Incorporation of high explosives into nano-aluminum based microspheres to improve reactivity

Atomistic insight into the microexplosion-accelerated oxidation process of molten aluminum nanoparticles

Prediction of nano/micro aluminum particles ignition in oxygen atmosphere

Ignition and combustion of a single aluminum particle in hot gas flow

Effect of ambient temperature on the micro-explosion characteristics of soybean oil droplet: The phenomenon of evaporation induced vapor cloud

The embodiment of the invention provides a micron-scale metal particle ignition and combustion testing device The micron-scale metal particle ignition and combustion testing device comprises a metal particle dispersing device, a powder supply thin tube, a high-temperature fuel gas ignition system, an observation system and a particle sampling device, wherein the metal particle dispersing device is positioned under the high-temperature fuel gas ignition system and is connected with the high-temperature fuel gas ignition system through the powder supply thin tube; the observation system is arranged above the high-temperature fuel gas ignition system; the particle sampling device moves above the high-temperature fuel gas ignition system so as to realize sampling According to the micron-scale metal particle ignition and combustion testing device provided by the invention, a single micron-scale metal particle ignition and combustion state can be directly obtained, meanwhile, a metal particle ignition and combustion environment created by planar flame furnace is closer to an ignition and combustion environment of actual metal particles, and an engineering application value of obtained testing data is high

Micron-scale metal particle ignition and combustion testing device

The invention discloses a solid rocket engine with the continuous and adjustable thrust and a solid rocket. The solid rocket engine with the continuous and adjustable thrust comprises a fuel gas generation assembly, a combustion chamber and a tail jetting pipe which are sequentially connected; the fuel gas generation assembly comprises an oxygen-enriched fuel gas generator and an oxygen-deficientfuel gas generator; an oxygen-enriched containing cavity capable of containing an oxygen-enriched electrically-controlled solid propellant is arranged in the oxygen-enriched fuel gas generator, and the oxygen-enriched fuel gas generator is provided with an oxygen-enriched ablation circuit; an oxygen-deficient containing cavity capable of containing an oxygen-deficient electrically-controlled solidpropellant is arranged in the oxygen-deficient fuel gas generator, and the oxygen-deficient fuel gas generator is provided with an oxygen-deficient ablation circuit; and the oxygen-enriched fuel gasgenerator is provided with an oxygen-enriched controller capable of controlling the oxygen-enriched fuel gas flow, and the oxygen-deficient fuel gas generator is provided with an oxygen-deficient controller capable of controlling the oxygen-deficient fuel gas flow. Therefore, the problems that a traditional solid rocket engine is narrow in thrust adjusting range and high in technical difficulty and the problem that a liquid rocket engine supplying and adjusting system is complex can be solved.

Solid rocket engine with continuous and adjustable thrust and solid rocket

In this study, a CO2 laser ignition experimental system was built to study the ignition process and characteristics of the Nitrate Ester Plasticized Polyether (NEPE) propellant. The effect of the energy density, ingredients, and the grain size distribution of the propellant on the ignition process was investigated using a CO2 laser igniter, a high-speed camera, and a tungsten-rhenium thermocouple. Four types of NEPE propellants were tested under different laser heat fluxes, and the ignition delay time, the ignition temperature, and the ignition energy were obtained. Experimental results show that the ignition process of the NEPE propellant can be divided into three stages, namely the first-gasification stage, the first-flame stage, and the ignition delay stage. When the energy density is lower than the ignition energy threshold, the ignition process cannot be achieved even under continuous energy loading. The increase of the energy density can lead to the decrease of the ignition delay time but has little effect on the ignition temperature. The ingredients and grain size distribution have great effects on both the ignition delay time and the ignition temperature. The grain size effect of aluminum is the largest compared with that of Ammonium Perchlorate (AP) and octahydro-1,3,5,7-tetranitro-1,3,5,7-tetrazocine (HMX), while the grain size effect of AP is larger than that of HMX.

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Study on the Ignition Process and Characteristics of the Nitrate Ester Plasticized Polyether Propellant

In this paper, a modular solid scramjet combustor with multicavity was proposed. The influence of multicavity shape on the performance of solid scramjet was investigated by the direct-connected tests. The experiments simulated a flight Mach 5.5 at 25 km. The boron-based fuel-rich propellant was used. The microstructure of combustion products was analyzed by SEM. The experimental results show that the fuel-rich mixture produced by the gas generator would ignite rapidly in the solid scramjet combustor. The combustion process showed a typical characteristic of establishment-development-maintenance-attenuation. Compared to the flame-holding cavity, the other shapes of cavities, e.g., narrow and lobe, can improve mixing and combustion. In our experiment, the combustion efficiency increased from 0.41 to 0.48, and the total pressure recovery was 0.36. In summary, the proposed solid scramjet combustor can effectively solve the ignition delay problem of the fuel-rich mixture, and the narrow/lobe cavity shows the ability to improve the mixing and combustion of the fuel-rich mixture.

/pdf/influence-of-the-multicavity-shape-on-the-solid-scramjet-3ebuum0lst.pdf

Feng Yunchao

Papers

Micron-scale metal particle ignition and combustion testing device

Solid rocket engine with continuous and adjustable thrust and solid rocket

Study on the Ignition Process and Characteristics of the Nitrate Ester Plasticized Polyether Propellant

Influence of the Multicavity Shape on the Solid Scramjet

Analysis of agglomeration particle size near the burning surface of aluminized solid propellant based on digital inline holography