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Journal articles on the topic 'HTPB propellants'

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Author: Grafiati
Published: 10 December 2022
Last updated: 28 January 2023

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1

Kohga, Makoto, Tomoki Naya, and Kayoko Okamoto. "Burning Characteristics of Ammonium-Nitrate-Based Composite Propellants with a Hydroxyl-Terminated Polybutadiene/Polytetrahydrofuran Blend Binder." International Journal of Aerospace Engineering 2012 (2012): 1–9. http://dx.doi.org/10.1155/2012/378483.

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Ammonium-nitrate-(AN-) based composite propellants prepared with a hydroxyl-terminated polybutadiene (HTPB)/polytetrahydrofuran (PTHF) blend binder have unique thermal decomposition characteristics. In this study, the burning characteristics of AN/HTPB/PTHF propellants are investigated. The specific impulse and adiabatic flame temperature of an AN-based propellant theoretically increases with an increase in the proportion of PTHF in the HTPB/PTHF blend. With an AN/HTPB propellant, a solid residue is left on the burning surface of the propellant, and the shape of this residue is similar to that of the propellant. On the other hand, an AN/HTPB/PTHF propellant does not leave a solid residue. The burning rates of the AN/HTPB/PTHF propellant are not markedly different from those of the AN/HTPB propellant because some of the liquefied HTPB/PTHF binder cover the burning surface and impede decomposition and combustion. The burning rates of an AN/HTPB/PTHF propellant with a burning catalyst are higher than those of an AN/HTPB propellant supplemented with a catalyst. The beneficial effect of the blend binder on the burning characteristics is clarified upon the addition of a catalyst. The catalyst suppresses the negative influence of the liquefied binder that covers the burning surface. Thus, HTPB/PTHF blend binders are useful in improving the performance of AN-based propellants.
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2

Lin, Yi-Hsien, Tsung-Mao Yang, Jin-Shuh Li, Kai-Tai Lu, and Tsao-Fa Yeh. "Preliminary Study on Characteristics of NC/HTPB-Based High-Energy Gun Propellants." ChemEngineering 6, no. 5 (October 10, 2022): 80. http://dx.doi.org/10.3390/chemengineering6050080.

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This study mainly explored the characteristics of NC/HTPB-based high-energy gun propellants with RDX, CL-20 or TKX-50 by experimental method. Three series of test samples were prepared referring to the formulation of M1 single-base gun propellant (M1 SBP). The thermochemical characteristics, chemical stability, explosion heat, impact and friction sensitivities of prepared samples were determined by simultaneous differential scanning calorimetry–thermogravimetric analysis (STA DSC–TGA), vacuum stability tester (VST), bomb calorimeter (BC), BAM fallhammer and BAM friction tester, respectively, and compared with those of the reference sample M1. The experimental results indicated that the thermochemical characteristics of NC/HTPB-based high-energy gun propellants were similar to those of M1 SBP. The NC/HTPB-based high-energy gun propellants had good chemical stability and were superior to M1 SBP. The explosion heat of NC/HTPB-based high-energy gun propellants was close to and slightly larger than that of M1 SBP. In addition, the NC/HTPB-based high-energy gun propellants had lower impact and friction sensitivities than the M1 SBP. Therefore, the NC/HTPB-based high-energy gun propellants have the potential to replace the M1 SBP. The combustion performances of NC/HTPB-based high-energy gun propellants will be continuously studied and verified in the future.
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3

Dong, Ge, Hengzhi Liu, Lei Deng, Haiyang Yu, Xing Zhou, Xianqiong Tang, and Wei Li. "Study on the interfacial interaction between ammonium perchlorate and hydroxyl-terminated polybutadiene in solid propellants by molecular dynamics simulation." e-Polymers 22, no. 1 (January 1, 2022): 264–75. http://dx.doi.org/10.1515/epoly-2022-0016.

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Abstract The interfacial interaction between the main oxidant filler ammonium perchlorate (AP) and hydroxyl-terminated polybutadiene (HTPB) matrix in AP/HTPB propellants were studied via an all-atom molecular dynamics simulation. The results of the simulation showed the effects of the microscopic cross-linked structure of the matrix, stretching rate during uniaxial stretching, and contact area between the filler and matrix on the mechanical properties, such as the stress and strain of the composite solid propellant. Among the aforementioned factors, the stretching rate considerably affects the mechanical properties of the solid propellant, and the maximum stress of the solid propellant proportionally increases with the stretching rate. When defects were introduced on the surface of the AP filler, the contact area between the filler and matrix affected the strain type of the matrix molecules. Owing to the interaction between the molecules and atoms, the strain behaviour of the matrix molecule changed with the change in its microscopic cross-linked structure during uniaxial stretching. Molecular dynamics simulations were used to explore the characteristics at the AP–HTPB interface in AP/HTPB propellants. The aforementioned simulation results further revealed the interfacial interaction mechanism of the AP–HTPB matrix and provided a theoretical basis for the design of high-performance propellants.
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4

Wu, Xinzhou, Jun Li, Hui Ren, and Qingjie Jiao. "Comparative Study on Thermal Response Mechanism of Two Binders during Slow Cook-Off." Polymers 14, no. 17 (September 5, 2022): 3699. http://dx.doi.org/10.3390/polym14173699.

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The HTPE (hydroxyl-terminated polyether) propellant had a lower ignition temperature (150 °C vs. 240 °C) than the HTPB (hydroxy-terminated polybutadiene) propellant in the slow cook-off test. The reactions of the two propellants were combustion and explosion, respectively. A series of experiments including the changes of colors and the intensity of infrared characteristic peaks were designed to characterize the differences in the thermal response mechanisms of the HTPB and HTPE binder systems. As a solid phase filler to accidental ignition, the weight loss and microscopic morphology of AP (30~230 °C) were observed by TG and SEM. The defects of the propellant caused by the cook-off were quantitatively analyzed by the box counting method. Above 120 °C, the HTPE propellant began to melt and disperse in the holes, filling the cracks, which generated during the decomposition of AP at a low temperature. Melting products were called the “high-temperature self-repair body”. A series of analyses proved that the different thermal responses of the two binders were the main cause of the slow cook-off results, which were likewise verified in the propellant mechanical properties and gel fraction test. From the microscopic point of view, the mechanism of HTPE’s slow cook-off performance superior to HTPB was revealed in this article.
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5

Ji, Yongchao, Liang Cao, Zhuo Li, Guoqing Chen, Peng Cao, and Tong Liu. "Numerical Conversion Method for the Dynamic Storage Modulus and Relaxation Modulus of Hydroxy-Terminated Polybutadiene (HTPB) Propellants." Polymers 15, no. 1 (December 20, 2022): 3. http://dx.doi.org/10.3390/polym15010003.

