Base Propellant Research Articles

Effect of Various Stabilizers on the Characteristics of a Nitrate Esters-Double Base Propellant under Thermal Aging

ABSTRACT The current study examined the stabilizing effect of lignin biopolymer in comparison to traditional 2-nitrodiphenylamine (2-NDPA) and 1,3-Dimethyl-1,3-diphenylurea (C-II) stabilizers on the stability of double-base nitrocellulose (NC)/diethylene glycol dinitrate (DEGDN) propellant during artificial aging (at 338.65 K for 60 days). Various spectroscopic techniques, including Fourier Transform Infrared Spectroscopy (FTIR) and X-ray Diffraction (XRD), were used, along with traditional stability tests like the Bergmann-Junk (BJ) test and isothermal thermogravimetric analysis (TGA). Experimental results confirmed that FTIR and XRD provided valuable insights into chemical changes during aging. Particularly, lignin-stabilized NC/DEGDN exhibited comparable stability to C-II and 2-NDPA at all stages of aging, as evidenced by the amount of the released nitrous gases measured by BJ test and thermal stability assessed by TGA. Additionally, multivariate data analysis using principal component analysis (PCA) of FTIR spectra successfully differentiated between aged and unaged samples and highlighted trends in stability. Overall, the findings suggest that lignin offers a comparable stabilizing effect for NC/DEGDN propellants relative to traditional stabilizers.

Investigation of Combustion Properties Optimizing of Composite Modified Double Base Propellant Containing CL-20

Abstract The effect of combustion catalysts which are several proportions of A-Pb, A-Cu and carbon on the combustion properties of composite modified double base (CMDB) propellant containing hexanitrohexaazaisowurtzitane (CL-20) were investigated by uniform design. The proportion of the three materials is optimized. The result shows that A-Pb, A-Cu and carbon can affect the combustion properties of CL-20-CMDB propellant. The effect of single A-Pb or carbon on the propellant combustion properties is obvious between 2 MPa and 8 MPa. The effect of single A-Cu on the propellant combustion properties is obvious between 14 MPa and 22 MPa. There is positive interactions of carbon with A-Pb or A-Cu between 2 MPa and 4 MPa and A-Pb with A-Cu or carbon are obvious. The calculation shows that the effect on adjusting the combustion properties of CL-20-CMDB propellant when the proportion of A-Pb, A-Cu and carbon is 3/0.8/0.2.

Exploration of the combustion characteristic based on the pyrolysis and combustion spectral analysis of single base propellant

The pyrolysis and combustion of gunpowder are inseparable. To explore the risk characteristics of single base propellant, the pyrolysis kinetics and spectral information of single base propellant during combustion were studied in this work. Notably, with an increased heating rate, the exothermic peak shifts to higher temperatures, and the exothermic rate intensifies during the pyrolysis process, resulting in an incomplete reaction and the formation of residues. The reaction of single base propellant encompasses decomposition stage and multiple level reactions, it is phase boundary reaction mechanism. NO is generated firstly at 441.108 K and is identified as the most influential substance in facilitating the transition from pyrolysis to combustion. It causes intensified molecular chain breakage, CO, NH3, H2O, HCN, CxHy, NO, CO2 are generated. The combustion process results in the destruction of the flocculent structure and amorphous regions within single base propellant, leading to a relatively smooth particle surface, reduced porosity, and structural collapse. Moreover, the combustion optical spectrum of single base propellant has a distinct characteristic absorptions at 589 nm, 767 nm, and 770 nm, corresponding to Na and K, respectively. The spectrals can be effectively discerned within 15 ms. During the from pyrolysis to combustion of the single base propellant, the reaction mechanism, spectral band and intensity provide valuable indicators for anticipating potential accidental combustion hazards.

