Propellant Burning Rate Research Articles

Tuning the micro‐structure, laser ignition, and isovolumetric burning performance of nitrocellulose propellant via incorporation of graphene oxide

AbstractNanoscale recombination between carbon nanomaterials (CNs) and polymers has been proposed for a variety of industrial and scientific applications. Composite energetic materials consisting of CNs with novel laser ignition property and tunable combustion performance have attracted people's attention. Here, reported is the novel manufacturing process of uniform nitrocellulose (NC)/graphene oxide (GO) nanocomposite propellant and the micro‐structure, laser ignition and isovolumetric burning features of the propellants introduced by GO. The results of microstructure tests indicated that GO (0.25–2 wt%) was stripped and dispersed homogeneously and dense nanocomposite propellants were prepared successfully through water ultrasonic dispersion, twin‐screw mixture, as well as compression molding. The crystallization of NC was forbidden by doping GO, meanwhile, the thermal stability and thermal conductivity of the composite propellants increased slightly with the addition of GO. The results of laser ignition combustion experiments showed that GO was an efficient additive to shorten the ignition delay time from more than 2000–14 ms when 2 wt% of GO was doped, however, the combustion flame intensity was also weakened due to the addition of GO. The combustion tests in a closed bomb vessel were conducted, and the results showed that GO would not affect the stable combustion of NC at high combustion pressure, moreover, the burning rate and dynamic vivacity of the composite propellants decreased with the increase of GO content.

Prediction of Solid Propellant Burning Rate Characteristics Using Machine Learning Techniques

AbstractWhen formulating a new solid propellant, one of the most important aspects of its performance is the burning rate's response to a change in pressure. For this reason, it is useful to be able to predict the burning rate response of a given propellant before the propellant formulation is created such that experimental trade studies are minimized or reduced in scale. While many theoretical and phenomenological models have been proposed to explain various aspects of energetic material combustion, little work has been made publicly available in the application of machine learning models to predicting solid propellant burning rates. To facilitate model creation, the material formulation and burning rate parameters for over 600 publicly available propellant formulations have been collected into a coherent data set. This work utilizes the large amount of publicly available data to inform a random forest machine learning (ML) model in the prediction of solid propellant burning rate parameters. This ML model operates over a large parameter space including ammonium perchlorate composite, plastic bonded high explosive, and double‐base propellants. The model's accuracy, adaptability, and prediction capabilities are presented and discussed. The effects of different materials on a propellant's expected burning rate are examined.

AP-HTPB propellant combustion under strain conditions with laser absorption spectroscopy.

Understanding the combustion behaviors of solid propellant with different levels of strains is of practical interest. In this work, an experimental study of the effects of static and dynamic strains on the burning rate, temperature, CO, and C O 2 formation of aluminized ammonium perchlorate (AP)-hydroxyl terminated poly-butadiene (HTPB) propellant combustion was presented at initial pressures of 0.1MPa, 0.2MPa, and 0.5MPa. The strains were being applied onto solid propellant by exerting static and cyclic loadings. The propellant burning rate was acquired by a 4kHz high-speed photography system, and the combustion temperature, CO, and C O 2 column densities were measured at 10kHz through laser absorption spectroscopy (LAS). At atmospheric pressure, it was demonstrated that the propellant burning rate increased with tensile stress and decreased with compressive stress. The measured flame temperature showed a similar correlation with strains as compared to the propellant burning rate. At elevated pressures, the increase of the propellant burning rate due to tensile stress was more evident, while the difference in combustion temperatures was less significant. For the cyclic strain condition, the variations of the measured C O 2 and CO column densities were consistent with the static strain condition.