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As a typical viscoelastic material, solid propellants have a large difference in mechanical properties under static and dynamic loading. This variability is manifested in the difference in values of the relaxation modulus and dynamic modulus, which serve as the entry point for studying the dynamic and static mechanical properties of propellants. The relaxation modulus and dynamic modulus have a clear integral relationship in theory, but their consistency in engineering practice has never been verified. In this paper, by introducing the “catch-up factor λ” and “waiting factor γ”, a method for the inter-conversion of the dynamic storage modulus and relaxation modulus of HTPB propellant is established, and the consistency between them is verified. The results show that the time region of the calculated conversion values of the relaxation modulus obtained by this method covers 10−8–104 s, spanning twelve orders of magnitude. Compared to that of the relaxation modulus (10−4–104 s, spanning eight orders of magnitude), an expansion of four orders of magnitude is achieved. This enhances the expression ability of the relaxation modulus on the mechanical properties of the propellant. Furthermore, when the conversion method is applied to the dynamic–static modulus conversion of the other two HTPB propellants, the results show that the correlation coefficient between the calculated and measured conversion values is R2 > 0.933. This proves the applicability of this method to the dynamic–static modulus conversion of other types of HTPB propellants. It was also found that λ and γ have the same universal optimal value for different HTPB propellants. As a bridge for static and dynamic modulus conversion, this method greatly expands the expression ability of the relaxation modulus and dynamic storage modulus on the mechanical properties of the HTPB propellant, which is of great significance in the research into the mechanical properties of the propellant.
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6

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 (November 5, 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 conventional aluminized (micro-Al, mAl) propellant. The strand burning rate and the associated combustion fl ame structure of propellants were also determined. The results show that nAl powder is nearly “round” or “ellipse” shaped, which is different from the tested micrometric Al used as a reference metal fuel. Two kinds of Al (nAl and mAl) powder can be dispersed in HTPB binder suffi ciently. The density of propellant decreases with increasing mass fraction of nAl powder; the measured heat of combustion, friction sensitivity, and impact sensitivity of propellants increase with increasing mass fraction of nAl powder in the formulation. The burning rates of fuel rich propellant increase with increasing pressure, and the burning rate of the propellant loaded with 20% mass fraction of nAl powder increases 77.2% at 1 MPa, the pressure exponent of propellant increase a little with increasing mass fraction of nAl powder in the explored pressure ranges.
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7

Dewi, Wiwiek Utami. "EVALUASI KINETIKA DEKOMPOSISI TERMAL PROPELAN KOMPOSIT AP/HTPB DENGAN METODE KISSINGER, FLYNN WALL OZAWA DAN COATS - REDFREN." Jurnal Teknologi Dirgantara 15, no. 2 (February 27, 2018): 115. http://dx.doi.org/10.30536/j.jtd.2017.v0.a2635.

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Decomposition of propellant Mechanism and kinetics have been investigated by using DTG/TA with three different methods: Kissinger, Flynn Wall Ozawa and Coats & Redfern. This research aims to determine decomposition kinetic parameters of LAPAN’s propellant. The propellants have different composition of Al and AP modal. RUM propellant consist of AP/HTPB. 450 propellant consists AP/HTPB/Al (bimodal). Meanwhile 1220 propellant consists of AP/HTPB/Al (trimoda). Thermal analysis takes place at 30 – 400oC and nitrogen atmosphere flow rate is 50 ml/min. The result according showed that propellant was decomposed by F1 mechanism (random nucleation with one nucleus on the individual particles). Activation energy of propellants are in range between 100.876 – 155.156 kJ/mol meanwhile pre-exponential factor are in range between 4.57 x 107 – 3.46 x 1012/min. Activation energy (E) as well as pre-exponential factor for 1220 propellant is the lowest among the others. AP trimodal application generates catalytic effect which decreases activation energy. 1220 propellant is easier to decompose (easier to react) than RUM and 450 propellant. AbstrakMekanisme dan kinetika dekomposisi propelan telah diinvestigasi menggunakan DTG/TA dengan tiga jenis metode yang berbeda yaitu Kissinger, Flynn Wall Ozawa dan Coats & Redfern. Penelitian ini bertujuan untuk mengetahui parameter kinetika dekomposisi propelan LAPAN. Propelan yang digunakan memiliki perbedaan komposisi Al dan jenis moda AP. Propelan RUM adalah propelan AP/HTPB. RX 450 adalah AP/HTPB/ Al (bimoda). Sementara itu, RX 1220 adalah AP/HTPB/ Al (trimoda). Pengujian termal berlangsung pada suhu 30 - 400oC dan atmosfer nitrogen berlaju alir 50 ml/menit. Hasil penelitian mengungkapkan bahwa semua jenis propelan terdekomposisi dengan mekanisme F1 (nukleasi acak dengan satu nukleus pada partikel individu). Energi aktivasi propelan berkisar antara 100,876 – 155,156 kJ/mol sementara faktor pre-eksponensial berkisar antara 4,57 x 107 – 3,46 x 1012/min. Energi aktivasi (E) dan faktor pre-eksponensial (A) RX 1220 adalah terendah dari ketiga sampel. Penggunaan jenis AP trimodul menciptakan efek katalitik yang menurunkan besarnya energi aktivasi. Propelan RX 1220 lebih mudah terdekomposisi (lebih mudah bereaksi) daripada propelan RUM dan RX 450.
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8

Wang, Qizhou, Guang Wang, Zhejun Wang, Hongfu Qiang, Xueren Wang, and Shudi Pei. "Strain-rate correlation of biaxial tension and compression mechanical properties of HTPB and NEPE propellants." AIP Advances 12, no. 5 (May 1, 2022): 055005. http://dx.doi.org/10.1063/5.0083205.

