Study On Combustion Properties Of Hydrogen Peroxide Gel And Secondary Atomization Mend

On the background of promoting the combustion efficiency of fuel-rich propellant, some experiments were conducted to investigate the preparation, supply and atomization characteristics of the gel propellant, and relative numerical study for the combustion characteristics was also implemented. The forementioned work lay some experimental and theoretical foundation for the design and optimization of gel propellant motor.Considering the strong oxidizability and chemical unstability of hydrogen peroxide (H2O2), the molecular structure, gelling mechanism and technology of organic gallant and nano silicon dioxide(SiO2) and the stability of gel system comprising different gellants as the focus were analyzed. It is found that nano SiO2was coated by amount of active silicon hydroxyl that could produce some kind of space grid structure with hydrogen bond, and finally a gel system characterized for its stability and good response was formed. It implied from the further study that the stability of H2O2gel could be strongly improved by adding Span80and Tween60to H2O2gel system based nano SiO2At present work, a gel transport equipment having stable performance, high reliability adjustable flux and smooth operation was designed. Strength of every part of the equipment was calculated and tested on the basis of realistic experimental operation requirement. The equipment was established choosing appropriate parts in accordance with the strength. On the other hand, a rheometer and PIV(Particle Image Velocimetry) system produced by Brookfield and Dantec, respectively, were used for the sake of more precise study for the operational characteristics of H2O2gel propellant.For the hydrogen peroxide gel propellant, experiment platform choosing impingement type injector whose impact angle was adjustable was founded. PIV system was applied to investigate the influence of impact angle and pressure drop on impingement liquid sheet and distribution of spray velocity of the gel propellant simulants. Conclusions indicated that the increase of impact angle and impingement velocity could result in decrease of sheet breakup length and uniform distribution of droplets’velocity, two of them could influence the impingement atomization.There was abundant with combustible gas in the combustion product of fuel-rich propellant. Through injecting oxidizer into fuel-rich gas, combustion temperature could strongly improved with the amount of combustible components decreasing due to secondary combustion in the afterburning chamber. At present work, secondary combustion process was simulated using Fluent. The calculation indicated that combustion temperature was increased31.8%after the secondary combustion. Meanwhile, the mass rates of hydrogen(H2) and carbon monoxide(CO) were improved43.94%and34.94%, respectively.