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Journal articles on the topic 'Solid propellant rocket'

Author: Grafiati

Published: 4 June 2021

Last updated: 26 July 2025

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1

Runtu, Khevinadya Ramadhani, Wahyu Sri Setiani, and Mala Utami. "Application Energetic Materials for Solid Composite Propellant to Support Defense Rocket Development." International Journal of Social Science Research and Review 6, no. 1 (2023): 153–59. http://dx.doi.org/10.47814/ijssrr.v6i1.756.

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In its application in space technology, solid composite propellants are often used as fuel in rockets for military purposes. Increasing the energy of the propellant is carried out by observing two stages, the use of energetic materials and improvements to the process technology. The current development of propellant technology makes it possible to use new energetic materials, simple formulations, high energy, and smokeless. The purpose of this research is to find out developments related to the use of highly energetic materials as raw materials for composite propellants for defense rockets at

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2

Jadhav, Shruti Dipak, Tapas Kumar Nag, Atri Bandyopadhyay, and Raghvendra Pratap Singh. "Experimental and Computational Investigation of Sounding Solid Rocket Motor." 3 1, no. 3 (2022): 29–38. http://dx.doi.org/10.46632/jame/1/3/5.

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Experimental sounding rockets are important contributors to aerospace engineering research. However, experimental-sounding rockets are rarely used for student research projects by institutes in India. The unavailability of rocket motors, which require complex machining and explosive propellants, is a major barrier to the use of sounding rockets in student research projects. We ran into this problem while developing a sounding rocket motor for project and learning purposes. The project focuses on designing and constructing a solid rocket motor that researchers can use as the primary propulsion

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3

Said, A., A. Maraden, T. M. Elhedery, A. M. abd Elall, and S. Elbasuney. "Propulsion theoretical and experimental analysis of composite propellants motors." Journal of Physics: Conference Series 2616, no. 1 (2023): 012057. http://dx.doi.org/10.1088/1742-6596/2616/1/012057.

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Abstract Rockets have revolutionized space technology and human space exploration. Most rockets and missiles are both propelled by rocket motors that use composite solid propellants. The ICT code and the NSAS CEA code are two programs that can be used to forecast theoretical propulsion parameters for composite solid rocket propellant. Rocket propellant performance is governed by a specific impulse factor, which is calculated theoretical and experiment. In this paper, the theoretical specific impulse for different composite solid propellant formulations at 70 bar combustion pressure and an adap

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4

Křepský, Martin. "Rocket Engines’ Solid Propellants and Combustion Products." Science & Military 19, no. 2 (2024): 36–42. https://doi.org/10.52651/sam.a.2024.2.36-42.

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Rocket technology has shown considerable progress in recent decades. In addition to peaceful use, rockets are used in the military as a means of transporting destructive charges on a target. Any information obtained, even a partial one, could be used to prevent or mitigate a missile threat. Different types of rocket engines are sources of rocket propulsion. One of the factors by which individual types of rockets differ from each other is the type of fuel used. Combustion of rocket fuel creates a flame that is a source of radiation. The article analyzes the composition of different types of sol

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S A, Reshmitha Shree, Saif Ahmed Ansari, Steven Raj, and Sukh Arora. "EVALUATION OF SOLID ROCKET PROPELLANTS FOR LOW EARTH ORBIT." INTERANTIONAL JOURNAL OF SCIENTIFIC RESEARCH IN ENGINEERING AND MANAGEMENT 08, no. 008 (2024): 1–3. http://dx.doi.org/10.55041/ijsrem37252.

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In contemporary aerospace technology, solid rocket propellants are commonly employed in the thriller and boost of space cargoes to LEO. These are reliable, uncomplicated, and high in thrust; and thus, can be used in both military as well as civil space ventures. This paper provides a comprehensive evaluation of five prominent solid rocket propellants: Five categories namely Ammonium Perchlorate Composite Propellant (APCP), Double-Base Propellant, Composite Modified Double Base (CMDB) Propellant, Hydroxyl-terminated polybutadiene (HTPB)-Based Propellant, and Ammonium Nitrate Composite Propellan

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Jain, Prakhar, Vineet Kumar Rathi, and Shelly Biswas. "Study of Aging Characteristics for Metalized HTPB Based Composite Solid Propellants Stored in Ambient Conditions." Defence Science Journal 74, no. 5 (2024): 615–26. http://dx.doi.org/10.14429/dsj.74.19786.

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The aging of any propellant is defined as the change in the physical, chemical, and performance parameters of solid rocket propellants. The propellant’s service life and aging properties are important parameters of the study, especially for missiles and other defense applications. Hydroxyl-terminated polybutadiene (HTPB) based composite solid propellants with ammonium perchlorate (AP) are the most prominently used propellants in the operations of solid rocket motors in the defense and space sectors. Thus, studying this composite solid propellant is of essential when determining ambient service

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7

Alblooshi, Abdulwahed, Awatif Ahmed, Maha Almazrouei, Nawwaf Alali, and Mohammed Alazizi. "Development of KNSB Rocket Motor for UAVs’ Rocket Assisted Take-Off (RATO) Boosters." Journal of Physics: Conference Series 2891, no. 14 (2024): 142021. https://doi.org/10.1088/1742-6596/2891/14/142021.