A comprehensive investigation of the impact of carbon-supported metal complexes of triaminoguanidine on the characteristics of a double-base propellant

ABSTRACT In this study, triaminoguanidine complexes grafted onto activated carbon (AC-TAG-Fe and AC-TAG-Co) were designed and investigated for their catalytic effect on the thermolysis of a double base propellant consisting of nitrocellulose (NC) and diethylene glycol dinitrate (DEGDN). The successful synthesis of transition metal complexes with triaminoguanidine and their subsequent grafting onto activated carbon were confirmed using various analytical techniques, including Fourier Transform Infrared Spectroscopy, Raman Spectroscopy, X-ray Diffraction, and Scanning Electron Microscopy. Thermal characterization using Thermogravimetric Analysis and Differential Scanning Calorimetry provided valuable insights into the thermal properties and reactivity of the elaborated NC/DEGDN-based composites. Importantly, the addition of various additives resulted in notable improvements in both the enthalpy of reaction and density. Isoconversional kinetic studies revealed that the incorporation of TAG-Fe and TAG-Co complexes reduced the apparent activation energy of the NC/DEGDN composite from 137.4 kJ/mol to 135.4 kJ/mol and 114.8 kJ/mol, respectively, suggesting their catalytic effect. Furthermore, it is found that the addition of activated carbon (AC) resulted in an increase in activation energy to 154 kJ/mol, whereas grafting TAG-Fe and TAG-Co complexes onto AC as a catalytic support subsequently reduced activation energy to 119 kJ/mol and 112 kJ/mol, respectively. Overall, this research serves as a valuable reference for future studies focusing on investigating the catalytic combustion characteristics of double-base solid propellants.

Post-burn and post-blast rapid detection of trace and bulk energetics by 3D-printed cone spray ionization mass spectrometry

Forensic analysis of post-blast and post-burn materials can be critical to a law enforcement or military investigation. 3D-printed cone spray ionization (3D-PCSI) coupled to a field portable mass spectrometer (MS) has been demonstrated as a rapid and low-cost alternative to traditional laboratory-based techniques (high resolution liquid or gas chromatography mass spectrometry) for the detection and analysis of energetic materials. 3D-PCSI-MS can sample trace or bulk energetics within or upon solid matrices with no sample preparation. Solid samples, in this case post-blast or post-burn energetics, are placed within the hollow cavity of the cone that has an approximately 100 µm spray-based emitter at the apex. An extraction/spray solvent is added, and a high voltage is subsequently applied. When coupled to a field portable MS, post-burn and post-blast analyses can be performed in the field. Double base propellant was burned on a variety of substrates and examined via 3D-PCSI-MS. An energetic material and stabilizers used in propellants were detected from the post-burn samples with no sample preparation. Trinitrotoluene (TNT, used in military and commercial explosives) and triacetone triperoxide (TATP, a homemade explosive) were examined post-blast on the US ton scale and the gram scale, respectively.

Theory-driven design of graphene-nickel gallate nanocomplex as functional catalyst for composite modified double base propellant