Embracing Anisotropy – Opportunities and Challenges to the Functional Application of Advanced Manufacturing of Energetic Materials

Embracing Anisotropy – Opportunities and Challenges to the Functional Application of Advanced Manufacturing of Energetic Materials

INFLUENCE OF BURNING RATE INHIBITORS ON THE THERMAL BEHAVIOR AND DECOMPOSITION KINETICS OF AMMONIUM PERCHLORATE

The addition of burning rate inhibitors (BRIs) to propellant formulations can be effective in reducing the burning rate of composite solid propellants (CSPs). Ammonium perchlorate (AP) is commonly used as an oxidizer for CSPs and is a major component of propellants. Therefore, it is of great significance to study the thermolysis performance of AP in the presence of BRIs. In this work, differential scanning calorimetry and thermogravimetric analysis were utilized to study the thermolysis of AP. Oxamide (OXA), ammonium sulfate (AS), ammonium oxalate (AO), and carbamide (CA) were selected as the BRIs. The results showed that as the BRI content increased, the endothermic peak remained essentially unchanged. The exothermic peak in the low-temperature decomposition (LTD) stage shifted to a hightemperature field, while the exothermic peak in the high-temperature decomposition (HTD) stage shifted to a low-temperature field. Furthermore, associated kinetic studies showed that the decomposition activation energies of AP with inhibitors during the LTD stage were higher than that of pure AP, proving that the selected BRIs could effectively inhibit the thermolysis of AP. However, during the HTD stage, the values of the activation energies for decomposition gradually increased in the order of AP + AO, AP + OXA, AP + CA, AP, and AP + AS, indicating that only AS had the effect of inhibition at this time.

Design, preparation, and combustion performance of energetic catalysts based on transition metal ions (Cu2+, Co2+, Fe2+) and 3-aminofurazan-4-carboxylic acid.

Development of energetic catalysts with high energy density and strong catalytic activity has become the focus and frontier of research, which is expected to improve the combustion performance and ballistic properties of solid propellants. In this work, three energetic catalysts, M(H2O)4(AFCA)2·H2O (AFCA = 3-aminofurazan-4-carboxylic acid, M = Cu, Co, Fe), are designed and synthesized based on the coordination reaction of transition metal ions and the energetic ligand. The target products are characterized by single crystal X-ray diffraction, Fourier transform infrared spectroscopy, differential thermal analysis, optical microscopy, and scanning electron microscopy. The results reveal that Cu(H2O)4(AFCA)2·H2O crystallizes in the monoclinic space group, Dc = 1.918 g cm-3. Co(H2O)4(AFCA)2·H2O, and Fe(H2O)4(AFCA)2·H2O belong to orthorhombic space groups, their density is 1.886 g cm-3 and 1.856 g cm-3, respectively. In addition, the designed catalysts show higher catalytic activity than some reported catalysts such as Co(en)(H2BTI)2]2·en (H3BTI = 4,5-bis(1H-tetrazol-5-yl)-1H-imida-zole), Co-AzT (H2AzT = 5,5'-azotetrazole-1,1'-diol), and [Pb(BTF)(H2O)2]n (BTF = 4,4'-oxybis [3,3'-(1-hydroxy-tetrazolyl)]furazan) for the thermal decomposition of ammonium perchlorate (AP). The high-temperature decomposition peak temperatures of AP/Cu(H2O)4(AFCA)2·H2O, AP/Co(H2O)4(AFCA)2·H2O, and AP/Fe(H2O)4 (AFCA)2·H2O are decreased by 120.3 °C, 151.8 °C and 89.5 °C compared to the case of pure AP, while the heat release of them are increased by 768.8 J g-1, 780.5 J g-1, 750.9 J g-1, respectively. Moreover, the burning rates of solid propellants composed of AP/Cu(AFCA)2(H2O)4·H2O, AP/Co(AFCA)2(H2O)4·H2O and AP/Fe(AFCA)2(H2O)4·H2O are increased by 2.16 mm s-1, 2.53 mm s-1, and 1.57 mm s-1 compared with the case of pure AP. This research shows considerable application prospects in improving the combustion and energy performance of solid propellants, it is also a reference for the design and preparation of other novel energetic catalysts.