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Abstract This research paper presents the design and development of a solid rocket motor composed of sugar-based propellant for Rocket Assist Take Off (RATO) systems. RATO systems can be integrated with different platforms that require an initial boost to be launched such as the C130 aircraft. Sugar-based propellants offer a cost-effective and environmentally friendly alternative to conventional solid rocket propellants with effective launch performances. The research purpose is to design and develop prototype rockets, verify rocket performance, and optimize the design for upscaling to larger

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8

Aswin, C., S. Srichand Vishnu, D. Aravind Kumar, et al. "Studies on Ignition Delay and Flame Spread in High-Performance Solid Rocket Motors." Applied Mechanics and Materials 232 (November 2012): 316–21. http://dx.doi.org/10.4028/www.scientific.net/amm.232.316.

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Accurate prediction of ignition delay and flame spread rate in solid propellant rocket motors is of great topical interest. In this paper using a standard k-ω turbulence model numerical studies have been carried out to examine the influence of solid rockets port geometry on ignition delay and the flame spread pattern. We observed that with the same inflow conditions and propellant properties heat flux histories and ignition time sequence are different for different port geometries. We conjectured from the numerical results that in solid rocket motors with highly loaded propellants, mass flux o

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9

Aziz, Amir, Rizalman Mamat, Wan Khairuddin Wan Ali, and Mohd Rozi Mohd Perang. "Review on Typical Ingredients for Ammonium Perchlorate Based Solid Propellant." Applied Mechanics and Materials 773-774 (July 2015): 470–75. http://dx.doi.org/10.4028/www.scientific.net/amm.773-774.470.

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Ammonium perchlorate (AP) based solid propellant is a modern solid rocket propellant used in various applications. The combustion characteristics of AP based composite propellants were extensively studied by many research scholars to gain higher thrust. The amount of thrust and the thrust profile, which may be obtained from a specific grain design, is mainly determined by the propellant composition and the manufacturing process that produces the solid propellant. This article is intended to review and discuss several aspects of the composition and preparation of the solid rocket propellant. Th

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10

Jobanpreet Singh. "Comparative Analysis of Potassium Nitrate-Based Solid Propellant Rockets: Sucrose vs. Sorbitol." International Journal of Advanced Research and Interdisciplinary Scientific Endeavours 2, no. 2 (2025): 462–71. https://doi.org/10.61359/11.2206-2507.

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This study provides a comprehensive comparative analysis of two strong propellant rocket fuels: potassium nitrate blended with sucrose (sugar) and potassium nitrate mixed with sorbitol. The primary objective of this study is to assess the performance, efficiency, and practicality of these propellant combinations through a series of static and dynamic tests. The research begins with the preparation and characterization of each propellant combination, ensuring consistency in composition and production procedures. The static tests involve measuring the thrust produced by each propellant using a p

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11

Srivastava, Sachin, G. Hamshitha, V. Jagannath, et al. "Numerical Studies of Solid Rocket Propellant PMMA-PBAN-ALF3-Nitrocellulose-Difluoramine." Journal of Physics: Conference Series 2856, no. 1 (2024): 012010. http://dx.doi.org/10.1088/1742-6596/2856/1/012010.

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Abstract The aim of the new investigation is the evaluation of solid rocket Propellant. In which performing numerical analysis of solid rocket propellant and calculating the constraints involved as derived from thrust i.e. velocity involved in the solid rocket propulsion motor usage. This paper aims to show the viability of solid rocket propellant for modern and future applications. Solid rocket motors are simple in design and fabricating. The need for a propellant that produces the same specific impulse as another chemical rocket engine. So it is needed to have a solid rocket motor with an en

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12

Lu, Zhishan. "Recent Advances of Design Optimization Techniques in Solid Rocket." Highlights in Science, Engineering and Technology 37 (March 18, 2023): 252–61. http://dx.doi.org/10.54097/hset.v37i.6080.

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A solid-propellant rocket or solid rocket refers to a rocket with an engine using solid propellants. The earliest solid rockets were powered by gunpowder. It is still used today in military armaments worldwide, model rockets, solid rocket boosters and on larger applications for their simplicity and reliability. With the fast development in the complexity of rockets, the importance of optimisation where the overall performance is maximised has been shown. Engineers are routinely given design tasks to find a design meeting the stringent constraints. For instance, researchers developed different

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13

Zhang, Yin, Zhensheng Sun, Yu Hu, et al. "Numerical Simulation of the Gas Flow of Combustion Products from Ignition in a Solid Rocket Motor Under Conditions of Propellant Creep." Aerospace 12, no. 2 (2025): 153. https://doi.org/10.3390/aerospace12020153.