New graphene-nickel gallate nanocomplex (G-M-Ni) was designed, synthesized and characterized to deal with the requirement of functional combustion catalyst based on investigations of combustion mechanisms of propellant, structural analysis of catalyst and simulation results of quantum mechanics. The positive effect of G-M-Ni is not only reflected in the significantly increased burning rate, but also reflected in the reduction of friction sensitivity of composite modified double base (CMDB) propellant. The G-M-Ni nanocomplex exhibited significantly enhanced catalytic performances, and the burning rate of propellant at 20 MPa enhanced from 23.15 to 29.07 mm·s−1. Besides, the friction sensitivity of propellant reduced from 64 % to 36 % after addition of 0.5% G-M-Ni. The positive effect of G-M-Ni on CMDB propellant combustion is mainly attributed to its promotion impact on nitroglycerin (NG) pyrolysis, which significantly increased the differential charge density and decreased the decomposition activation energy (from 1.89 eV to 1.38 eV). The gas products produced by the rapid pyrolysis of NG are conducive to the heat feedback between the gas phase and the combustion surface, which makes the propellant have higher burning rate, bright flame, thin dark zone and flocculated quenching surface morphology. The findings in this study confirm the potential of G-M-Ni as a functional combustion catalyst for CMDB propellants, which has guiding significance and inspiration for the development of new combustion catalysts from the view of molecular-level insights. Novelty and significance statementRecently, graphene based functional combustion catalysts have attracted much attention in the field of solid propellants due to their excellent catalytic combustion performance, reduced sensitivity, and improved mechanical properties. Herein, novel graphene-nickel gallate nanocomplex (G-M-Ni) were designed, synthesized and characterized to deal with the to deal with the requirement of functional combustion catalyst based on investigations of combustion mechanisms of CMDB propellant, structural analysis of new material and simulation results of quantum mechanics. By taking graphene as the benchmark, the G-M-Ni nanocomplex exhibited significantly enhanced catalytic performances, and excellent effect on the reduction of friction sensitivity. The relationship between molecular structure of G-M-Ni and combustion characteristics of CMDB propellant were disclosed. The theory-driven design mode of this work may provide new pathways to tune combustion behaviors of CMDB propellants from the view of molecular-level insights.

EVALUATION OF SOLID ROCKET PROPELLANTS FOR LOW EARTH ORBIT

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 Propellant (ANCP) have been identified. This also falls under the evaluation and includes aspects such as historical bases to see how the formulation of the propellant has changed over time regarding the development of propellant technology. In the case of each propellant, the chemical properties of the mix and reactions that its fundamental are analyzed. It also shares details regarding the changes and advancements made in the little while to enhance capability, safety, and environmental compatibility of these fuels, such as synthesizing fuels for liquid bipropellants. Some of the modern applications of technologies within the active spectrum of aerospace operations are explained in more detail to provide clients with the most versatile and essential information. Among the essentials of this work, the complex calculation of thrusts developed by the specific propellant with corresponding graphics has significant importance. These estimations afford chances of comparing the efficiency of the propellant in terms of producing thrusts as well as achieving the indicated optimal performance. Thus, the main objective of this study is to identify which of the solid rocket propellants to use in LEO missions and if any, what modifications could be made to improve them. Thus, the purpose of this paper is to contribute to the development of the constantly evolving branch of rocket propulsion by discussing the benefits and shortcomings of each propellant. These findings and recommendations could be useful in perfecting the recipes for the propellants and improving the efficiency of the subsequent missions to planets. Keywords: Aerospace, Solid rocket propellants, Thrust, Low earth orbit.

A Study on the Propulsion Performance of Hybrid-Driven Underwater Glider Equipped with a Kappel Tip Rake Propeller

In order to solve the problem of the lack of maneuverability of the conventional underwater glider, this paper proposes a hybrid-driven underwater glider equipped with a Kappel tip rake propeller, analyzes the propulsion performance of different types of Kappel tip rake propellers in the wake field of the hybrid-driven underwater glider, optimizes the overall propulsion performance of the hybrid-driven underwater glider, and realizes self-propulsion and gliding with high efficiency and low energy consumption. In the research process, the Schnerr–Sauer cavitation model and the cavitation simulation strategy of VOF two-phase flow were adopted, coupled with the SST k-ω and γ transition turbulence model, and the control calculation error was not more than 3%. Based on the hydrodynamic performance study of the Kappel tip rake propeller, the self-propelled simulation was carried out under the working conditions of 6 kn, 5 kn, 4 kn, and 3 kn, and the gliding simulation was carried out under the working conditions of 1 kn, 0.5 kn, and a glide angle of 12°. The propulsion performance of the hybrid-driven underwater glider with different models of Kappel tip rake propellers was analyzed. It was found that the maximum open water propulsion efficiency of the propeller Kap05 had the largest improvement, which was 3.07% higher than that of the reference base propeller. Under the self-propelled condition, the hybrid-driven underwater glider with the propeller Kap05 had the lowest wake fraction, and the propellers Kap04 and Kap05 had the best propulsion performance in the wake field of the hybrid-driven underwater glider. In the gliding condition, the form of the folding paddle can reduce the gliding resistance generated by the propeller by more than 45% and the gliding negative lift by more than 68%. A moderate tip rake can effectively improve the propulsion efficiency of the Kappel tip rake propeller in the wake field of the hybrid-driven underwater glider, reduce energy loss, and improve the overall performance of the hybrid-driven underwater glider.