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An effective biaxial tension and compression test method is proposed based on the shortcomings of current research for the mechanical properties of solid propellants under complex stress states. The equal proportion biaxial tension and compression test of HTPB (Hydroxyl-terminated polybutadiene) and NEPE (NitrateEster Plasticized Polyether) solid propellants is performed at different rates while at room temperature, and the damage morphology of the tension–compression zone is analyzed using micro-CT. The results show that the failure mode of the solid propellant under biaxial tension and compression loading is similar to that under uniaxial tension. Meanwhile, the compressive strength is much greater than the tensile strength, which will eventually cause tensile failure. With an increased loading rate, the growth trend of the initial modulus, ultimate strength, and maximum elongation of the propellant is gradually flattened, and the damage degree is gradually reduced. Additionally, damage that forms in the HTPB propellant is from dewetting and particle fracture while that for the NEPE propellant is from matrix tearing. The porosity can be used as the meso-damage parameter of the propellant.
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9

Chaturvedi, Shalini, and Pragnesh N. Dave. "Solid propellants: AP/HTPB composite propellants." Arabian Journal of Chemistry 12, no. 8 (December 2019): 2061–68. http://dx.doi.org/10.1016/j.arabjc.2014.12.033.

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10

Xie, Zhi Min, Si Chi Chen, and You Shan Wang. "Relaxation Properties of the Solid Propellant Based on Hydroxyl-Terminated Polybutadiene." Advanced Materials Research 989-994 (July 2014): 172–76. http://dx.doi.org/10.4028/www.scientific.net/amr.989-994.172.

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The polymer-based propellant is a typical viscoelastic material. Better understanding of the relaxation properties of the propellant in the storage conditions is of great importance for predicting the lifetime. Due to the component complexity of the composite propellants, the transformation relation between the relaxation modulus and the complex modulus may not be suitable for all kinds of propellants. In the present work, we focused on the transformation of the relaxation modulus and complex modulus for the HTPB propellant. The master curves for the relaxation modulus and the storage modulus of the aged/unaged HTPB propellants were obtained by performing the stress relaxation tests and DMA tests, respectively. It was found that there existed a great difference in the double logarithmic plot between relaxation modulus and storage modulus master curves. Moreover, the testing results for the relaxation modulus and the storage modulus were well fitted by an empirical transformation relation with three segment-related coefficients. These three coefficients were determined by using the unaged samples, and then were applied to estimate the relaxation modulus of the aged samples. A good agreement between the calculation and the experimental results was also found, revealing that the three coefficients were insensitive to the aging time.
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11

Abd-Elghany, Mohamed, Thomas M. Klapötke, and Ahmed Elbeih. "Environmentally safe (chlorine-free): new green propellant formulation based on 2,2,2-trinitroethyl-formate and HTPB." RSC Advances 8, no. 21 (2018): 11771–77. http://dx.doi.org/10.1039/c8ra01515e.

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12

Hoque, Ehtasimul, Chandra Shekhar Pant, and Sushanta Das. "Study on Friction Sensitivity of Passive and Active Binder based Composite Solid Propellants and Correlation with Burning Rate." Defence Science Journal 70, no. 2 (March 9, 2020): 159–65. http://dx.doi.org/10.14429/dsj.70.14802.

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Friction sensitivity of composite propellants and their ingredients is of significant interest to mitigate the risk associated with the accidental initiation while processing, handling, and transportation. In this work, attempts were made to examine the friction sensitivity of passive binder: Hydroxy Terminated Polybutadiene/Aluminium/Ammonium Perchlorate and active binder: (Polymer + Nitrate Esters)/Ammonium Perchlorate/Aluminium/Nitramine based composite propellants by using BAM Friction Apparatus. As per the recommendation of NATO standard STANAG–4487, the friction sensitivity was assessed by two methods: Limiting Frictional load and Frictional load for 50% probability of initiation (F50). The test results showed that the active binder based formulations were more vulnerable to frictional load as compared to the formulations with passive binders. Examination of a comprehensive set of propellant compositions revealed that the particle size distribution of Ammonium Perchlorate and burn rate catalysts were the most influential factors in dictating the friction sensitivity for HTPB/Al/AP composite propellants. For active binder/AP/Al/Nitramine composite propellants, the formulation with RDX was found more friction sensitive with a sensitivity value of 44 N as compared to its HMX analog (61 N). The correlation studies of friction sensitivity, burning rate, and thermal decomposition characteristics of HTPB/Al/AP composite propellants is described.
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13

Rosita, Geni. "RETIKULASI HIDROXYL TERMINATED POLUBUTADIENE (HTPB) MANDIRI DENGAN TOLUENE DIISOCIANATE (TDI) MEMBENTUK POLIURETAN SEBAGAI FUEL BINDER PROPELAN." Jurnal Teknologi Dirgantara 14, no. 1 (July 22, 2016): 51. http://dx.doi.org/10.30536/j.jtd.2016.v14.a2567.

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LAPAN has successfully made HTPB independently. The next stage is to manufacture fuel-binder by reacting the HTPB with TDI. Stages of this test to get the gel time and the hardness that can qualify as a propellant binder. In this research HTPB:TDI reacted in some ratio, and HTPB are treated differently on the viscosity and average molecular weight. From some of the compositions of the reaction, which can be used as a propellant fuel binder are that meet several criteria, among others, there are no air bubbles, elastic, non-sticky for easy process, not hard and not brittle so that the propellant is not easy to crack. Observations during the gel time, which can be used as fuel binder composition propellants are HTPB:TDI are 6:1, 7:1, 8:1 and 9:1. Thus, the self-developed HTPB can already be used as a fuel binder in the manufacture of composite propellant. Abstrak LAPAN telah berhasil membuat HTPB secara mandiri. Tahapan berikutnya adalah melakukan pembuatan fuel binder dengan mereaksikan HTPB mandiri tersebut dengan TDI. Tahapan uji ini untuk mendapatkan gel time dan kekerasan yang dapat memenuhi syarat sebagai binder propelan. Pada penelitian ini dilakukan reaksi HTPB : TDI pada beberapa perbandingan, dan HTPB yang direaksikan berbeda pada viskositas dan berat molekul reratanya. Dari beberapa komposisi hasil reaksi, yang dapat digunakan sebagai fuel binder propelan adalah yang memenuhi beberapa kriteria, antara lain tidak ada gelembung udara, elastis, tidak lengket untuk memudahkan pencetakan, tidak keras dan tidak getas supaya propelan tidak mudah retak. Hasil pengamatan selama gel time, yang dapat digunakan sebagai fuel binder propelan adalah komposisi HTPB:TDI, 6:1, 7:1, 8:1 dan 9:1. Dengan demikian maka HTPB mandiri yang dikembangkan sudah dapat digunakan sebagai fuel binder pada pembuatan propelan komposit.
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14

Rosita, Geni. "RETIKULASI HIDROXYL TERMINATED POLUBUTADIENE (HTPB) MANDIRI DENGAN TOLUENE DIISOCIANATE (TDI) MEMBENTUK POLIURETAN SEBAGAI FUEL BINDER PROPELAN." Jurnal Teknologi Dirgantara 14, no. 1 (March 19, 2018): 51. http://dx.doi.org/10.30536/j.jtd.2016.v14.a2947.

