Combustion of Nanoaluminum and Magnesium in Fuel‐Rich Propellants

Maggi, F.; Zadra, Francesco

doi:10.1002/prep.201900354

Cited by 14 publications

(4 citation statements)

References 17 publications

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“…Hypergolic fuels are mainly used as propellants in rocket engines and simply consist of a fuel and a strong oxidizer that ignite spontaneously upon contact at ambient conditions without external stimuli. Fuels include hydrazine derivatives, heterocyclics, long-chain aliphatics, N-alkyl diamines, aromatics, sugars, ionic liquids, metal-organic frameworks and metal powders (Al, Mg), whereas strong oxidizers include fuming nitric acid HNO 3 , N 2 O 4 , NH 4 ClO 4 , KClO 3 , concentrated H 2 O 2 and Na 2 O 2 to name a few [34][35][36][37][38][39][40][41][42][43][44][45][46]. Some criteria for hypergolic fuels are high energy value (25-50 kJ•g −1 [41]), high density (e.g., preferably solid fuels that occupy less space), inexpensiveness, low toxicity and fast ignition upon contact with a strong oxidizer.…”

Section: Carbon Hypergolicitymentioning

confidence: 99%

Biomass Waste Carbonization in Piranha Solution: A Route to Hypergolic Carbons?

Chalmpes

Baikousi

Giousis

et al. 2022

Micro

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In the present work we report for the first time the carbonization of biomass waste, such as stale bread and spent coffee, in piranha solution (H2SO4-H2O2) at ambient conditions. Carbonization is fast and exothermic, resulting in the formation of carbon nanosheets at decent yields of 25–35%, depending on the starting material. The structure and morphology of the nanosheets were verified by X-ray diffraction, Raman, X-ray photoelectron and microscopy techniques. Interestingly, the obtained carbon spontaneously ignites upon contact with fuming nitric acid HNO3 at ambient conditions, thus offering a rare example of hypergolicity involving carbon as the solid fuel (i.e., hypergolic carbon). Based on the relatively large interlayer spacing of the as-produced carbons, a simple structural model is proposed for the observed hypergolicity, wherein HNO3 molecules fit in the gallery space of carbon, thus exposing its basal plane and defect sites to a spontaneous reaction with the strong oxidizing agent. This finding may pave the way towards new type hypergolic propellants based on carbon, the latter exclusively obtained by the carbonization of biomass waste in piranha solution.

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Section: Carbon Hypergolicitymentioning

confidence: 99%

Biomass Waste Carbonization in Piranha Solution: A Route to Hypergolic Carbons?

Chalmpes

Baikousi

Giousis

et al. 2022

Micro

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“…[1][2][3][4] Compared with traditional rocket, rocket ramjet uses fuel-rich propellants. [5][6][7] Fuel-rich propellants include magnesium-based fuel-rich propellants, aluminiumbased fuel-rich propellants, and boron-based fuel-rich propellants. [8][9][10][11][12][13][14] Boron-based fuel-rich propellants have the highest specic impulse between them because boron (B) has a high caloric value and high-density performance characteristics.…”

Section: Introductionmentioning

confidence: 99%

Dual-core–shell structure B@LiF@AP with multi-effect synergies to improve processibility and energy release characteristics of B

et al. 2023

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“…This not only reduces the combustion stability of the fuel-rich in the gas generator and slows down the rate at which the particles leave the combustion surface, but also leads to poor fuel injection, which in turn leads to slag accumulation and nozzle erosion [4][5]. Using Al nanoparticles helps avoid Al particle agglomerations during combustion [6][7][8], as does the addition of high-entropy alloys [9][10], fluoropolymer coatings [11][12]. However, as a result, the addition of more powders leads to problems such as higher viscosity of the slurry [13], and fluoropolymer coating can complicate the process, both leading to difficulties in achieving a stable process.…”

Section: Introductionmentioning

confidence: 99%

Enhanced combustion characteristics of fuel‐rich propellant based on Al−Mg via GAP‐IPDI energetic thermoplastic polymer

Luo

Zhang

Jin

et al. 2023

Propellants Explo Pyrotec

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In this work, the energetic thermoplastic polymers were synthesized with different ratios of energetic prepolymer glycidyl azide (GAP) and isophorone diisocyanate (IPDI), and used as the binder to prepare fuel‐rich propellants based on Al−Mg. The results showed that energetic thermoplastic polymer enabled the fuel‐rich propellant a faster flame spread, greater flame strength, and a stronger injection effect of metal droplets. The weight loss (Δm) of the propellants increased with GAP content, while the weight loss rate (Dmax) increased similarly. The Δm increased from 7.92 % to 9.86 % and Dmax from −0.23 % ⋅ °C−1 to −0.35 % ⋅ °C−1 in the range 100–256.5 °C. The propellant with the highest GAP content (85GAP‐Prop) had the lowest apparent activation energy (150.77 kJ ⋅ mol−1). The average pressure rate of 85GAP‐Prop burning in a closed bomb reached 7.67 MPa ⋅ s−1 and the maximum instantaneous pressure rate could reach 16.52 MPa ⋅ s−1, significantly higher than the other propellants. The combustion products analysis indicated that the higher GAP content in the GAP‐IPDI energetic thermoplastic polymer more significantly reduced the agglomeration of Al particles and improved the loosening of the combustion products. The rapid combustion gas generation characteristic and energy release of energetic thermoplastic polymer enhanced the combustion characteristics of the fuel‐rich propellant based on Al−Mg, which promoted dispersion level between the metal droplets. This work provides insight into the combustion principles and performance improvements of fuel‐rich propellant based on Al−Mg.

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Combustion of Nanoaluminum and Magnesium in Fuel‐Rich Propellants

Cited by 14 publications

References 17 publications

Biomass Waste Carbonization in Piranha Solution: A Route to Hypergolic Carbons?

Biomass Waste Carbonization in Piranha Solution: A Route to Hypergolic Carbons?

Dual-core–shell structure B@LiF@AP with multi-effect synergies to improve processibility and energy release characteristics of B

Enhanced combustion characteristics of fuel‐rich propellant based on Al−Mg via GAP‐IPDI energetic thermoplastic polymer

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