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The development of modern solid rocket technology with high-performance and high-loading ratio propellants places higher requirements on the safety and stability of the solid rocket motor. The propellant of the solid rocket motor will creep during long-term vertical storage, which may adversely affect its regular operation. The ignition transient process is a critical phase in the operation of solid rocket motors. The Abaqus v.2022 finite element simulation software is used to analyze the ignition transient under propellant creep conditions and obtain the deformed combustion chamber profile. T

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14

Ma, Jiaju. "Analysis of the characteristics of rocket propellant." Theoretical and Natural Science 5, no. 1 (2023): 490–95. http://dx.doi.org/10.54254/2753-8818/5/20230296.

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Rocket propellant is an important part of the rocket. Solid or liquid propellant will burn in the engine combustion chamber, and then a large amount of high-pressure gas will be generated. High-pressure gas will be ejected from the engine nozzle at a high speed, generating a reaction force on the rocket, so that the rocket will advance in the opposite direction of the gas injection. This paper mainly analyzes the advantages and disadvantages of current propellants and conceives a theoretically feasible propellant selection method. The main method of research is to calculate the theory of each

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15

Abdelraouf, A. M., O. K. Mahmoud, and M. A. Al-Sanabawy. "Thrust termination of solid rocket motor." Journal of Physics: Conference Series 2299, no. 1 (2022): 012018. http://dx.doi.org/10.1088/1742-6596/2299/1/012018.

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Abstract Rocket motors are engines that create the necessary thrust for the rocket motion. There are different types of rocket motors based on the propellant state, such as solid propellant rocket motors, liquid propellant rocket motors, and hybrid propellant rocket motors. One of the biggest disadvantages of solid propellant rocket motors, in comparison to liquid and hybrid propellant rocket motors, is that they are extremely difficult to extinguish, necessitating the use of specific devices. This paper reviews various ways for thrust termination such as fluid injection, rapid increase in thr

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16

Sheikholeslam, Mohammad Reza Zadeh, Daryoosh Kazemi, and Hooman Amiri. "Experimental Analysis of the Influence of Length to Diameter Ratio on Erosive Burning in a Solid Tubular Propellant Grain." Applied Mechanics and Materials 110-116 (October 2011): 3394–99. http://dx.doi.org/10.4028/www.scientific.net/amm.110-116.3394.

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Erosive burning usually refers to the increase in the propellant burning rate caused by high velocity combustion gasses flowing over the propellant surface. It may seriously affect the performance of solid-propellant rocket motors [1]. A series of experiments had been made to study the effects of length to the diameter ratio in a single tubular propellant grain on the erosive burning phenomenon. In the same combustion pressure and different grain geometries, the burning pattern ofAP1based propellantwere recorded. Furthermore, pressure-time curve for each condition was obtained. The mean veloci

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17

Ankit, Kumar. "Experimental Study on High Powered Rocket with SS Motor &Parachute Ejection System." International Journal of Innovative Science and Research Technology 8, no. 5 (2023): 1425–28. https://doi.org/10.5281/zenodo.7982428.

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A solid rocket is a high powered solid propellant-driven rocket which has a motor with no movingparts. But mostly, it is used for single use purposes. So, we have designed a high-power solid propulsion rocket SS motor with parachute ejection system. Parachute ejection system refers to usage of parachutes namely, a main parachute, which deploys at the apogee, due to the max apogeerocket tilts and takes instantaneous recordings, and a main parachute which deploys at a preprogrammed altitude. The propellant of the rocket solid fuel which give high thrust ratio and couldlift the rocket at distant

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18

Сюткина-Доронина, Светлана Васильевна. "ДО ПИТАННЯ ОПТИМІЗАЦІЇ ПРОЕКТНИХ ПАРАМЕТРІВ І ПРОГРАМ УПРАВЛІННЯ РАКЕТНОГО ОБ'ЄКТА З РАКЕТНИМ ДВИГУНОМ НА ТВЕРДОМУ ПАЛИВІ". Aerospace Technic and Technology, № 2 (25 березня 2017): 44–59. http://dx.doi.org/10.32620/aktt.2017.2.06.

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The complex problem of the simultaneous optimization of the control programs and design parameters of the controlled single-stage rocket with cruise solid propellant rocket engine is formulated. The problem is formulated as an problem of optimal control theory with limitations in the form of equalities and differential constraints. The structure of the optimized parameters of the solid propellant rocket engine includes design parameters of the controlled solid propellant rocket and parameters characterizing the programs of the motion control of the controlled solid propellant rocket and parame

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19

Yue, Songchen, Lu Liu, Huan Liu, et al. "Agglomerate Size Evolution in Solid Propellant Combustion under High Pressure." Aerospace 10, no. 6 (2023): 515. http://dx.doi.org/10.3390/aerospace10060515.