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LAPAN has successfully made HTPB independently. The next stage is to manufacture fuelbinder by reacting the HTPB with TDI. Stages of this test to get the gel time and the hardness that can qualify as a propellant binder. In this research HTPB:TDI reacted in some ratio, and HTPB are treated differently on the viscosity and average molecular weight. From some of the compositions of the reaction, which can be used as a propellant fuel binder are that meet several criteria, among others, there are no air bubbles, elastic, non-sticky for easy process, not hard and not brittle so that the propellant is not easy to crack. Observations during the gel time, which can be used as fuel binder composition propellants are HTPB:TDI are 6:1, 7:1, 8:1 and 9:1. Thus, the self-developed HTPB can already be used as a fuel binder in the manufacture of composite propellant. ABSTRAKLAPAN telah berhasil membuat HTPB secara mandiri. Tahapan berikutnya adalah melakukan pembuatan fuel binder dengan mereaksikan HTPB mandiri tersebut dengan TDI. Tahapan uji ini untuk mendapatkan gel time dan kekerasan yang dapat memenuhi syarat sebagai binder propelan. Pada penelitian ini dilakukan reaksi HTPB : TDI pada beberapa perbandingan, dan HTPB yang direaksikan berbeda pada viskositas dan berat molekul reratanya. Dari beberapa komposisi hasil reaksi, yang dapat digunakan sebagai fuel binder propelan adalah yang memenuhi beberapa kriteria, antara lain tidak ada gelembung udara, elastis, tidak lengket untuk memudahkan pencetakan, tidak keras dan tidak getas supaya propelan tidak mudah retak. Hasil pengamatan selama gel time, yang dapat digunakan sebagai fuel binder propelan adalah komposisi HTPB:TDI, 6:1, 7:1, 8:1 dan 9:1. Dengan demikian maka HTPB mandiri yang dikembangkan sudah dapat digunakan sebagai fuel binder pada pembuatan propelan komposit.
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15

Vorozhtsov, Alexander, Marat Lerner, Nikolay Rodkevich, Sergei Sokolov, Elizaveta Perchatkina, and Christian Paravan. "Preparation and Characterization of Al/HTPB Composite for High Energetic Materials." Nanomaterials 10, no. 11 (November 8, 2020): 2222. http://dx.doi.org/10.3390/nano10112222.

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Nanosized Al (nAl) powders offer increased reactivity than the conventional micron-sized counterpart, thanks to their reduced size and increased specific surface area. While desirable from the combustion viewpoint, this high reactivity comes at the cost of difficult handling and implementation of the nanosized powders in preparations. The coating with hydroxyl-terminated polybutadiene (HTPB) is proposed to improve powder handling and ease of use of nAl and to limit its sensitivity to aging. The nAl/HTPB composite can be an intermediate product for the subsequent manufacturing of mixed high-energy materials while maintaining the qualities and advantages of nAl. In this work, experimental studies of the high-energy mixture nAl/HTPB are carried out. The investigated materials include two composites: nAl (90 wt.%) + HTPB (10 wt.%) and nAl (80 wt.%) + HTPB (20 wt.%). Thermogravimetric analysis (TGA) is performed from 30 to 1000 °C at slow heating rate (10 °C/min) in inert (Ar) and oxidizing (air) environment. The combustion characteristics of propellant formulations loaded with conventional and HTPB-coated nAl are analyzed and discussed. Results show the increased burning rate performance of nAl/HTPB-loaded propellants over the counterpart loaded with micron-sized Al.
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16

Tang, Yuqing, Hanyu Deng, Tenghui Liao, and Yingjian Qi. "Research on the vacuum aging performance of HTPB propellant based on the DSC method." Journal of Physics: Conference Series 2403, no. 1 (December 1, 2022): 012013. http://dx.doi.org/10.1088/1742-6596/2403/1/012013.

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Abstract The space environment has extreme conditions such as high vacuum and rapid temperature changes, which will lead to problems such as energy drop, irregular burning rate, and abnormal ignition of solid propellants. To obtain the space aging law of HTPB propellant, the aging performance of HTPB (hydroxyl-terminated polybutadiene) propellant in a vacuum environment was studied and compared with that under the atmosphere. According to the DSC test results of the propellant before and after aging, the behaviors of oxidative crosslinking, chain-scission degradation, and oxidant decomposition during the aging process of solid propellant were investigated. The research showed that the low-temperature endothermic peak and “V-type” high-temperature exothermic peak temperature of HTPB propellant increased after aging, and the high-temperature peak bifurcated into “W-type” double peaks. The right peak caused by the “decarboxylation” reaction was more obvious after atmospheric aging while the left peak caused by AP decomposition was remarkable after vacuum aging. In addition, the oxidative crosslinking reaction occurred after aging, and the activation energy characterized by low-temperature peaks continued to increase. In the later stage of atmospheric aging, chain-scission degradation occurred due to OA moisture absorption, and the activation energy decreased. It firstly increased by 126% within 93 days, and then decreased by 23.4%. No degradation and chain-scission reaction occurred in a vacuum environment, the crosslinking reaction rate was high, and the activation energy increased by 40.4% within 49 days. After the aging of the HTPB propellant, the internal AP decomposed, and the activation energy characterized by the high-temperature exothermic right peak continued to increase. The activation energy increased by 40.5% within 49 days after vacuum aging, and increased by 29.9% within 93 days after atmospheric aging, indicating that the decomposition of AP in the HTPB propellant was more obvious under a vacuum environment.
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17

van der Heijden, A. E. D. M., H. L. J. Keizers, and W. H. M. Veltmans. "HNF/HTPB BASED COMPOSITE PROPELLANTS." International Journal of Energetic Materials and Chemical Propulsion 5, no. 1-6 (2002): 587–96. http://dx.doi.org/10.1615/intjenergeticmaterialschemprop.v5.i1-6.610.

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18

Bekhouche, Slimane, and Yun Jun Luo. "Research of Formulation and Processing of Hydroxyl-Terminated Polybutadiene (HTPB) Propellants." Advanced Materials Research 1030-1032 (September 2014): 155–60. http://dx.doi.org/10.4028/www.scientific.net/amr.1030-1032.155.