Improving ignition and combustion performance of Al@Ni in CMDB Propellants: Effect of nickel coating

Micron-sized aluminum particles tend to melt into agglomerates, leading to incomplete combustion, two-phase flow losses, and energy decrease of propellants. The higher ignition performance of core–shell Al@Ni makes it a promising candidate fuel with high combustion efficiency. However, little work has been done to study the combustion of Al@Ni in propellants. Here, we report a first attempt to investigate the combustion mechanism of core–shell Al@Ni in the double-based propellant containing high energy explosive HMX, and evaluate its potential as a fuel. Nickel in Al@Ni is determined to play a critical role during its intrinsic combustion and the combustion in propellants. In the condensed phase, the presence of Ni enhances the oxidation process by forming a porous oxide layer on the aluminum surface that promotes oxygen diffusion. Subsequently the phase transition and expansion of Ni break down this oxide layer, leading to the earlier ignition on the burning surface. Upon Al melting, the alloying of Ni and Al accelerates the volume expansion and surface tension reduction of the fuel, giving rise to vigorous melt-dispersion combustion and enhanced energy release. Enhanced thermal feedback and thermal decomposition exotherm combined to increase the burning rate of propellant. The resulting higher flame temperature allows the evaporation of small aluminum droplets into vapor to form smoke oxide productions, further reducing the size distribution of the condensed combustion products (CCPs). This study demonstrates the potential of Al@Ni as an effective fuel for double-based propellants, and provides the insight into its combustion mechanism in HMX-CMDB propellants, which is believed to be important for the development of novel aluminum-based fuels for solid propellants.

Tunning Combustion Behaviors of Composite Modified Double-Based Propellants with a Novel Energetic Burn Rate Modifier

ABSTRACT The flexible control in burning rate and stable combustion of solid propellants over a broad range of pressures essentially determine the performance of solid rocket motors. The nanoscale metals and their oxides are usually utilized as the traditional burn rate modifiers in adjusting the combustion behaviors of solid propellants, but the energy characteristics of propellants are greatly compromised owing to the inert nature of additives used. In this paper, a series of metal complexes of triaminoguanidine-glyoxal polymer (TAGP-Ms) with high nitrogen content were synthesized and employed as energetic burn rate inhibitors in tunning the combustion properties of composite modified double-based (CMDB) propellants. The influences of prepared TAGP-Ms on the thermal decomposition and combustion of CMDB propellants were comprehensively investigated based on thermal analysis technique and combustion characterization methods. It was found that the peak temperatures of the second exotherm displayed for the propellants containing TAGP-Ms inhibitors were significantly increased by more than 30°C (except for TAGP-Cu), indicating the TAGP-Ms is capable of suppressing the thermal decomposition of CMDB propellants. More importantly, the heat releases of CMDB propellants were substantially enhanced by 16%~34% determined by DSC analysis. In comparison to the blank reference, the energetic TAGP-Ms inhibitors could promote the heat of combustion for the involved CMDB propellants by 5%~9%. The burning rates of CMDB propellants were notably reduced over a wide range of pressures by adding TAGP-Ms, whereas the calculated pressure exponents at pressures ranging from 10 to ~ 22 MPa appear to be relatively high due to the accelerated HMX decomposition. The measured combustion wave temperatures suggest that the CMDB propellants with TAGP-Ms undergo a three-stage combustion process with the highest temperatures in the range of 2160 ~ 2230°C.

