Mems-based Containing Thruster Performance Studies

Thruster is the important component for bit maintenance station keepingas well as well special attitude control of the micro satellite. The threelayers thruster arrays was designed and loading method of propellant and testmethod of micro thrust were investigated in paper. A numerical simulation ofstructure and mechanics properties was made for the micro thruster.When thepropellant was lead styphnate and nickel hydrazine nitrate, their propertiesof ignition and thrust were investigated . The main conclusions were following:1.A three layers micro thruster arrays was designed. The middle layer waschamber, the top layer was ignition circuit and the bottom layer containeda diaphragm with many nozzles. It could integrate 4×6 array on the prototypeWith 9mm×9mm.2. Design a vacuum system to load propellant, in experiment, the system got to the best condition when the vacuum was about 0. 4MP and the air flux was 250L·h^-1. A test device was designed which tested the properties of thrust according the scale, When the micro thrust was less than 20mN, it could be measured exactly.3. ANSYS was used to established an instantaneous micro-thermal conduct model, a numerical simulation of structure and mechanics properties was made for the micro-thruster, the distribution of the temperature, stress and strain was analyzed.4. When the main propulsion was nickel hydrazine nitrate and the chamber diameter ranged from 0.6mm to 1.8mm, the micro thrust ranged from 0.1mN to 1.6mN, impulse ranged from 0.41μN·s to 8μN·s, the micro thrust and impulse got more and more with the nitrocellulose density; When the main propulsion was lead styphnate and the chamber diameter ranged from 0.6mm to 2.0mm, the micro—thrust ranged from 0.7mN to 5.0mN, impulse ranged from 2.5μN ?s to 45μN?s , the micro-thrust and impulse were maximal when the nitrocellulose density was 15%.5. The theoretical result indicated that the micro-thruster's working course was a speedy combustion.