Combustion Characteristics of a Novel Grain‐Binding High Burning Rate Propellant

Guo, Xiaode; Li, Fengsheng; Song, Hang; Liu, Guanpeng; Kong, Lei; Li, Miaomiao; Chen, Weifan

doi:10.1002/prep.200800223

Cited by 8 publications

(2 citation statements)

References 6 publications

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“…SDFS is a concept borrowed from composite modified double-base propellant [36] and new for hybrid propellant burning, whereby the binder will release fuel particles from a block of composite solid fuel over some critical threshold condition (for example, a melting temperature). Combustion visualization shows a lot of burning granules of the implemented filler escaping from the burning surface into the gas flow; see Figure 7.…”

Section: Self-disintegration Fuel Structure (Sdfs)/paraffinmentioning

confidence: 99%

Innovative Methods to Enhance the Combustion Properties of Solid Fuels for Hybrid Rocket Propulsion

et al. 2019

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The low regression rates for hydroxyl-terminated polybutadiene (HTPB)-based solid fuels and poor mechanical properties for the alternative paraffin-based liquefying fuels make today hybrid rocket engines far from the outstanding accomplishments of solid motors and liquid engines. In this paper, a survey is conducted of several innovative methods under test to improve solid fuel properties, which include self-disintegration fuel structure (SDFS)/paraffin fuels, paraffin fuels with better mechanical properties, high thermal conductivity fuels and porous layer combustion fuels. In particular, concerning HTPB, new results about diverse insert and low-energy polymer particles enhancing the combustion properties of HTPB are presented. Compared to pure HTPB, regression rate can be increased up to 21% by adding particles of polymers such as 5% polyethylene or 10% oleamide. Concerning paraffin, new results about self-disintegrating composite fuels incorporating Magnesium particles (MgP) point out that 15% 1 μm- or 100 μm-MgP formulations increase regression rates by 163.2% or 82.1% respectively, at 335 kg/m2·s oxygen flux, compared to pure paraffin. Overall, composite solid fuels featuring self-disintegration structure appear the most promising innovative technique, since they allow separating the matrix regression from the combustion of the filler grains. Yet, the investigated methods are at their initial stage. Substantial work of refinement in this paper is for producing solid fuels to fulfill the needs of hybrid rocket propulsion.

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Section: Self-disintegration Fuel Structure (Sdfs)/paraffinmentioning

confidence: 99%

Innovative Methods to Enhance the Combustion Properties of Solid Fuels for Hybrid Rocket Propulsion

et al. 2019

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“…For AP-propellants the regression rate can be increased by using fine particles with d 50 < 5 μm [7]. As the literature does not indicate any possibilities of significantly increasing the burning rate of ADN propellants by chemical modification, other ways must be found.…”

Section: Introductionmentioning

confidence: 99%

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

Sims

Fischer

Tagliabue

2022

Propellants Explo Pyrotec

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RAM-and SCRAM-Jet engines can not generate static thrust and only work at high speeds. This starting velocity of the motor v 0 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 AlÀ 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.

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Burning Rate Performance Study of Ammonium Perchlorate Catalyzed by Heteroleptic Copper(I) Complexes with Pyrazino[2,3‐f][1,10]phenanthroline‐Based Ligands

Escobar

Morales-Verdejo

Arroyo³

et al. 2021

Eur J Inorg Chem

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This contribution describes the catalytic effect of heteroleptic Cu(I) complexes with pyrazino[2,3‐f][1,10]phenanthroline‐based ligands (C1‐7) on the thermal decomposition of ammonium perchlorate (AP). The complexes C2 and C4‐7 were synthesized and characterized by NMR, HRMS and, in the case of C7, by X‐ray diffraction. The burning rate performance of C1‐7 on thermal decomposition of AP was studied by differential scanning calorimetry technique. The effect of the counter ion type, the number of metal centers and ligand substitution was evaluated. These AP+complex mixtures exerted a shift to lower ignition temperatures and an increase in the released heats during thermal decomposition compared with pure AP. The compound C4 showed the higher catalytic effect among the complexes series, and C5 exerted the highest energy release, in contrast to the other evaluated complexes and to the reported compounds CuO, [Cu2(en)2(HBTI)2]2 and Catocene.

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Combustion Characteristics of a Novel Grain‐Binding High Burning Rate Propellant

Cited by 8 publications

References 6 publications

Innovative Methods to Enhance the Combustion Properties of Solid Fuels for Hybrid Rocket Propulsion

Innovative Methods to Enhance the Combustion Properties of Solid Fuels for Hybrid Rocket Propulsion

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

Burning Rate Performance Study of Ammonium Perchlorate Catalyzed by Heteroleptic Copper(I) Complexes with Pyrazino[2,3‐f][1,10]phenanthroline‐Based Ligands

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