Thermal Decomposition, Ignition Process and Combustion Behavior of Nitrate Ester Plasticized Polyether Propellant at 0.1–3.0 MPa

Nitrate ester plasticized polyether (NEPE) propellant is widely used in solid rocket motors, having both good mechanical properties and high specific impulse. However, its ignition and combustion process are complex and need to be better understood. In this study, a high-pressure sealed combustion chamber was constructed, a thermogravimetry-differential scanning calorimetry was used to investigate the thermal decomposition process, and a high-speed camera was used to capture the ignition process and combustion behavior of the propellant. The results showed that the thermal decomposition process of this propellant could be divided into two stages. The first stage (50–350°C) was the major mass loss stage and exhibited typical features of BTTN, RDX, and AP decomposition. The second stage (350–500°C) was mainly accompanied by decomposition of the remaining components as well as slight oxidation of aluminum particles. The ignition process of NEPE propellant was divided into four stages, including the inert heating period stage, thermal decomposition stage, initial flame stage, and stable combustion stage. After the propellant absorbed heat, the propellant started to pyrolyze and gasify to generate flammable gas. When the temperature of the propellant surface reached the flammable gas ignition point, an initial flame was generated on the surface, which spread rapidly, covering the surface. The ignition delay time of the propellant was measured by a signal acquisition system, and a mathematical model was then established for the ignition delay time. The results showed that the ignition delay time decreased with increased laser heat flux and ambient pressure. Finally, the Vielle burning rate empirical formula was used to fit the burning rate data for the propellant. The resulting good fit was consistent with experimental measurements and showed that the formula was valid for predicting the NEPE propellant burning rate under 0.1–3.0 MPa nitrogen.

In Situ Cutting of Ammonium Perchlorate Particles by Co-Bipy "scalpel" for High Efficiency Thermal Decomposition.

Burning rate of solid propellants can be effectively improved by adding catalysts and using smaller size ammonium perchlorate (AP). Although few reports, the exploration of changing the size of AP primary particles by catalysts is of great significance for improving combustion performance. Here, taking Co-bipy as an example, the potential advantages of such materials as AP decomposition catalysts are reported. Due to the existence of NO3 - combined with oxygen rich environment provided by AP, the structural self-transformation from micronrods to nanoparticles can be quickly realized during the heating process. More importantly, when Co-bipy decomposes, it can play the role of "scalpel" and in situ cut AP particles. Results show that high-temperature decomposition of Co-bipy/AP occurs at 305.8 °C, which is 137.5 °C lower than that of pure AP. Catalytic mechanism is discussed by in situ IR and TG-IR, CoO can effectively increase the content of reactive oxygen species and weaken the N-H bond, realizing the rapid oxidation of NH3 . Eventually, the behavior of Co-bipy cutting AP particles is tested. This interesting catalyst structure self-transformation behavior can not only realize the influence on AP, but also perform a positive function in the combustion process of solid propellants, such as opening the adhesive AP interface.

Design and Development of Composite Propellant Using CuFe2O4 Spinel Decorated Graphene Oxide Nanocomposite as Novel Burn Rate Modifier

AbstractThe burning rate of composite rocket propellant is a principal ballistic property that is considered while designing the rocket motor. Carbon bonded materials such as CNT(carbon nanotubes), fullerene, graphene, etc. due to their high surface area have exhibited promising results as burn rate modifiers in a propellant. Apart from enhancing the burn rate, unlike their inorganic counterparts, they are combustible and contribute towards energy output. Herein, we report a spinel structure CuFe2O4 decorated Graphene Oxide nanocomposite as novel burn rate modifier (BRM) in propellant composition. By incorporating 0.6 % of this burn rate modifier to the propellant remarkable improvement in burn rate by 61 % was observed.

Are All Solid Propellant Burning Rate Modifiers Catalysts?

AbstractSolid rocket motors are used for both national defense and launch vehicles. The internal ballistics of the motor depend on the propellant burning rate, which is often modified by burning rate enhancers. Despite the common use, there is not a complete mechanistic understanding of how these modifiers influence the combustion process. In this comment, it is argued that these additives can influence propellant combustion as a catalyst, via thermodynamic means, or a combination. An approach is suggested on how to classify traditional and novel burning rate modifiers as a first step to improving the scientific community‘s knowledge on the matter.