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Solid composite propellants are extensively used for propulsion of rockets, missiles and space applications. The composite propellant is a polymeric matrix in which the oxidizer and fuel particles are embedded in a polymeric binder. Different composite propellant mixtures have been prepared using ammonium-perchlorate (ratio 70:30) as oxidant and mixture of aluminium powder (ratio 50:50) as metal component. In the present work, RDX (Cyclotrimethylene trinitramine) has been used in successive increments replacing AP (Ammonium Perchlorate) in number of batches by varying the percentage of solid loading, and studied their different properties such as viscosity build-up, mechanical and ballistic properties.
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19

Traissac, Y., J. Ninous, R. Neviere, and J. Pouyet. "Mechanical Behavior of a Solid Composite Propellant during Motor Ignition." Rubber Chemistry and Technology 68, no. 1 (March 1, 1995): 146–57. http://dx.doi.org/10.5254/1.3538726.

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Abstract In order to understand the behavior of composite propellants during motor ignition, a particular study about mechanical and ultimate properties of a Hydroxy-Terminated Polybutadiene (HTPB) filled propellant under superimposed hydrostatic pressure was carried out. The mechanical response of the propellant was obtained for uniaxial tensile and simple shear tests at various temperatures, strain rates and superimposed pressures from atmospheric pressure to 15 MPa. The experimentally observed ultimate properties were found to be strongly pressure sensitive and the data were formalized in a specific stress failure criterion.
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20

Yang, Yi, Xinjie Yu, Jun Wang, and Yaxue Wang. "Effect of the Dispersibility of Nano-CuO Catalyst on Heat Releasing of AP/HTPB Propellant." Journal of Nanomaterials 2011 (2011): 1–5. http://dx.doi.org/10.1155/2011/180896.

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Kneading time is adjusted to change the dispersibility of nano-CuO in AP/HTPB (Ammonia Perchlorate/Hydroxyl-Terminated Polybutadiene) composite propellants. Nano-CuO/AP is prepared to serve as the other dispersing method of nano-CuO, named predispersing procedure. Several kinds of heat releasing, thermal decomposition by DSC, combustion heat in oxygen environment, and explosion heat in nitrogen environment, are characterized to learn the effect of dispersibility of nano-CuO catalyst on heat releasing of propellants. With pre-dispersing procedures, thermal decomposition temperature of nano-CuO/AP and its propellant are about C and C lower than that of AP simple mixed with nano-CuO and its propellant, respectively. Comparing propellant with simple mixed nano-CuO kneading 3 hours, combustion heat and explosion heat of propellant with nano-CuO/AP increase about 1.4% and 1.7%, respectively. However, because of the breaking of nano-CuO/AP structure during kneading procedure, combustion heat and explosion heat of all the samples are decreased with the increase of kneading time after 3 hours.
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21

Yao, Er Gang, Feng Qi Zhao, Si Yu Xu, Rong Zu Hu, Hui Xiang Xu, and Hai Xia Hao. "Combustion Characteristics of Composite Solid Propellants Containing Different Coated Aluminum Nanopowders." Advanced Materials Research 924 (April 2014): 200–211. http://dx.doi.org/10.4028/www.scientific.net/amr.924.200.

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Aluminum nanopowders coated with oleic acid (nmAl+OA), perfluorotetradecanoic acid (nmAl+PA) and nickel acetylacetonate (nmAl+NA) were prepared. The combustion characteristics of hydroxyl terminated polybutadiene (HTPB) composite solid propellants containing different coated aluminum nanpowders were investigated. The result shows that the burning rate of the propellant sample containing nmAl+NA is the highest at different pressure, the maximum burning rate is up to 26.13 mm·s-1at 15 MPa. The burning rates of propellant samples containing nmAl+OA and nmAl+PA are almost the same at different pressures, and higher than the propellant samples containing untreated aluminum nanopowders only at the pressure range of 10 ~ 15 MPa. The flame brightness of different propellants under different pressure is not the same. The flame brightness is increased with the pressure increasing. The flame center zone brightness of the propellant containing nmAl+PA and nmAl+NA is brighter under 4 MPa, and the brightness of nmAl+NA is the brightest. The surface coating of aluminum nanopowder has little effect on the combustion flame temperature of solid propellant. The burning surface temperature increases with the pressure increasing.
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Qin, Zhao, Jiang Wu, Rui Qi Shen, Ying Hua Ye, and Li Zhi Wu. "Laser-Controlled Combustion of Solid Propellant." Advanced Materials Research 884-885 (January 2014): 87–90. http://dx.doi.org/10.4028/www.scientific.net/amr.884-885.87.

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This paper describes experimental work on laser-controlled combustion of solid propellants. Combustion of AP/HTPB, including ignition, combustion, extinction and re-ignition could be controlled by CO2 laser irradiation at the back pressure of 0.1, 0.3 and 0.5 MPa in nitrogen. Burning rate of propellant increased linearly with the increasing of laser power density. Vieilles law was used here to check pressure effect to burning rate, pressure exponent under different power density (except 0.5 MW/m2) are very close to 0.17.
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23

Mukhtar, Amir, Habib Nasir, and Hizba Waheed. "Pressure-Time Study of Slow Burning Rate Ap/HTPB Based Composite Propellant by Using Closed Vessel Test (CVT)." Key Engineering Materials 778 (September 2018): 268–74. http://dx.doi.org/10.4028/www.scientific.net/kem.778.268.

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The Closed vessel (CV) is an equipment used to study the ballistic parameters by recording burning time history, pressure buildup during the process and vivacity of the propellants. It is an apparatus which consists of strong pressure vessel, piezo-electric pressure transducers, sensors and dedicated software. To save time and resources this method is employed instead of dynamic firing while doing research and development of propellants. A measured amount of propellant charge is loaded in the vessel and fired remotely. Ignition is provided by the filament which ignites the black powder charge. In this study, we have used Closed Vessel Tests (CVT) for the first time for recording the ballistic parameters of slow burning composite rocket propellant. We developed a set of composite solid propellant samples containing a mixture of bimodal Ammonium Perchlorate (AP) as an oxidizer, Hydroxy-terminated Polybutadiene (HTPB) as a binder as well as fuel, Dioctyl Sebacate (DOS) as plasticizer, 1-(2-methyl) Aziridinyl Phosphine Oxide (MAPO) as bonding agent and Toluene Diisocyanate (TDI) as curator. Samples were developed by changing the solid loading percentage of bimodal AP particles. By increasing the percentage of AP, the oxidizer-fuel ratio (O/F) increases which effects the ballistic parameters. It is observed that maximum pressure and vivacity increases with increase in solid filler in the propellants. As quantity of AP increases, rate of rise of pressure also increases. CVT firing of each sample was done three times to obtain average burning time and pressure buildup history to evaluate the effect of oxidizer loadings on ballistic parameters of the composite propellant.
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Lin, Guomin, Yixue Chang, Yu Chen, Wei Zhang, Yanchun Ye, Yanwen Guo, and Shaohua Jin. "Synthesis of a Series of Dual-Functional Chelated Titanate Bonding Agents and Their Application Performances in Composite Solid Propellants." Molecules 25, no. 22 (November 16, 2020): 5353. http://dx.doi.org/10.3390/molecules25225353.