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Solid propellant combustion and flow are significantly affected by condensed combustion products (CCPs) in solid rocket motors. A new aluminum agglomeration model is established using the discrete element method, considering the burning rate and formulation of the propellant. Combining the aluminum combustion and alumina deposition model, an analytical model of the evolution of CCPs is proposed, capable of predicting the particle-size distribution of completely burned CCPs. The CCPs near and away from the propellant burning surface are collected by a special quench vessel under 6~10 MPa, to ve

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20

Murachman, Bardi, Sajono Sajono, Fauzan Afandi, and Johan Khaeri. "Optimization Study of the Solid Propellant (Rocket Fuel) Based on Extracted Bitumen of Indonesian Natural Buton Asphalt." ASEAN Journal of Chemical Engineering 13, no. 2 (2014): 57. http://dx.doi.org/10.22146/ajche.49732.

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The asphalt propellant for rockets has been investigated since 1960. This material has been developed with the variation of fuels, oxidizer, binders, metal elements and additives. As solid propellant, it has some advantages and disadvantages during the implementation. At present, Extracted Buton asphalt has been studied as an alternative propellant fuels. It is a natural asphalt, extracted from Buton island asphalt rock. When the extract of buton asphalt is mixed with oxidizer, binder, and metal powder, it can be functioned as propellant which is able to release high intensity of energy, have

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21

Zhang, Jing, Zhen Wang, Shixiong Sun, and Yunjun Luo. "Influence of Solid Filler on the Rheological Properties of Propellants Based on Energetic Thermoplastic Elastomer." Materials 16, no. 2 (2023): 808. http://dx.doi.org/10.3390/ma16020808.

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Glycidyl azide polymer-energetic thermoplastic elastomer propellant (GAP-ETPE) has high development prospects as a green solid propellant, although the preparation of GAP-ETPE with excellent performance is still a challenge. Focusing on the demand of high-strength solid propellants for free-loading rocket motors, a GAP-ETPE model propellant with excellent overall performance was prepared in this work, and the influence of adhesive structure characteristics on its fluidity was studied. Furthermore, the influence of filler on the rheological properties of the model propellant was investigated by

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22

Czerwińska, Magdalena, and Piotr Prasuła. "STUDY OF THERMO-MECHANICAL PROPERTIES OF AGED HOMOGENEOUS SOLID ROCKET PROPELLANT ACCORDING TO STANAG REQUIREMENTS." PROBLEMY TECHNIKI UZBROJENIA 145, no. 1 (2018): 47–63. http://dx.doi.org/10.5604/01.3001.0012.1325.

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Proper operation of rocket motor depends significantly on thermo-mechanical properties of propellant used. For this reason it is important that characteristics of a particular propellant versus the time and temperature pass a thorough investigation to assess its operation at different conditions. The paper illustrates investigations of ageing process influencing thermo-mechanical properties of homogeneous rocket propellant. A selected type of rocket propellant was subjected to accelerated ageing in conditions specified in AOP-48 document to establish in the next step its thermal and mechanical

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23

Song, Shixiong, Quanbin Ren, Min Tang, Jiawei Shi, and Jiawei Wang. "A Study on Ultra-Low-Pressure Ratio Technology on the Basis of 3D-Printed Propellant for a Solid Rocket Motor." Aerospace 10, no. 10 (2023): 862. http://dx.doi.org/10.3390/aerospace10100862.

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Fused deposition technology (FDM), as an additive manufacturing (AM) technology, holds immense potential in the field of solid grain manufacturing. It can accomplish complex grain shaping with ultra-low-pressure ratios, which are challenging to achieve using conventional grain manufacturing processes. In this work, solid propellants with complex structures were made by using 3D printing. The obtained sample grains of the solid propellants had a complete structure, which conformed to the design model and had no obvious defects. Then, the combustion and mechanical properties of the printed solid

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Soe, Hlaing Tun, and Hong Jun Xiang. "Star Grain Regression under Spin Induced Acceleration Effect." Applied Mechanics and Materials 110-116 (October 2011): 451–56. http://dx.doi.org/10.4028/www.scientific.net/amm.110-116.451.

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Spinning is used in some of solid rocket motors to increase the flight trajectory precision or for stability requirements. The angular acceleration due to the spin effect increases the burning rate of solid propellant and changes the motor performance by increasing the operating pressure and decreasing the burning time. So it is important to know the grain regression taken place in the solid propellant rocket motor in the acceleration field. In this study, we represent the grain regression analysis of two-dimensional axis-symmetric star grain configuration of the solid propellant rocket motor

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25

Pourpoint, Timothee L., Tyler D. Wood, Mark A. Pfeil, John Tsohas, and Steven F. Son. "Feasibility Study and Demonstration of an Aluminum and Ice Solid Propellant." International Journal of Aerospace Engineering 2012 (2012): 1–11. http://dx.doi.org/10.1155/2012/874076.

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Aluminum-water reactions have been proposed and studied for several decades for underwater propulsion systems and applications requiring hydrogen generation. Aluminum and water have also been proposed as a frozen propellant, and there have been proposals for other refrigerated propellants that could be mixed, frozen in situ, and used as solid propellants. However, little work has been done to determine the feasibility of these concepts. With the recent availability of nanoscale aluminum, a simple binary formulation with water is now feasible. Nanosized aluminum has a lower ignition temperature

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CEGŁA, Marcin, Janusz ZMYWACZYK, and Piotr KONIORCZYK. "Analysis of Thermal Decomposition of Solid Rocket Propellants." Problems of Mechatronics Armament Aviation Safety Engineering 10, no. 2 (2019): 43–54. http://dx.doi.org/10.5604/01.3001.0013.2115.