Controlling the combustion and agglomeration characteristics of a solid composite propellant via a DC electric field

This study explores the use of a DC electric field to control the combustion and agglomeration characteristics of a solid composite propellant as typically deployed for rocket propulsion. Experiments were performed in a custom-built reacting flow facility that supports high-speed photography and the collection of condensed combustion products (CCPs). The propellant burning rate, aluminum agglomeration process, CCP size distribution, and combustion efficiency were systematically examined under a range of electric-field voltages (−5 to 5 kV) in both the forward and backward directions. It was found that as the electric-field voltage increased, both the propellant burning rate and combustion efficiency increased, while the degree of aluminum agglomeration decreased, reducing the particle size of the CCPs. The introduction of an electric field can bring about profound effects via particle charge acceleration, Rayleigh crushing, and ion excitation. For example, aluminum near the burning surface can split into smaller particles, the diffusion flames around droplets can exhibit a higher stand-off ratio, and more hollow agglomerates can form, as evidenced by an inspection of scanning electron microscopy images of the CCPs. The electric field was found to have a more pronounced effect in the forward direction than in the backward direction. A physical mechanism was proposed for how an electric field can alter propellant combustion. Through this, the combustion and agglomeration characteristics of solid composite propellants can be precisely tuned with an electric field without resorting to changes in the propellant formulation. The findings of this study contribute to a better understanding of how an electric field can be used to control propellant combustion and thrust in solid rocket motors.

ADN Solid Propellants with High Burning Rates as Booster Material for Hypersonic Applications

AbstractRAM‐ and SCRAM‐Jet engines can not generate static thrust and only work at high speeds. This starting velocity of the motor v0 is usually generated by carrier rockets or boosters, which mostly use solid propellants based on ammonium perchlorate (AP) and hydroxyl‐terminated polybutadiene (HTPB). Modern solid propellants based on ammonium dinitramide (ADN) and Glycidyl Azide Polymer (GAP) have significant advantages in terms of environmental compatibility and thermodynamic performance. In the present work, it is shown that the already high burning rate of ADN solid propellants can be more than doubled by means of metallic fibers, which significantly increases the thrust of such engines. In order to achieve such results, 3 wt% of Al−Mg alloy fibers are added to the propellant. A formulation with 3 mm long fibres shows the highest burning rate with 84.0 mm/s at 26.5 MPa. Small scale motor tests confirm these investigations. The burning mechanism is studied by SEM/EDX investigations and by measuring the thermal conductivity. These show that the fibres remain on the burning surface and thus transfer the heat from the flame to the depth of the propellant. The thermal conductivity of samples with AlMg5 fibers is about 22 % higher than the reference.

On the Use of Fluorine‐Containing Nano‐Aluminum Composite Particles to Tailor Composite Solid Rocket Propellants

AbstractThe burning rate of solid propellants is an important factor for optimizing rocket motors and improving performance. The enhanced burning rate can increase thrust and reduce a propulsion system‘s overall size and weight. In this study, a novel nano‐aluminum/THV composite additive was prepared and introduced into a solid ammonium perchlorate/polybutadiene composite solid rocket propellant to enhance its burning rate. The morphology of the composite particle additive and its effects on combustion were characterized. The use of small quantities (<15 wt.%) of the additive resulted in a burning rate enhancement of up to 2.1 times that of the conventional coarse aluminized propellant with a specific impulse loss of only 3 seconds, and as much as 4.7 times enhancement with a predicted loss of 22 seconds in theoretical specific impulse. Some of this loss may be recovered by the improved combustion efficiency in smaller rocket motors because the additive was shown to significantly reduce the aluminum agglomeration at the propellant burning surface and reduce the size of reaction products which may reduce two‐phase flow losses. The additive also provides wide burning rate tailorability, favorable for motor, grain, and thrust curve design. The burning rate enhancement mechanism is thought to be a physical cratering mechanism governed by the burning rate disparity between the binder/oxidizer system and the nano‐aluminum/fluoropolymer additive and not a chemical catalytic effect.

