Investigation of Additively Manufactured Layered Composite Solid Propellant

McClain, Monique; Afriat, Aaron; Montano, Brandon J.; Ray, Simon; Rhoads, Jeffrey F.; Gunduz, I. Emre; Son, Steven F.

doi:10.2514/6.2020-1427

Cited by 9 publications

(3 citation statements)

References 8 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…For comparison purposes, we recall similar work by Sippel et al [35], where the replacement of traditional microscale Al with mechanically activated Al/PTFE resulted in an increase in the burning rate by 1.6 times at most, accompanied by an increase in the burning rate exponent (0.36 to 0.58), and an Isp loss of ~6 seconds. These materials could find interesting applications, such as in additively manufactured propellants deposited in prescribed locations to tailor grain regression [58,59], or for optical ignition purposes in energetics [60,61].…”

Section: Combustion Experimentsmentioning

confidence: 99%

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

Uhlenhake

Yehia

Noel

et al. 2022

Propellants Explo Pyrotec

Self Cite

View full text Add to dashboard Cite

The 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.

show abstract

Section: Combustion Experimentsmentioning

confidence: 99%

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

Uhlenhake

Yehia

Noel

et al. 2022

Propellants Explo Pyrotec

Self Cite

View full text Add to dashboard Cite

show abstract

“…Furthermore, solid propellant grains are of particular interest in different field of energetics, where rapid gas production with compact devices is required (e.g., beside space propulsion, air-bags and fire extinguishers). Specifically, recent efforts for propulsion applications have focused on exploring innovative binders and proof of concepts [ 8 , 9 , 10 , 11 ]. In parallel, photo-polymerization has lately emerged as a viable alternative to traditional manufacturing in a variety of industries [ 12 , 13 , 14 , 15 , 16 , 17 ].…”

Section: Introductionmentioning

confidence: 99%

Rheological and Mechanical Characterization of 3D-Printable Solid Propellant Slurry

Zumbo,

Stumpo,

Antonaci

et al. 2024

Polymers

View full text Add to dashboard Cite

This study delves into the rheological and mechanical properties of a 3D-printable composite solid propellant with 80% wt solids loading. Polybutadiene is used as a binder with ammonium sulfate, which is added as an inert replacement for the ammonium perchlorate oxidizer. Further additives are introduced to allow for UV curing. An in-house illumination system made of four UV-A LEDs (385 nm) is employed to cure the resulting slurry. Rheological and mechanical tests are conducted to evaluate the viscosity, ultimate tensile strength and strain, and compression behavior. Viscosity tests are performed for both pure resin and complete propellant composition. A viscosity reduction factor is obtained for the tested formulations when pre-heating slurry. Uniaxial tensile and compression tests reveal that the mechanical properties are consistent with previous research. Results emphasize the critical role of temperature and solid loading percentage. Pre-heating resin composites may grant a proper viscosity reduction while keeping mechanical properties in the applicability range. Overall, these findings pave the way for the development of a 3D printer prototype for composite solid propellants.

show abstract

“…As the development of efficient alternative propellant compositions requires the ab initio design of the fuel-binder component, it is advantageous to have the new materials compatible also with emerging modern production techniques, such as additive manufacturing (AM). Harnessing AM to the production of energetic materials, such as propellants, is currently being attempted. − In one approach, conventional thermoset polymers, such as HTPB/isocyanate, are deposited layer by layer and cured. In another approach, commercial photo-monomers, such as acrylates and epoxides, are used as the fuel and binder.…”

Section: Introductionmentioning

confidence: 99%

Alkyl Vinyl Imidazolium Ionic Liquids as Fuel Binders for Photo-curable Energetic Propellants

Zertal

Yong

Levi

et al. 2022

ACS Appl. Polym. Mater.

View full text Add to dashboard Cite

Polymers, made of energetic ionic liquid building blocks, are used as the fuel-binder part in propellant compositions. These compositions exhibit desired mechanical and energetic properties and may serve as a photoactive feed for 3D printable propellants. Quaternary vinyl imidazolium energetic salts, having perchlorate and nitrate counter ions, are used as monomers in fuel-binder polymers, while ammonium perchlorate is used as the heterogeneous oxidizer in the composition. The vinyl groups on the heterocyclic cations provide covalent interconnecting sites for the construction of the polymer backbone and binding sites for in-chain plasticizers, enabling control over mechanical and initiation sensitivity properties in the cured composite product. The advantageous oxygen balance and heat of formation values of these ionic liquid monomers, along with their ability to photo-polymerize, allow both the effective dispersion and reduced ratios of the heterogeneous oxidizer content without compromising the energetic properties of the resultant propellant. An intermolecular interaction between the heterocyclic imidazolium units was identified, which enables noncovalent reinforcement and may explain some of the observed properties of the compositions. Pressure-independent burn rates were achieved in compositions containing 2-ethoxyethyl acrylate plasticizer, thus avoiding the need for additional additives, stratification, and geometrical constraints on the burning bulk.

show abstract

Investigation of Additively Manufactured Layered Composite Solid Propellant

Cited by 9 publications

References 8 publications

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

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

Rheological and Mechanical Characterization of 3D-Printable Solid Propellant Slurry

Alkyl Vinyl Imidazolium Ionic Liquids as Fuel Binders for Photo-curable Energetic Propellants

Contact Info

Product

Resources

About