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The paper presents results of thermal decomposition analysis of selected solid rocket propellants. Homogeneous propellant PAC and heterogeneous propellant H2 were subjected to simultaneous thermal analysis with the use of NETZSCH STA 2500 Regulus device with five heating rates of 2.5, 5, 7.5, 10 and 15 K/min. The method combines TG, DTG and DTA analytical techniques in a single measurement. The aim of the conducted experiments was to study thermal decomposition of these energetic materials as well as to determine activation energy of the decomposition process and the preconditioning factor fro

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Timarov, A. G., I. O. Eliseev, D. M. Borisov, and V. V. Mironov. "ANALYSIS OF FOREIGN EXPERIENCE OF DUAL USE SOLID ROCKET MOTORS." Вестник Российской академии наук 93, no. 12 (2023): 1151–61. http://dx.doi.org/10.31857/s0869587323120083.

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In countries, such as the United States, China, India, France, Israel and many others, solid-propellant rocket engine technologies are used not only in military missiles, but also in launch vehicles of the rocket and space industry. Such an approach of dual application of technologies makes it possible to introduce and develop new innovative solutions to increase the degree of unification of related technologies. One of the most important factors influencing the efficiency of using solid propellant rocket engines in space programs is the cost of solid rocket propellants and propulsion system c

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Wang, Zhuopu, Wenchao Zhang, and Yuanzhe Liu. "A Phenomenological Model for the Unsteady Combustion of Solid Propellants from a Zel’dovich-Novzhilov Approach." Aerospace 10, no. 9 (2023): 767. http://dx.doi.org/10.3390/aerospace10090767.

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Solid rocket motors are prone to combustion instabilities, which may lead to various problems for the rockets, from unexpected oscillations, precision decreasing, to explosion. The unsteady combustion dynamics of the propellants play a crucial role in most solid rocket motors experiencing combustion instabilities. A modeling framework for the unsteady combustion of the solid propellant is constructed via the Zel’dovich-Novozhilov (ZN) phenomenological perspective. The overall unsteady combustion features of a quasi-steady homogeneous one-dimensional (QSHOD) model are investigated. The phenomen

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Mihailescu, Cristina. "Practical Methods of Optimizing the Maximum Range for Rockets." International Journal on Applied Physics and Engineering 2 (October 5, 2023): 137–43. http://dx.doi.org/10.37394/232030.2023.2.13.

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Range extension for artillery projectiles, rockets, and missiles is a problem of trajectory optimization based on a set of constraints aimed at maximizing the range as a measure of performance. Solid Rocket Motors (SRM) are rocket motors that use solid propellants. For higher engine efficiency and cost minimization, optimization of the engine is necessary, which implies a modification of the schematics of the engine. SRM optimization is currently a key topic in aerospace engineering research. Because some input data remain constant, others can be considered as variables, and their influence on

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Dogadkin, Vladimir A., Vadim V. Kolga, and Vitaly R. Trukhin. "Parametrical analysis of the strength of the nozzle of a solid fuel rocketer." Siberian Aerospace Journal 24, no. 3 (2023): 510–20. http://dx.doi.org/10.31772/2712-8970-2023-24-3-510-520.

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The paper presents an approach to solving the problem of designing a solid propellant rocket engine nozzle using a design feature in the form of a carbon fiber insert. The design task is to select the optimal parameters of the plate thickness (plate shape) that provide the necessary strength and stability of the structure with a minimum weight. During the design process, a parametric analysis of a carbon fiber insert in the solid propellant rocket nozzle was carried out. By varying the thickness of the plate, an optimal design scheme is found that meets the given safety and stability factors.

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Pang, W. Q., F. Q. Zhao, L. T. DeLuca, C. Kappenstein, H. X. Xu, and X. Z. Fan. "Effects of Nano-Sized Al on the Combustion Performance of Fuel Rich Solid Rocket Propellants." Eurasian Chemico-Technological Journal 18, no. 3 (2016): 197. http://dx.doi.org/10.18321/ectj425.

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Several industrial- and research – type fuel rich solid rocket propellants containing nano-metric aluminum metal particles, featuring the same nominal composition, were prepared and experimentally analyzed. The effects of nano-sized aluminum (nAl) on the rheological properties of metal/HTPB slurries and fuel rich solid propellant slurries were investigated. The energetic properties (heat of combustion and density) and the hazardous properties (impact sensitivity and friction sensitivity) of propellants prepared were analyzed and the properties mentioned above compared to those of a conventiona

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Abdullah, Mohamed, F. Gholamian, and A. R. Zarei. "Noncrystalline Binder Based Composite Propellant." ISRN Aerospace Engineering 2013 (September 24, 2013): 1–6. http://dx.doi.org/10.1155/2013/679710.