-Ferrocenedicarboxylic Acid Salts as Burning Rate Modifiers of Double-Base Propellant

To expand the possibilities of using solid propellants in gas generators or civil- purpose rockets, the properties of new compounds proposed as burning rate modifiers were considered. -ferrocenedicarboxylic acid and its insolubility in water copper, iron, and lead salts were synthesized. The effect of the salts on the burning rate of a double-base propellant was studied. It was shown that individually 3% of copper salt (CFDA) has the most considerable effect on the burning rate, increasing by times at the pressure interval of 1–10 MPa. It is possible to lower the n value in the burning law from 0.71 to 0.21 in a pressure range of 6–15 MPa with use of lead salt. Carbon nanotubes significantly increase the efficiency of FDA salts. An interesting phenomenon was discovered: Iron salt (IFDA) affects the burning rate only at pressure up to 2 MPa, and at higher pressures, but only in combination with a carbon nanotube. IFDA also reduces the efficiency of CFDA. An explanation of that fact was suggested.

Determining the Burning Rate of Fine-Grained Propellants in Closed Vessel Tests

This paper presents the method of determining the burning rate of fine-grained propellants based on the results of closed vessel tests. It is shown that in the case of fine-grained propellants, the standard methods of determining the burning rate fail. There are two reasons for this: imperfections of the grain shapes and the prolonged process of ignition due to a more developed surface than that of coarse grains at the same mass of the propellant. The value of the exponent in the burning law is estimated by the use of the so-called experimental form–function. The upper and lower limits of the value of the coefficient in the burning law are estimated. The accuracy of the proposed method is analyzed. Its validity is assessed by comparing the results of closed vessel tests analysis with accessible literature data.

Combustion and agglomeration characteristics of aluminized propellants containing Al/CuO/PVDF metastable intermolecular composites: A highly adjustable functional catalyst

In this experimental study, we explore how the combustion and agglomeration characteristics of solid propellants can be modified by replacing aluminum with ternary Al/CuO/PVDF(Polyvinylidene Fluoride) metastable intermolecular composites (MICs). Using thermogravimetric−differential scanning calorimetry, a laser ignition setup, and a high-pressure propellant combustion system, we examine the thermal reactivity, ignition behavior, burning rate, agglomeration, and condensed combustion products of various MICs-inclusion propellants. We find that the use of ternary Al/CuO/PVDF MICs can decrease the onset temperature and increase the oxidation efficiency of Al, as compared with common binary MICs. The ratio of CuO/PVDF is found to have a strong effect on the combustion intensity of the metallic powders, but only a weak effect on their ignition delay. Higher proportion of PVDF is found to have a negative effect on the combustion rate. Specifically, the combustion intensity is found to decrease first and then increase as the PVDF content increases. The exothermic Al/CuO reaction is found to alter the heat transfer of the condensed layer on the propellant surface, while PVDF plays a critical role in the thermal feedback of the gaseous reaction. When combined, these two factors lead to a ± 30% variation in the propellant burning rate. Furthermore, ternary MICs are found to reduce agglomeration during propellant combustion. The two optimal formulations are 2.5 wt.% CuO/2.5 wt.% PVDF and 3.5 wt.% CuO/1.5 wt.% PVDF. The use of these formulations is found to decrease the mean particle size of the condensed combustion products to only 11 μm, as compared with 76 μm for the original Al-inclusion propellant. High-speed microscope images reveal the existence of crack phenomena in the pockets surrounding the AP particles on the burning surface due to the Al/CuO reaction, as well as the floccule breakup mechanism of Al aggregates in the presence of PVDF, both of which reduce agglomeration. Overall, this study shows that replacing Al with ternary Al/CuO/PVDF MICs has significant effects on the agglomeration, combustion and ignition features of aluminized propellants. The findings of this study can be used to aid the development of highly adjustable functional catalysts for solid propellants.

