publicationDate":"2023-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"67421352","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2023-01-01DOI: 10.1615/intjenergeticmaterialschemprop.2023048721
S. Gallier
{"title":"A PHYSICAL MODEL FOR THE PREDICTION OF ALUMINUM OXIDE RESIDUES","authors":"S. Gallier","doi":"10.1615/intjenergeticmaterialschemprop.2023048721","DOIUrl":"https://doi.org/10.1615/intjenergeticmaterialschemprop.2023048721","url":null,"abstract":"","PeriodicalId":44417,"journal":{"name":"International Journal of Energetic Materials and Chemical Propulsion","volume":null,"pages":null},"PeriodicalIF":0.7,"publicationDate":"2023-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"67422195","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2023-01-01DOI: 10.1615/intjenergeticmaterialschemprop.v22.i1.40
Harshit Shukla, Velidi V. S. S. Gurunadh
In the past few decades, space technology has moved toward using many small satellites working in a cluster instead of making individual satellites for space missions. Nano or microsatellites increase the reliability of the mission while minimizing cost, rather than having one large satellite increasing both the cost and the failure risk for any given space mission. Considering the case of a small satellite cluster, it is easy to manage mission requirements with less complexity during any hazard, compared to an individual satellite. All of this has led to the increasing application of micro and nanosatellites in space engineering. These small satellites are propelled by micropropulsion created by microthrusters. Currently, liquid, gas, and electrical thrusters are the most common. This paper mainly describes the recent advancements in the field of MEMS microthrusters. MEMS (microelectromechanical system) thrusters are used in small satellites in a variety of ways that require very little thrust. In the paper discussion, MEMS-based solid-propellant microthrusters (SPMs) are delineated. All advancements in the MEMS solid thrusters are indicated in the article, dedicated to mounting schemes, designing approaches, and various performance testing experiments. The main challenge in this technology is combustion, which takes place in an exceptionally small volume.
{"title":"A STUDY ON THE RECENT ADVANCES IN THE DESIGN OF MEMS-BASED SOLID MICROTHRUSTERS","authors":"Harshit Shukla, Velidi V. S. S. Gurunadh","doi":"10.1615/intjenergeticmaterialschemprop.v22.i1.40","DOIUrl":"https://doi.org/10.1615/intjenergeticmaterialschemprop.v22.i1.40","url":null,"abstract":"In the past few decades, space technology has moved toward using many small satellites working in a cluster instead of making individual satellites for space missions. Nano or microsatellites increase the reliability of the mission while minimizing cost, rather than having one large satellite increasing both the cost and the failure risk for any given space mission. Considering the case of a small satellite cluster, it is easy to manage mission requirements with less complexity during any hazard, compared to an individual satellite. All of this has led to the increasing application of micro and nanosatellites in space engineering. These small satellites are propelled by micropropulsion created by microthrusters. Currently, liquid, gas, and electrical thrusters are the most common. This paper mainly describes the recent advancements in the field of MEMS microthrusters. MEMS (microelectromechanical system) thrusters are used in small satellites in a variety of ways that require very little thrust. In the paper discussion, MEMS-based solid-propellant microthrusters (SPMs) are delineated. All advancements in the MEMS solid thrusters are indicated in the article, dedicated to mounting schemes, designing approaches, and various performance testing experiments. The main challenge in this technology is combustion, which takes place in an exceptionally small volume.","PeriodicalId":44417,"journal":{"name":"International Journal of Energetic Materials and Chemical Propulsion","volume":null,"pages":null},"PeriodicalIF":0.7,"publicationDate":"2023-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"67425201","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2023-01-01DOI: 10.1615/intjenergeticmaterialschemprop.v22.i2.50
H. Boenish, Carlos Garcia, P. Venkatesh, J. Costello, Evan Daniel, Michael Fitzpatrick, Curtis A. Foster, Benjamin Graybill, Mesa Hollinbeck, Daniel Kolano, Margaret Lea, Lars Osborne, Patrick Riley, Tucker Smith, Da-rid F. Barnes
A thruster, designated LE111, utilizes hydrazine and MON3 as fuel and oxidizer and produces a thrust of 111 N at nominal operating conditions with an Isp of up to 328 s. The thruster is throttleable through the use of separate fuel and oxidizer metering valves and is able to transition to a hydrazine monopropellant mode at any point during its operation. Completed qualification testing has demonstrated a versatile operating box that includes chamber pressure-mixture ratio excursions, heated propellants up to 341 K, and gaseous helium ingestion through propellant flow paths. Overall, the thruster has achieved 15,455 s of accumulated on-time and a maximum continuous burn time of 6,000 s. The thruster achieves its performance through a novel micro-coaxial gas-gas injection scheme and an innovative regeneratively cooled combustion chamber, which uses the oxidizer as the working fluid. The thruster's capabilities and performance recorded during the completed qualification testing are described, and its design is outlined. This paper is published with the permission of the authors granted to 3AF – Association Aéronautique et Astronautique de France (www.3AF.fr) organizer of the Space Propulsion International conference.
{"title":"111 N HYDRAZINE BIPROPELLANT ENGINE (HBE) WITH GAS-GAS INJECTION","authors":"H. Boenish, Carlos Garcia, P. Venkatesh, J. Costello, Evan Daniel, Michael Fitzpatrick, Curtis A. Foster, Benjamin Graybill, Mesa Hollinbeck, Daniel Kolano, Margaret Lea, Lars Osborne, Patrick Riley, Tucker Smith, Da-rid F. Barnes","doi":"10.1615/intjenergeticmaterialschemprop.v22.i2.50","DOIUrl":"https://doi.org/10.1615/intjenergeticmaterialschemprop.v22.i2.50","url":null,"abstract":"A thruster, designated LE111, utilizes hydrazine and MON3 as fuel and oxidizer and produces a thrust of 111 N at nominal operating conditions with an Isp of up to 328 s. The thruster is throttleable through the use of separate fuel and oxidizer metering valves and is able to transition to a hydrazine monopropellant mode at any point during its operation. Completed qualification testing has demonstrated a versatile operating box that includes chamber pressure-mixture ratio excursions, heated propellants up to 341 K, and gaseous helium ingestion through propellant flow paths. Overall, the thruster has achieved 15,455 s of accumulated on-time and a maximum continuous burn time of 6,000 s. The thruster achieves its performance through a novel micro-coaxial gas-gas injection scheme and an innovative regeneratively cooled combustion chamber, which uses the oxidizer as the working fluid. The thruster's capabilities and performance recorded during the completed qualification testing are described, and its design is outlined. This paper is published with the permission of the authors granted to 3AF – Association Aéronautique et Astronautique de France (www.3AF.fr) organizer of the Space Propulsion International conference.","PeriodicalId":44417,"journal":{"name":"International Journal of Energetic Materials and Chemical Propulsion","volume":null,"pages":null},"PeriodicalIF":0.7,"publicationDate":"2023-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"67425304","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2022-01-01DOI: 10.1615/intjenergeticmaterialschemprop.2022041581
A. Zarei, K. Mardi
{"title":"A simple and selective spectrophotometric method for determination of ethyl centralite as stabilizer in double base solid propellants: a comparative study with high performanc","authors":"A. Zarei, K. Mardi","doi":"10.1615/intjenergeticmaterialschemprop.2022041581","DOIUrl":"https://doi.org/10.1615/intjenergeticmaterialschemprop.2022041581","url":null,"abstract":"","PeriodicalId":44417,"journal":{"name":"International Journal of Energetic Materials and Chemical Propulsion","volume":null,"pages":null},"PeriodicalIF":0.7,"publicationDate":"2022-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"67417663","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
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