Exploring the characteristics and thermal behavior of double base propellants based on nitrocellulose and diethylene glycol dinitrate in the presence of ternary-nanothermites containing various oxidizers

Exploring the characteristics and thermal behavior of double base propellants based on nitrocellulose and diethylene glycol dinitrate in the presence of ternary-nanothermites containing various oxidizers

Examining the impact of nano‐sized Litharge, Tenorite, and Hematite on the thermal decomposition of ammonium perchlorate‐based cross‐linked composite modified double base propellant

AbstractThis study aims to compare the catalytic effects of three nano‐metal oxides (nMOs); Litharge (α‐PbO), Tenorite (CuO), and Hematite (α‐Fe2O3) on the thermal decomposition of an ammonium perchlorate based cross‐linked composite modified double base propellant (AP‐XLCMDBP). The three nMOs are synthesized via a chemical precipitation method and then characterized using XRD, FTIR, and SEM. Their effect on the thermal decomposition of AP‐XLCMDBP is studied using thermogravimetric analysis (TGA) and differential scanning calorimeter (DSC). The results indicate that Litharge has no significant effect on the thermal decomposition of AP‐XLCMDBP. However, both Tenorite and Hematite nanocatalysts accelerate the thermolysis process and enhance the total heat released from AP‐XLCMDBP. Moreover, compared to Tenorite, Hematite nanoparticles are found to be a more efficient catalyst, where their presence in AP‐XLCMDBP leads to a significant decrease in activation energies of the first and the second decomposition stages by 13.67 kJ/mol and 17.57 kJ/mol, respectively. An increase of the total decomposition heat by 153.73 J/g is also attained in the presence of Hematite, displaying its high catalytic action on the thermal decomposition of AP‐XLCMDBP.

Modified Arrhenius kinetics for double base propellant decomposition: Effect of water

Numerous studies have been conducted on the decomposition mechanisms of cellulose nitrate (NC), a polymer employed in double base (DB) rocket propellants. It is well known that storage temperature affects the lifetime of these energetic formulations. However, less studies have been published on the influence of water. This research examined the role of water on the stabiliser consumption rate during accelerated ageing of a DB rocket propellant, as well as the impact on the shelf life prediction of the energetic formulation. Different volumes of water (0.8, 1.6, 2 and 4 µl/g) were added to the propellant in sealed vials, which were then isothermally aged (70, 80, 90, 100 °C). Analyses of the stabiliser consumption showed a faster decomposition kinetics in presence of water which is indirectly linked to the shortening of the storage life of the NC based propellant by 35 %. For the conditions, an activation energy of 133 ± 4 kJ/mol was reported for the water catalytic decomposition mechanism. A numerical model that included water as a variable was reported to reduce the uncertainty in the determination of the service life of NC based propellant. International standards such as Allied Ordnance Publication 48 should not overlook the effect of water/moisture on the safety of ammunition containing NC and should implement a modified Arrhenius equation.

A Novel Method of Improving the Mechanical Properties of Propellant Using Energetic Thermoplastic Elastomers with Bonding Groups.

