The Research Of Thruster Properties And Propellant Of Micro Chemical Thrusters

In this paper, the Micro chemical Thruster's structure was designed and loading method of propellant and test method of thrust were investigated. When the propellant was lead styphnate and nickel hydrazine nitrate, their properties of ignition and thrust were investigated under different chamber diameter and different proportion of themixed propellant. The influence of different thruster parameters on thruster properties was calculated. The main researches were as following:1. A three layers thruster was designed. The middle layer was chamber, the top layer was ignition circuit and the bottom layer contained a diaphragm with several nozzles. It could integrate 4 micro-thruster which diameter was 0.8mm on the diaphragm with 10*10*2mm.2. Design a vacuum method to load propellant into the micro-hole. A test device was designed which tested the properties of thrust according the theory of electromagnetism scale. Using the Hall-effect sensor to measure the scale displacement that could be converted the magnitude of the thrust. Using photoelectricity detector to measure the burning period. a3. Experiment testified that the properties of thrust of lead styphnate mixed with nitrocellulose was as the following: when the chamber diameter ranged from 0.5mm to 1.2mm, the thrust was about 0.05~0.38mN, impulse was about 3.2E-05-3.0E-04 mN-s.4. Experiment testified that the properties of thrust of nickel hydrazine nitrate mixed with nitrocellulose was as the following: when the chamber diameter ranged from 0.8mm to 1.5mm, the thrust was about 0.06~0.25mN, impulse was about 1.8E-03~1.0E-02mN-s.5. Calculating result showed: the thrust changing caused by the magnitude of At/Ac was more larger than that both of the pressure index: "n" and of the chamber diameter, and the best thrust could be get when At/Ac<0.3.