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This study reports on propellants based on cross-linked HTPE binder plasticized with butyl nitroxyethylnitramine (BuNENA) as energetic material and HP 4000D as noncrystalline prepolymer. This binder was conducted with solid loading in the 85%. The results showed an improvement in processability, mechanical properties and burning rate. In addition, its propellant delivers (about 6 seconds) higher performance (specific impulse) than the best existing composite solid rocket propellant. Thermal analyses have performed by (DSC, TGA). The thermal curves have showed a low glass transition temperature

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Adeniyi, Gbadebo Omoniyi, Inkechukwu Nkere, Lanre Moshood Adetoro, and Olusegun Samuel Sholiyi. "Performance Analysis of a Dual-Fuel Sugar Based Solid Rocket Propellant." European Journal of Engineering and Technology Research 6, no. 2 (2021): 34–41. http://dx.doi.org/10.24018/ejers.2021.6.2.2347.

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The effects of dual-fuel on improving the ballistic efficiency of a low energy sugar-based solid rocket propellant were investigated in this paper. This was achieved by establishing a threshold proportion of sucrose to sorbitol that provided the highest ballistic efficiency, using a beam load cell (model single-point 2,000 kg linearly defined by 0-20 kN force, with ±.005 percent precision). Seven different propellant formulations were prepared, loaded into the rocket motor and tested for performance. The major performance parameters of interest were the thrust, total impulse, burn time, delive

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Adeniyi, Gbadebo Omoniyi, Inkechukwu Nkere, Lanre Moshood Adetoro, and Olusegun Samuel Sholiyi. "Performance Analysis of a Dual-Fuel Sugar Based Solid Rocket Propellant." European Journal of Engineering and Technology Research 6, no. 2 (2021): 34–41. http://dx.doi.org/10.24018/ejeng.2021.6.2.2347.

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The effects of dual-fuel on improving the ballistic efficiency of a low energy sugar-based solid rocket propellant were investigated in this paper. This was achieved by establishing a threshold proportion of sucrose to sorbitol that provided the highest ballistic efficiency, using a beam load cell (model single-point 2,000 kg linearly defined by 0-20 kN force, with ±.005 percent precision). Seven different propellant formulations were prepared, loaded into the rocket motor and tested for performance. The major performance parameters of interest were the thrust, total impulse, burn time, delive

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35

Junqueira Pimont, Lia, Paula Cristina Gomes Fernandes, Luiz Fernando de Araujo Ferrão, Marcio Yuji Nagamachi, and Kamila Pereira Cardoso. "Study on the Mechanical Properties of Solid Composite Propellant Used as a Gas Generator." Journal of Aerospace Technology and Management, no. 1 (January 21, 2020): 7–10. http://dx.doi.org/10.5028/jatm.etmq.65.

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A gas generating propellants are used as initiators of liquid rocket propellants turbopumps and have as desired characteristic a high-volume production of low-temperature gas. In this context, some formulations of composite propellant containing polyurethane (based on liquid hydroxyl-terminated polybutadiene), guanidine nitrate, ammonium perchlorate, and additives were evaluated and characterized in order to verify their potential as gas generator propellant, as well as to evaluate the influence of additives on mechanical properties. The formulations were prepared, analyzed, and tested for mec

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Tigga, Anish Soloman, Murali G., and Masthan Vali P.S.N. "Investigation on solid propellant test and time calibration for complete combustion." E3S Web of Conferences 391 (2023): 01097. http://dx.doi.org/10.1051/e3sconf/202339101097.

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A solid propellant is simple and reliable rocket fuel. Once ignited, the propellant cannot be stopped since they burn until they run out. Solid fuel rockets are widely used in military applications such as missiles, model rockets, boosters for satellite launchers and so on because they can be stored for long periods of time without degrading the propellant. The primary objective of this research is to study the burnout mass of solid propellants using various propellants and catalysts. Potassium Nitrate (KNO3) was chosen as an oxidant in the experiment because of its compatibility with other in

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Xiong, Weiqiang, Yunjie Liu, Tianfu Zhang, et al. "Effect of Al–Li Alloy on the Combustion Performance of AP/RDX/Al/HTPB Propellant." Aerospace 10, no. 3 (2023): 222. http://dx.doi.org/10.3390/aerospace10030222.

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Aluminium–lithium alloy (Al–Li alloy) powder has excellent ignition and combustion performance. The combustion product of Al–Li alloy powder combined with ammonium perchlorate is gaseous at the working temperature of solid rocket motors, which greatly reduces the loss of two-phase flow. Experimental investigations were thoroughly conducted to determine the effect of the Al–2.5Li (2.5 wt% lithium) content on propellant combustion and agglomeration based on thermogravimetry-differential scanning calorimetry, heat combustion, laser ignition, combustion diagnosis, a simulated 75 mm solid rocket mo

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Madi, V. V. "Mathematical simulation of rocket engine with a composite sectional charge." Journal of «Almaz – Antey» Air and Space Defence Corporation, no. 3 (September 30, 2016): 36–40. http://dx.doi.org/10.38013/2542-0542-2016-3-36-40.