The relatively poor mechanical properties of extruded modified double base (EMDB) propellants limit their range of applications. To overcome these drawbacks, a novel method was proposed to introduce glycidyl azide polymer-based energetic thermoplastic elastomers (GAP-ETPE) with bonding groups into the propellant adhesive. The influence of the molecular structure of three kinds of elastomers on the mechanical properties of the resultant propellant was analyzed. It was found that the mechanical properties of the propellant with 3% CBA-ETPE (a type of GAP-ETPE that features chain extensions using N-(2-Cyanoethyl) diethanolamine and 1,4-butanediol) were improved at both 50 °C and -40 °C compared to a control propellant without GAP-ETPE. The elongation and impact strength of the propellant at -40 °C were 7.49% and 6.58 MPa, respectively, while the impact strength and maximum tensile strength of the propellant at 50 °C reached 21.1 MPa and 1.19 MPa, respectively. In addition, all three types of GAP-ETPE improved the safety of EMDB propellants. The friction sensitivity of the propellant with 3% CBA-ETPE was found to be 0%, and its characteristic drop height H50 was found to be 39.0 cm; 126% higher than the traditional EMDB propellant. These results provide guidance for studies aiming to optimize the performance of EMDB propellants.

Effect of silica filler on peroxide cured ethylene propylene diene terpolymer insulation for large rocket motors

AbstractNon‐compatibility with double base propellant and nitrate ester plasticized polyether based propellant and poor aging resistance limit the overall life of sulfur cured EPDM insulation and warranted the development of peroxide cured EPDM insulation in order to reap the full benefits of EPDM insulation. This article describes the effect of silica filler on the physical, mechanical, thermal, and ablative properties of peroxide cured EPDM insulation, free from chlorosulphonated polyethylene and filled with conventional precipitated silica, which has been validated for the requirements of large composite rocket motor casing. Significant findings, which have been corroborated by instrumental techniques viz. DSC, TGA, FTIR, and SEM are presented in this article.

Correlation between microstructural evolution and mechanical properties of CMDB propellant during uniaxial tension

AbstractNumerical simulation of the deformation and damage evolution process of composite modified double base (CMDB) propellant based on the microstructure is of great significance for improving its macro‐mechanical properties. The macro‐mechanical properties and damage evolution of CMDB propellant were studied experimentally and numerically in current work. To establish the correlation between microstructural evolution and the macro‐mechanical response of the propellant, a three‐dimensional microstructure model of the CMDB propellant was constructed utilizing the molecular dynamics particle filling approach. At the interface between RDX particles and the nitrocellulose‐nitroglycerine (NC‐NG) matrix, the conventional cohesive element was replaced by cohesive contact, and the parameters of the cohesive zone model (CZM) at the interface between the particles and the matrix were obtained by parameter inversion based on the Hooke‐Jeeves parameter optimization algorithm. The processes of damage initiation, propagation, convergence, and failure at the cohesive interface were simulated using the bilinear cohesive zone model (BCZM). The results revealed that the fracture strength of NC‐NG propellant with added RDX particles was significantly increased and the fracture elongation was reduced. The three‐dimensional microstructure model can accurately describe the microstructure of CMDB, and dewetting at the interface is the primary cause of propellant degradation when subjected to an external load, which compromises the mechanical properties of the propellant.

Storage-life prediction and relationship between maximum elongation and stabilizer depletion for a composite modified double base propellant (CMDB) propellant

Storage-life prediction and relationship between maximum elongation and stabilizer depletion for a composite modified double base propellant (CMDB) propellant

Determining kinetic parameters for the thermal decomposition of double base propellant catalyzed by a graphene oxide–barium oxide nanocomposite

Determining kinetic parameters for the thermal decomposition of double base propellant catalyzed by a graphene oxide–barium oxide nanocomposite

Combinations of essential oils as effective green stabilizers for single base propellants