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Titanate-based bonding agents are a class of efficient bonding agents for improving the mechanical properties of composite solid propellants, a kind of special composite material. However, high solid contents often deteriorate the rheological properties of propellant slurry, which limits the application of bonding agents. To solve this problem, a series of long-chain alkyl chelated titanate binders, N-n-octyl-N, N-dihydroxyethyl-lactic acid-titanate (DLT-8), N-n-dodecyl-N, N-dihydroxyethyl-lactic acid-titanate (DLT-12), N-n-hexadecyl-N, N-Dihydroxyethyl-lactic acid-titanate (DLT-16), were designed and synthesized in the present work. The infrared absorption spectral changes of solid propellants caused by binder coating and adhesion degrees of the bonding agents on the oxidant surface were determined by micro-infrared microscopy (MIR) and X-ray photoelectron spectroscopy (XPS), respectively, to characterize the interaction properties of the bonding agents with oxidants, ammonium perchlorate (AP) and hexogen (RDX), in solid propellants. The further application tests suggest that the bonding agents can effectively interact with the oxidants and effectively improve the mechanical and rheological properties of the four-component hydroxyl-terminated polybutadiene (HTPB) composite solid propellants containing AP and RDX. The agent with longer bond chain length can improve the rheological properties of the propellant slurry more significantly, and the propellant of the best mechanical properties was obtained with DLT-12, consistent with the conclusion obtained in the interfacial interaction study. Our work has provided a new method for simultaneously improving the processing performance and rheological properties of propellants and offered an important guidance for the bonding agent design.
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Dostanic, Jasmina, Gordana Uscumlic, Tatjana Volkov-Husovic, Radmila Jancic-Heinemann, and Dusan Mijin. "The use of image analysis for the study of interfacial bonding in solid composite propellant." Journal of the Serbian Chemical Society 72, no. 10 (2007): 1023–30. http://dx.doi.org/10.2298/jsc0710023d.

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In the framework of this research, the program Image Pro Plus was applied for determining the polymer-oxidizer interactions in HTPB-based composite propellants. In order to improve the interactions, different bonding agents were used, and their efficiency was analyzed. The determination of the quantity, area and radius of non-bonded oxidizer crystals is presented. The position of formed cracks in the specimen and their area have a great influence on the mechanical properties of composite propellant. The preparation of the composite propellant in order to enable the photographing of their structure by means of stereoscopic and metallographic microscopes with the digital camera is also described as well. .
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26

Yogeshkumar, Velari, Nikunj Rathi, and P. A. Ramakrishna. "Solid Fuel rich Propellant Development for use in a Ramjet to Propel an Artillery Shell." Defence Science Journal 70, no. 3 (April 24, 2020): 329–35. http://dx.doi.org/10.14429/dsj.70.15061.

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This study describes the development of a fuel-rich propellant to be used in a solid fuel ramjet to provide active propulsion to a 155 mm artillery shell. Fuel-rich propellants consisting of aluminum, ammonium perchlorate and hydroxyl terminated polybutadiene were developed and their ballistic properties were measured to choose the appropriate fuel for the ramjet application. The attempts made were to enhance the burn rates of the propellant to provide required burn rates at lowest possible pressures in primary combustor of the ramjet. The propellant selection was done with reference of working time period of the base bleed unit, to calculate the required burn rate and corresponding pressure in primary combustor. It was observed that the fuel rich propellant of composition 35% ammonium perchlorate with 1 % Iron oxide embedded on it, 30 % mechanically activated aluminum with 10% polytetrafluoroethylene, and 25 % HTPB was found suitable for the above application. This provided the higher burn rates among all developed propellants with high pressure index of 0.58. This makes it suitable for the ramjet requiring higher burn rates at lower possible primary chamber pressures. The Young’s modulus and tensile strength of this propellant was measured to be 1.73 MPa and 0.24 MPa, respectively.
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27

Korobeinichev, Oleg P., and Alexander A. Paletsky. "Flame structure of ADN/HTPB composite propellants." Combustion and Flame 127, no. 3 (November 2001): 2059–65. http://dx.doi.org/10.1016/s0010-2180(01)00308-x.

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28

Cui, Huiru, Xuan Lv, Yurong Xu, Zhiwen Zhong, Zixiang Zhou, and Weili Ma. "A Step-by-Step Equivalent Microprediction Method for the Mechanical Properties of Composite Solid Propellants considering Dewetting Damage." International Journal of Aerospace Engineering 2022 (February 14, 2022): 1–12. http://dx.doi.org/10.1155/2022/2427463.

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Reliable prediction of the macromechanical properties of composite solid propellants in the microscale can accelerate the development of propellants with high mechanical properties. According to the characteristics of the composition ratio of a four-component hydroxyl-terminated polybutadiene (HTPB) propellant with the component ammonium perchlorate (AP), hydroxyl-terminated polybutadiene, aluminum powder (AL), and cyclotrimethylenetrinitramine (or RDX for short), an improved random delivery algorithm was developed to separately model filler particles with the different sizes. A step-by-step equivalent representative volume element (RVE) model was generated to reflect the microstructures of the propellant. The isotropy and uniformity of the RVE model were also tested using a two-point probability function. The Park-Paulino-Roesler (PPR) cohesive model was introduced to simulate the particle debonding (or dewetting) in solid propellant. The stress-strain curves of the propellant were obtained by the macroscopic test with the extension rate 200 mm/min at different temperatures. Based on these experimental data, the 8 characteristic parameters suitable for the microinterface of the propellant were obtained by using an inversion optimization method. A microscale finite element prediction model of the propellant considering dewetting damage was constructed to study the evolution process of the microdamage of the propellant. The predicted stress-strain curves of the propellant under different loading conditions were in good agreement with the test results.
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29

Ajaz, A. G. "Hydroxyl-Terminated Polybutadiene Telechelic Polymer (HTPB): Binder for Solid Rocket Propellants." Rubber Chemistry and Technology 68, no. 3 (July 1, 1995): 481–506. http://dx.doi.org/10.5254/1.3538752.

