1,1-diamino-2,2-dinitroethene (FOX-7) an insensitive high-energetic compound, has rarely been reported previously with respect to combustion performance. In order to quickly apply it to propellants, the thermal decomposition behaviors of FOX-7 should be optimized. Metal complexes of nano-graphene oxide have an obvious effect on the thermal decomposition of energy materials. In this paper, the metal (Cu2+ and Fe3+) complexes of nano-graphene oxide (nGO) have been synthesized using nGO as a ligand and metal ions as a coordination center. They were mixed with FOX-7 as additives to form energetic composites, and the chemical bond distributions and thermal decomposition processes of these composites have been investigated. The results show that Cu2+ and Fe3+ are uniformly distributed on the surface of the nGO. The thermal decomposition processes of nGO-metal-FOX-7 composites have been fully characterized by Differential scanning calorimeter (DSC) and Thermal gravimetric analyzer-Differential scanning calorimeter-Infrared spectroscopy-Mass spectrum (TG-DSC-IR-MS) coupling technology. The results show that the Fe3+ based complex affect the decomposition of FOX-7 than the Cu2+ based one with the initial decomposition temperature of 230 °C and the apparent heat release of 3535.6 J·g-1. Moreover, the addition of nGO-metal complexes could promote the formation of nitrogen during the decomposition of FOX-7, indicating a more complete decomposition.

The Effects of Metal Complexes of Nano-Graphene Oxide to Thermal Decomposition of FOX-7.

An experimental investigation of the effect of boron (B) and aluminum (Al) additives to fuel-rich propellant for a solid fuel ramjet application was performed. In this research, depending on the co...

Combustion Characteristics of Ramjet Fuel Grains with Boron and Aluminum Additives

In this paper, experimental results of an aluminized fuel-rich propellant having energetics similar to boron-based fuel-rich propellant and having no residue after combustion are discussed. Using t...

Attaining Hypersonic Flight with Aluminum-Based Fuel-Rich Propellant

Performance Evaluation of Ramjet Fuel Grains with Boron and Magnesium Additives

According to the domestic and foreign institutions of solid fuel scramjet experimental data, adopt the numerical simulation method, design to construct the numerical model of the combustion chamber, using RNG k- turbulence model and eddy dissipation combustion model, simulation combustor working condition, analysis of the combustion chamber flow field data, concluded that the combustion phenomenon occurs mainly in the center of the flow field area. At the entrance of the combustion chamber can produce normal shock. The cavity can reduce the air velocity and it can guarantee the stability of the flame burning, and that to calculate the specific impulse is 126N·s/kg.

http://dpi-proceedings.com/index.php/dtmse/article/download/10838/10391

Flow Field Computational Analysis in a Solid Fuel Scramjet Combustor

It is well known that reduction of Ammonium Perchlorate (AP) content in composite propellant reduces the burn rate of solid composite propellants. Below a certain level of AP content the propellant does not burn. This paper explores ways to enhance the burn rate of fuel-rich composite solid propellant. The methods employed to enhance the burn rate of the propellant in the study are 1) Use of pyral 2) Recrystallization of AP, 3) Method to add catalyst into the propellant and 4) Addition of AC with moisture. Pyral was added as a metal fuel which resulted in propellants having higher burn rates and their density variations along the length were absent contrary to those without pyral. Addition of AC with moisture in these propellants increases the burn rate pressure index. The highest burn rate achieved is 3.8 mm/s at 70 bar with the propellant comprised of AP (particle size < 15 μm) and nanosized catalyst.

jogesh K. nanda

Papers

Development of AP/HTPB based Fuel-rich Propellant for Solid Propellant Ramjet