Synthesis, characterization, and catalytic behaviour of nano‐bimetallic nickel oxide on the thermal decomposition of dihydroxylammonium‐5,5′‐bistetrazole‐1,1′‐diolate

Abstract(Synthesis, characterization, and catalytic behaviour of nano‐bimetallic nickel oxide on the thermal decomposition of dihydroxylammonium‐5,5′‐bistetrazole‐1,1′‐diolate)Bimetal combustion catalyst has become an emerging field in recent years, which is still in its infancy. When the combustion catalyst is used in double‐base propellants, it can produce effects that conventional catalysts cannot achieve. In this study, nano‐bimetallic nickel oxides (nanospheres of NiFe2O4 and the sub‐nanometre flower NiCo2O4) were prepared by hydrothermal method and characterized using X‐ray powder diffraction (XRD), X‐ray photoelectron spectroscopy (XPS), scanning electron microscopy (SEM), and N2 adsorption–desorption test (BET). Moreover, its thermal catalytic action on dihydroxylammonium 5,5'‐bistetrazole‐1,1'‐diolate (TKX‐50) was studied. The thermal analysis of composite TKX‐50/NiFe2O4 and TKX‐50/NiCo2O4 was carried out by thermogravimetric differential scanning calorimetry (TG‐DSC). The results show that when the addition amount of NiFe2O4 is 10%, the heating rate is 5.0 K min−1, the NiFe2O4 has the best catalytic activity for TKX‐50 thermal decomposition, and the high thermal decomposition peak temperature (Tpeak1) is decreased by 29 °C. More interestingly, the apparent activation energies of the two composites were calculated by Kissinger, Ozawa, and Starink methods. The advanced thermal analysis kinetics software (AKTS) was used to perform kinetic calculations on the DSC experimental curves of the above‐mentioned composite energetic materials, and reaction rate curves obtained by the simulation are in good agreement with the experimental curves of the thermal decomposition reaction process, further proving that the accuracy of the experiment is high. Therefore, the addition of NiFe2O4 shows high catalytic efficiency on the thermal decomposition of TKX‐50 components, and this would be beneficial to promote the burning rate of propellants containing TKX‐50 components. © 2022 Society of Chemical Industry (SCI).

Modifying the ignition, combustion and agglomeration characteristics of composite propellants via Al-Mg alloy additives

The performance of propellants, explosives and pyrotechnics is known to benefit from the use of metallic alloys as fuel additives. Previous studies have shown that switching from pure Al to Al-Mg alloy can improve the agglomeration and combustion features of composite propellants. However, the optimal ratio of Al and Mg has yet to be explored. We experimentally examine the effects on ignition, combustion and agglomeration arising from substituting pure Al particles with four different Al-Mg alloys whose Mg content ranges from 10 to 60%. Using thermogravimetric−differential scanning calorimetry, we find that switching to Al-Mg alloy can enable oxidation to occur earlier and can increase the oxidation rate and the enthalpy of thermal reaction, which is found to be positively correlated with the Mg content. Using laser ignition measurements, we find that the addition of Mg can promote the ignition and combustion of Al, with (Al/Mg)0.5 exhibiting the most balanced combination of a high combustion intensity, a short ignition delay, and a high mass burning rate. Through high-pressure measurements taken at 1 to 7 MPa, we find that switching to Al-Mg alloy can increase the propellant burning rate (by nearly a factor of two) and the pressure exponent (from 0.23 to 0.43). We also find that the burning rate and pressure exponent are both highest for the propellant containing (Al/Mg)0.1, but that both quantities decrease with further increases in Mg content. High-speed microscopic surface imaging at 1 MPa reveals that increasing the Mg content can increase the overall combustion intensity of the propellant and decrease the diameter of spherical agglomerates, consistent with the observed size distribution of the condensed combustion products. From these measurements, it can be concluded that (Al/Mg)0.5 provides the optimal balance of ignition, combustion and agglomeration characteristics in the formulation of composite propellants containing Al-Mg alloy.