AbstractNitrocellulose‐based propellants undergo natural (and inevitable) autocatalytic degradation reactions. The presence of a stabilizer is essential to avoid and reduce the degradation reactions by capturing the NOx molecules. Traditional stabilizers, such as diphenylamine, and ethylcentralite, react with NOx through their amine and/or amide groups, leading to n‐nitroso groups, which are known to have carcinogenic, mutagenic and reprotoxic properties. Molecules that are not prone to form by‐products containing nitrosamines have been studied as substitutes, such as guaiacol and curcumin. However, the aromatic rings on these molecules have their acidity augmented when capturing the NOx groups and, paradoxically, increasing hydrolysis rates. In order to find a solution for the problem, we evaluated the use of essential oils containing terpenes and/or phenolic compounds to introduce a buffering capacity. Several propellant formulations with those compounds were subjected to traditional stability tests (German, Bergman–Junk and Storage tests), Pressure Vacuum Stability Test and Heat Flow Microcalorimetry. Finally, industrial batches were produced for the evaluation of real (ballistic) performance. Results indicated that the usage of essential oils increases stability properties not only through a sum of effects, but also in a synergistic way. Ballistic results were also adequate.

Elucidating the effect of nitrocellulose-encapsulated MgAl–CuO on the thermal behavior of double base propellant based on nitrocellulose and diethylene glycol dinitrate

Elucidating the effect of nitrocellulose-encapsulated MgAl–CuO on the thermal behavior of double base propellant based on nitrocellulose and diethylene glycol dinitrate

Investigation of the Effect of Axial Gap on the Mechanical Response of a Cartridge-Loaded CMDB Propellant Grain under Vibration Loads

In this study, the effect of the axial gap on the mechanical response of a cartridge-loaded propellant grain under vibration loads is investigated. The wide strain rate range of uniaxial compression tests ( 1.7 × 10 − 3 ~ 4 × 10 3 s − 1 ) on the composite modified double base (CMDB) propellant was carried out by using a universal testing machine, a hydraulic testing machine, and a split Hopkinson pressure bar system, respectively. A linear viscoelastic constitutive model of the CMDB propellant was developed by using the experimental measurements. The results show the studied CMDB propellant has a strong strain rate dependence, exhibiting an initial linear elasticity followed by a strain hardening region. The dynamic process of collision between the propellant grain and the motor case in the axial direction induced by vibration loads was simulated with the developed constitutive model by using the finite element method. The effects of the gap size between the propellant grain and the case and the vibration frequency on the mechanical response of the grain were studied. This shows that with a constant vibration frequency, the stress of the grain increases first and then decreases with increasing gap size. Moreover, the stress increases with increasing vibration loads.

Development of high burn rate propellant and testing in miniature rocket motor for control applications

For aerospace vehicles, notably missiles or satellites for attitude and divert control, impulsive thrusters are most desirable if they are quantized as exact instantaneous pulses available over and after extended periods of inactive storage. These thrusters operate for a few milliseconds (ms), typically between 10 ms to 100 ms duration. Compared to its liquid or gaseous counterpart, an impulsive thruster powered by solid propellants is a simple, and reliable solution. Therefore, they are suitable as reaction control systems and divert thrusters for satellite and unmanned aerial vehicle applications.A typical solid propellant would need an extremely thin web thickness for port burning arrangement due to its brief burn duration, which makes propellant manufacturing and its structural anchoring in motor challenging. A high burn rate and high-density propellant based on ammonium perchlorate, aluminum, and Teflon is processed to enable end-burning configuration thus solving the problems, simplifying propellant manufacturing, structural design and integration. It also permits stacking propellants for multi-pulse applications. The high burn rate (40 mm/s at 120 bar pressure) propellant is formulated and tested for ballistic performance evaluation in proof motor configuration, and evaluation of its advantages over conventional propellant. A case of identical design requirements with both double base propellant and high burn rate pressed propellant is compared, tested and evaluated to compare the relative performance merits. The volumetric load is increased from 47% to 82% due to the development and adoption of high burn rate propellant. The overall weight of the thruster is also reduced by 20%.