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Experimental Research And Numerical Analysis Of Pulsed Plasma Thruster Power Supply And The Ablative Characteristics Of Characteristics Propellant

Posted on:2014-02-22Degree:MasterType:Thesis
Country:ChinaCandidate:J DengFull Text:PDF
GTID:2232330395982497Subject:Weapons project
Abstract/Summary:PDF Full Text Request
Electric propulsion is an important part in the aerospace field. Pulsed plasma thruster(PPT) is a kind of electromagnetic thruster, which has many characters of small volume, light weight, high reliability, low power consumption and high specific impulse. PPT tasks more use of such as position keeping, attitude controlling requirements of micro-satellites. Through the research of PPT, It could greatly promote the development of the space industry by improving its performance, thus so many countries have paid close attention to it. The traditional PPT is made of parallel plate electrodes, however the coaxial PPT which has three electrodes has much smaller size and higher efficiency.This article designed the three electrode coaxial pulsed plasma thruster structure with teflon propellant(PPT), And designed the pulse trigger ignition circuit and the capacitor energy storage pulsed power supply which meet the demand of PPT to charge and discharge. We set up the three electrode coaxial PPT experiment system, It includes vacuum system, PPT discharge system, electric parameters measurement system and the high speed video system. It details the system structure and principle. The measured data had been totally analyzed. Based on the experiment, This article structures the discharge model, ablation model and plume2d expansion model of the coaxial micro PPT. Discharge model and the ablation model are solved by the classical Runge-Kutta method. We analyse the effects of the parameter in loop and ablation characteristics of the propellant. In the plume2d expansion model, we ignore the force that ion in the electric field and magnetic field. The fluid could be seen as ideal gas, which inflations in the vacuum environment. This article adopted the CE/SE method for the solution. We can get the initial conditions from discharge model and ablation model.The comparative results between the experimental data and calculation value showed that the mathematical model algorithm is effective and reasonable. It could be used in the working process of PPT and be forecasted and analyzed.
Keywords/Search Tags:electric propulsion, pulsed plasma thruster, plume, numerical simulation
PDF Full Text Request
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