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Due to the need to improve the appearance of the solid-propellant rocket engine, we stated the task of developing the methods allowing us to calculate internal ballistics performance of a composite sectional charge of solid propellant. These methods were implemented on a computer in the mathematical package MathCAD Prime 3.0, it has accuracy that is sufficient for technical evaluation of the rocket engine using solid propellant with the sectional charge.

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Hindman, Edward E., and William G. Finnegan. "Will Space Shuttle Launch Clouds be an Important Source of Ice Nuclei?" Journal of Weather Modification 14, no. 1 (2012): 75–77. http://dx.doi.org/10.54782/jwm.v14i1.71.

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Laboratory and field measurements demonstrate that combustion aerosol from solid rocket motor propellants contain ice nuclei. The measurements indicate an activity at -20°C of about 10^10 nuclei per gram of propellant. When this activity is applied to the 10^9 grams of propellant burned each space shuttle launch and the planned frequent launches are considered, shuttle launch clouds should be an important source of ice nuclei.

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Chen, Jiazhao, Xueren Wang, and Chunguo Yue. "Comparison Analysis of Modes Before and After Liquid Rocket Filling." International Journal of Mechanical and Electrical Engineering 3, no. 1 (2024): 31–39. http://dx.doi.org/10.62051/ijmee.v3n1.05.

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Taking the two-stage liquid rocket as an example, we use the ANSYS calculation software to consider the fluid-solid coupling after propellant filling, calculate the modes under the first and last two conditions of propellant filling, and obtain the first 20 natural frequency and vibration pattern of the liquid rocket, which provide reference for the safe use of the target range. The calculation results show that the natural frequency of the liquid rocket system decreases after propellant filling compared with that before filling, the modes of order 1 and 2 are low frequency vibration, the natu

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Sun, Shixiong, Benbo Zhao, Yuan Cheng, and Yunjun Luo. "Research on Mechanical Properties and Sensitivity of a Novel Modified Double-Base Rocket Propellant Plasticized by Bu-NENA." Materials 15, no. 18 (2022): 6374. http://dx.doi.org/10.3390/ma15186374.

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The research and development of rocket propellants with a high solid content and superior mechanical and security performance is urgently needed. In this paper, a novel extruded modified double-base (EMDB) rocket propellant plasticized by N-butyl-N-nitratoethyl nitramine (Bu-NENA) was prepared to overcome this challenge. The results indicated that Bu-NENA decreased the mechanical sensitivity successfully, contributing to the mechanical properties against traditional nitroglycerin (NG) based EMDB propellants, while hexogen (RDX), which is beneficial to propellant energy, was not conducive to th

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He, Kai-le, and Xiao-chun Xue. "Cook-off Characteristics of Solid Rocket Motor with AP/HTPE Propellant Charge." Journal of Physics: Conference Series 2478, no. 3 (2023): 032014. http://dx.doi.org/10.1088/1742-6596/2478/3/032014.

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Abstract Conducting thermal safety research on solid rocket motors is a method to effectively improve the battlefield survivability of rockets and missile weapons. Based on the AP-based cock-off reaction mechanism, a 2-D unsteady axial symmetrical model of solid rocket motor is developed. The software Fluent is used to calculate the numerical value of the rocket motor under thermal stimulation conditions of different heating rates. The results indicate that the heating rate of cook-off is negatively correlated with the ignition delay time of the motor, and there is no significant connection be

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Man’ko, Tamara Antonovna, and Kristina Viktorovna Коzis. "THE ISSUES OF CHEMISTRY AND TECHNOLOGIES OF RESIN MIXTURES FABRICATION FOR INTERNAL HEAT-PROTECTIVE COATING OF ROCKET SOLID FUEL ENGINE." Journal of Rocket-Space Technology 27, no. 4 (2019): 13–20. http://dx.doi.org/10.15421/451903.

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One of specific features of rocket engineering – is the high rate of sophistication and renewal of structures due to constantly growing operational and technical specifications imposed to them. Every generation of rocket and space products features a new complex of design and processing parameters and new materials possessing higher properties. It is impossible to resolve the entire scope of design and processing tasks in course of development, creation and operation of spacecraft without extend development and infusion of new materials which possess a number of required characteristics impose

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Shangguan, Zihan, Jian Zheng, and Liangcheng Sun. "Analysis of the mechanical response of solid rocket engine propellant under acceleration shock." Journal of Physics: Conference Series 2764, no. 1 (2024): 012098. http://dx.doi.org/10.1088/1742-6596/2764/1/012098.

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Abstract The increased-range solid rocket engine of new ammunition often needs to withstand extremely high acceleration overload, leading to damage to the propellant’s structural integrity. To address this issue, this paper constructs a nonlinear viscoelastic constitutive model for the CMDB propellant by using low- and high-strain rate mechanical property tests. Combined with the secondary development of explicit dynamics and numerical simulation technology, the mechanical response of a certain type of solid rocket propellant under different acceleration impacts is analyzed. The results show t

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Kravchuk, I. S., D. V. Bashynskyi, V. V. Taranenko, and M. V. Zirka. "Flight Range Extension of a Guided Aerial Bomb with a Rocket Engine during Climb Bombing." Advances in Military Technology 16, no. 2 (2021): 265–76. http://dx.doi.org/10.3849/aimt.01462.