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Abstract This paper presents a review of hydroxyl-terminated polybutadiene telechelic polymer (HTPB) with emphasis on its preparation, properties, end group modifications, hydrogenation, role as polyurethane precursors and binders for solid rocket propellants.
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30

Kim, Ki-Hong, Chang-Kee Kim, Ji-Chang Yoo, and Jack J. Yoh. "Test-Based Thermal Decomposition Simulation of AP/HTPB and AP/HTPE Propellants." Journal of Propulsion and Power 27, no. 4 (July 2011): 822–27. http://dx.doi.org/10.2514/1.b34099.

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31

Aziz, Amir, and Wan Khairuddin bin Wan Ali. "A Study of Basic Aluminized Propellants Characteristics." Applied Mechanics and Materials 110-116 (October 2011): 1321–27. http://dx.doi.org/10.4028/www.scientific.net/amm.110-116.1321.

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There were very limited number of references published discussing the burning characteristic of aluminized propellant without any additive substance. This paper describes the performance characteristics of basic formulations of aluminized ammonium perchlorate based propellant. Four sets of propellant formulations namely by p60, p66, p74 and p80 had been formulated and manually prepared without adding any additives. The propellant consists of ammonium perchlorate (AP) as an oxidizer, aluminum (Al) as fuel and hydroxy-terminated polybutadiene (HTPB) as fuel/binder. For each mixture, HTPB binder composition was fixed at 15% per-weight. By varying AP and Al, the effect of oxidizer-fuel (O/F) ratio on the whole propellant can be determined. The propellant strands were manufactured using press-molding method and burnt in a strand burner over a range of chamber pressure from 6 atm to 31 atm. Based on theoretical evaluation using NASA CEC71 program, p66 has been selected for testing in ballistic evaluation motor (BEM) to ascertain its characteristics performance. The results from burning rate test shows that the increasing of O/F ratio and combustion pressure lead to the increase in burning rate. The highest burning rate achieved was 12mm/sec at combustion pressure of 31atm for propellant p80 which has O/F ratio of 4.0. While for the BEM, the propellant efficiency obtained for p66 was 95.44%.
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32

Jabez, I. Kingstone Lesley, Urmila Das, R. Manivannan, and Sarat Babu Anne. "Influence of HTPB prepolymer on achieved properties of composite solid propellant." High Performance Polymers 31, no. 9-10 (February 26, 2019): 1162–72. http://dx.doi.org/10.1177/0954008319830468.

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Changes/variations during manufacturing and storage of free radical-polymerized hydroxyl-terminated polybutadiene resin/prepolymer (widely used binder for the composite solid propellants) are not reflected in terms of appreciable change in the hydroxyl value. As a result, cured properties of the propellant mixed using the given formulation finalized by keeping R ratio (NCO/OH ratio) within 0.7–0.9 did not yield predicted mechanical properties. Investigations carried out subsequently, by the authors, identified the root cause to be variations in molecular weight and its distribution, which were not indicated in terms of change in hydroxyl value. Authors confirmed their findings by 1H1NMR studies whereby the variation in molecular weight distribution could be explained in terms of variation in spin–spin relaxation time ( T 2) values.
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33

Bogusz, Rafał, Paulina Magnuszewska, and Bogdan Florczak. "STUDIES OF HIGH EXPLOSIVES IMPACT ON REDUCTION OF HCL IN HETEROGENEOUS SOLID ROCKET PROPELLANTS." PROBLEMY TECHNIKI UZBROJENIA, no. 3 (December 1, 2017): 29–45. http://dx.doi.org/10.5604/01.3001.0010.6308.

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The paper describes an influence of high explosives: hexogene (RDX), octogene (HMX), and dinitro-diaminoethene (FOX-7) on the properties of heterogeneous solid rocket propellant (HSRP) prepared on the base of Hydroxy Terminated Polybutadiene (HTPB) in which ammonium perchlorate (AP) was partially replaced by sodium nitrate (SN). It reduced the content of HCl in combustion products. Theoretical values of thermochemical and thermodynamic properties such as isochoric combustion heat (Q), specific impulse (Isp) and contents of combustion products in motor combustion chamber and nozzle have been identified by using the ICT-Code program. The rheological properties (virtual viscosity) of the propellant slurry during curing process, the sensitivity to mechanical stimuli (impact, friction), decomposition temperature, calorific value and hardness of propellants containing explosive materials were tested by instruments and ballistic properties were investigated by laboratory rocket motor (LRM).
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34

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 (January 6, 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 the Rocket Technology Research Center, ORPA-BRIN. This study uses qualitative analysis methods with research designs in the literature studies and simulation results. In the context of mastering rocket propellant technology in Indonesia, the application of highly energetic materials is expected to be able to solve the problem of rocket propulsion performance. Currently, the Rocket Technology Research Center, ORPA-BRIN is developing a smokeless propellant composite with a composition based on the energetic materials AP/HTPB/Al and an oxidizing agent RDX. From the results of the combustion simulation software ProPEP and RPA, it shows that the composition of the resulting combustion gaseous (Al2O3 and HCl) shows a decrease when using RDX energetic material-based propellant. It's known that RDX can significantly reduce smoke in propellant combustion products. The application of the new highly energetic materials compound is expected to significantly solve the problem of solid rocket propulsion performance.
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35

Baker, P. J., A. M. Mellor, and C. S. Coffey. "Critical impact initiation energies for three HTPB propellants." Journal of Propulsion and Power 8, no. 3 (May 1992): 578–85. http://dx.doi.org/10.2514/3.23517.

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36

Venugopal, S. "Combustion experiments of HTPB/RFNA mixed hybrid propellants." Indian Journal of Science and Technology 4, no. 10 (October 20, 2011): 1267–73. http://dx.doi.org/10.17485/ijst/2011/v4i10.8.

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37

Gupta, D. C., S. S. Deo, D. V. Wast, S. S. Raomore, and D. H. Gholap. "HTPB-based polyurethanes for inhibition of composite propellants." Journal of Applied Polymer Science 55, no. 8 (February 22, 1995): 1151–55. http://dx.doi.org/10.1002/app.1995.070550801.

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38

PRASUŁA, Piotr, Beata SZTEJTER, Piotr KASPRZAK, and Michał CHMIELAREK. "INCREASING THE ENERGY OF alpha, omega - DIHYDROXYPOLIBUTADIENE (HTPB) USED IN SOLID HETEROGENEOUS ROCKET PROPELLANT." PROBLEMY TECHNIKI UZBROJENIA 161, no. 3 (November 29, 2022): 37–59. http://dx.doi.org/10.5604/01.3001.0016.1154.