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The possibility of a significant flight range extension of a guided aerial bomb during climb bombing due to the jet thrust created by a solid-propellant rocket engine was considered. By means of simulation, a comparative analysis of the range of a guided aerial bomb equipped (not equipped) with a solid-propellant rocket engine under typical flight conditions of the carrier aircraft during level flight and climb bombing was performed. It was demonstrated that the use of a solid-propellant rocket engine, whose mass is 20 % of the guided aerial bomb’s mass, allows to increase the horizontal range

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Glascock, Matthew S., Joshua L. Rovey, and Kurt A. Polzin. "Impulse and Performance Measurements of Electric Solid Propellant in a Laboratory Electrothermal Ablation-Fed Pulsed Plasma Thruster." Aerospace 7, no. 6 (2020): 70. http://dx.doi.org/10.3390/aerospace7060070.

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Electric solid propellants are advanced solid chemical rocket propellants that can be controlled (ignited, throttled and extinguished) through the application and removal of an electric current. This behavior may enable the propellant to be used in multimode propulsion systems utilizing the ablative pulsed plasma thruster. The performance of an electric solid propellant operating in an electrothermal ablation-fed pulsed plasma thruster was investigated using an inverted pendulum micro-newton thrust stand. The impulse bit and specific impulse of the device using the electric solid propellant we

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Holler, Marcel, Guenter Mussbach, Alexander Weigand, et al. "COPING WITH SPACE ENVIRONMENT: TESTING SOLID PROPELLANTS FOR IN-ORBIT USE." International Journal of Energetic Materials and Chemical Propulsion 22, no. 5 (2023): 45–66. http://dx.doi.org/10.1615/intjenergeticmaterialschemprop.v22.i5.30.

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The results of a risk reduction study are presented, proving the suitability of solid rocket motors (SRMs) to de-orbit satellites at the end of their lifetime. In a risk reduction program, three basic unexplored questions regarding this technological approach were investigated: (1) what are the effects of the size and type of particles ejected during the operation of SRMs; (2) what is the effect of the micrometeoroid impact on the solid propellant; and (3) what are the effects of prolonged exposure to space radiation during the 20-year expected satellite lifetime of satellites? Using a series

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Лазарева, Ю. И., С. В. Клименко, А. В. Кулик та И. В. Лазарев. "АНАЛИЗ СОВРЕМЕННОГО СОСТОЯНИЯ И ПЕРСПЕКТИВЫ РАЗВИТИЯ РАКЕТНЫХ ДВИГАТЕЛЕЙ ДЛЯ ИССЛЕДОВАНИЯ ДАЛЬНЕГО КОСМОСА". System design and analysis of aerospace technique characteristics 27, № 2 (2022): 50–58. http://dx.doi.org/10.15421/471923.

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The article analyzes the current state and development prospects of rocket engines for space exploration. Currently, for flights to other planets, not to mention the stars, the use of liquid-propellant and solid-propellant rocket engines is becoming increasingly unprofitable, although many rocket engines have been developed. Thus, to reach manned planes even the nearest planets, it is necessary to develop rocket launchers on engines operating on principles different from chemical propulsion systems. The most promising in this regard are electric, laser and nuclear rocket engines, as well as hy

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Bergman, Yoel. "THE NEW 1942 METHOD FOR PROPELLANT DESIGN AND LATER UPDATES." Journal of the International Committee for the History of Technology 28, no. 2 (2023): 128–35. http://dx.doi.org/10.11590/icon.2023.2.07.

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The brief research reviews the history of an innovative method in propellant technology. In 1942, the renowned US scientist Joseph Hirschfelder led a team that devised a simple calculative method for helping to design wartime solid propellants, whose gas, when burnt, served to drive projectiles in gun barrels. The method estimated the temperature of the gas for each propellant and other factors. Until then, these were estimated through a rigorous theoretical process. The simplified theoretical approach of the new method gave nearly the same temperatures and other important values, all with bas

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Miszczak, Maciej. "POLISH DISCLOSED SECRET PATENTS ON TECHNOLOGY OF SOLID, HETEROGENEOUS ROCKET PROPELLANTS." PROBLEMY TECHNIKI UZBROJENIA 160, no. 2 (2022): 119–35. http://dx.doi.org/10.5604/01.3001.0015.9901.

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Results of search and analysis of Polish disclosed secret patents on manufacture technology of solid, heterogeneous rocket propellants, were presented. As a result of this search, fifteen patent descriptions of inventions were found. These inventions were applied as secret ones to the Polish Patent Office in years 1963-1997. Information pieces about their disclosure, i.e. about removing secrecy from them, were published in the announcements of the News of the Polish Patent Office issued in years 2007-2017. Main topics of these inventions related to the ways of obtainment of compositions and ch

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