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Solid heterogeneous rocket propellants (SHRP), which are very popular and widely used in the armaments industry (guided missile propulsion engines and long-range, short-range and medium-range anti-aircraft rockets) have inert binders that significantly affect the final performance parameters of propulsion charges. In this study, the popular HTPB binder was modified by introducing azide groups into the polymer chain during three different syntheses. Compounds with different content of explosive groups were obtained and tested for compatibility with the essential SHRP components: ammonium chlorate(VII) and dioctyl adipate. Then, preliminary application tests of the obtained HTPB derivative were carried out, showing the potential of the obtained energetic polymer and the possibility of its use as a binder in solid heterogeneous rocket fuels. HTPB, energetic binder, azide groups
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39

Cauty, Franck, Yves Fabignon, and Charles Erades. "NEW ACTIVE BINDER-BASED PROPELLANTS: A COMPARISON WITH CLASSICAL COMPOSITE AP/HTPB PROPELLANTS." International Journal of Energetic Materials and Chemical Propulsion 12, no. 1 (2013): 1–13. http://dx.doi.org/10.1615/intjenergeticmaterialschemprop.2013005271.

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40

Pinalia, Anita, Bayu Prianto, Henny Setyaningsih, Prawita Dhewi, and Ratnawati Ratnawati. "Design of Propellant Composite Thermodynamic Properties Using Rocket Propulsion Analysis (RPA) Software." Reaktor 22, no. 1 (July 12, 2022): 1–6. http://dx.doi.org/10.14710/reaktor.22.1.1-6.

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Rocket Propulsion Analysis (RPA) is software for predicting the performance of a rocket engine. It is usually used in conceptual and preliminary design. Heat capacity and specific impulse are two properties related to the performance of a propellant. This work aimed to design AP/HTPB-based solid propellant composite with various compositions and predict the heat capacity and specific impulse using the RPA software. The materials used were ammonium perchlorate (AP) as the oxidizer, Hydroxy-Terminated Polybutadiene (HTPB) as the fuel binder, Al powder as the metal fuel, and other additives. Four propellants with different formulations were prepared and tested for heat capacity and specific impulse. The experimental heat capacity was obtained using a differential scanning calorimeter (DSC), while the specific impulse was obtained using a bomb calorimeter. The same propellant formulations were used as the input to the RPS to predict the heat capacity and specific impulse. The results show that the experimental heat capacity of the propellant ranges from 1.576 to 4.08 J g–1 K–1, and the simulation result ranges from 1.78 to 3.48 J g–1 K–1. The overall average deviation is 16.3%. The predicted specific impulse at vacuum and sea level ranges from 231.3 to 234.0 s and from 219.8 to 220.9 s, respectively. Meanwhile, the experimental specific impulse at vacuum and sea level varies from 236.2 to 240.3 s and from 228.5 to 232.9 s, respectively. The overall average deviation is 3.7%. Therefore, the RPA is reliable for predicting specific impulse of propellant, but it is not accurate enough for predicting the heat capacity of propellant composite.
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41

Araujo, Luis, and Octavia Frota. "ON THERMOCHEMICAL CHARACTERISTICS OF AP/NSAN/HTPB COMPOSITE PROPELLANTS." International Journal of Energetic Materials and Chemical Propulsion 4, no. 1-6 (1997): 118–28. http://dx.doi.org/10.1615/intjenergeticmaterialschemprop.v4.i1-6.140.

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42

Naseem, Hamza, Jyothsna Yerra, H. Murthy, and P. A. Ramakrishna. "Ageing studies on AP/HTPB based composites solid propellants." Energetic Materials Frontiers 2, no. 2 (June 2021): 111–24. http://dx.doi.org/10.1016/j.enmf.2021.02.001.

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43

Xu, Hui-Xiang, Feng-Qi Zhao, Wei-Qiang Pang, Hong-Wei Guo, Zhi-Hua Sun, and Xue-Zhong Fan. "Application Characteristics of Ammonium Dinitramide to HTPB Composite Propellants." Asian Journal of Chemistry 26, no. 13 (2014): 3995–99. http://dx.doi.org/10.14233/ajchem.2014.16516.

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44

Erişken, Cevat, Ahmet Göçmez, Ülkü Yilmazer, Fikret Pekel, and Saim Özkar. "Modeling and rheology of HTPB based composite solid propellants." Polymer Composites 19, no. 4 (August 1998): 463–72. http://dx.doi.org/10.1002/pc.10121.

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45

Désilets, Sylvain, and Sébastien Côté. "Chemical Bond Between Stabilizers and HTPB Binders in Propellants." Propellants, Explosives, Pyrotechnics 25, no. 4 (September 2000): 186–90. http://dx.doi.org/10.1002/1521-4087(200009)25:4<186::aid-prep186>3.0.co;2-b.

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46

Patil, M. S., and Haridwar Singh. "Ballistic and mechanical properties of HTPB based composite propellants." Journal of Hazardous Materials 19, no. 3 (January 1988): 271–78. http://dx.doi.org/10.1016/0304-3894(88)80026-8.

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47

Manjari, R., V. C. Joseph, L. P. Pandureng, and T. Sriram. "Structure-property relationship of HTPB-based propellants. I. Effect of hydroxyl value of HTPB resin." Journal of Applied Polymer Science 48, no. 2 (April 10, 1993): 271–78. http://dx.doi.org/10.1002/app.1993.070480211.

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48

Lee, Sunyoung, Taeha Ryu, Myungpyo Hong, and Hyoungjin Lee. "Study on the Enhancement of Burning Rate of HTPB/AP Solid Propellants." Journal of the Korean Society of Propulsion Engineers 21, no. 4 (August 1, 2017): 21–27. http://dx.doi.org/10.6108/kspe.2017.21.4.021.

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49

Krishnan, S., and R. Jeenu. "Combustion characteristics of AP/HTPB propellants with burning rate modifiers." Journal of Propulsion and Power 8, no. 4 (July 1992): 748–55. http://dx.doi.org/10.2514/3.23545.

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50

Hickman, S. R., and M. Q. Brewster. "Oscillatory Combustion of Fine-AP/HTPB Propellants: Disproportionate Pyrolysis Response." Journal of Propulsion and Power 16, no. 5 (September 2000): 867–73. http://dx.doi.org/10.2514/2.5652.

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